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EP1505261A1 - Device to control clearances in a gas turbine - Google Patents

Device to control clearances in a gas turbine Download PDF

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Publication number
EP1505261A1
EP1505261A1 EP04291818A EP04291818A EP1505261A1 EP 1505261 A1 EP1505261 A1 EP 1505261A1 EP 04291818 A EP04291818 A EP 04291818A EP 04291818 A EP04291818 A EP 04291818A EP 1505261 A1 EP1505261 A1 EP 1505261A1
Authority
EP
European Patent Office
Prior art keywords
air
ramps
ring assembly
air circulation
spacers
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP04291818A
Other languages
German (de)
French (fr)
Other versions
EP1505261B1 (en
Inventor
Alain Gendraud
Delphine Roussin
David Audeon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1505261A1 publication Critical patent/EP1505261A1/en
Application granted granted Critical
Publication of EP1505261B1 publication Critical patent/EP1505261B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components

Definitions

  • the present invention relates to the general field of game control between the top of rotating blades and a set to fixed ring of a gas turbine.
  • a gas turbine for example a high-pressure turbine of turbomachine, typically comprises a plurality of stationary vanes arranged alternating with a plurality of blades in the gas passage hot from the combustion chamber of the turbomachine.
  • the blades movable turbine are surrounded on the entire circumference of the turbine by a set with fixed ring. This fixed ring set defines the flow of hot gases through the vanes of the turbine.
  • Such means generally present in the form of annular conduits which surround the fixed ring assembly and are traversed by air taken from other parts of the turbomachine. This air is injected on the outer surface of the fixed ring assembly opposite the vein of hot gas flow and thus causes expansion or thermal contractions of the fixed ring assembly varying its diameter.
  • these thermal dilations and contractions are controlled according to the operating speed of the gas turbine by through a valve that allows to control the flow and the temperature of the air supplying the pipes.
  • the group consisting of pipes and the valve thus forms a game steering box at the top blade.
  • the air of the steering boxes which was injected on the outer surface of the fixed ring assembly shall be evacuated to outside. This evacuation of the air must be able to take place without as much disturb the flow of air that is injected on the surface outer ring fixed assembly.
  • the air to be evacuated generally tends to to disrupt the flow of air that is injected, which decreases the efficiency of the game steering box at the top of the blades.
  • the present invention therefore aims to overcome such drawbacks by providing a game control device that allows you to obtain a high temperature homogeneity of the fixed ring assembly while avoiding disturbances between the air to be evacuated and the air to be injected.
  • a game control device between the top of rotating vanes and a fixed ring assembly of a turbine to gas, the device comprising a circular control casing surrounding the fixed ring assembly, characterized in that the control box has at least two spaced apart annular air circulation ramps each other in the axial direction and each comprising a plurality of perforations to change the temperature of the fixed ring assembly by air discharge, an annular channel of spaced air supply radially of the air circulation ramps, at least one air duct for supplying air to the supply channel, and a plurality of spacers distribution channels connecting the air supply channel to the ramps circulation of air to supply air to the air while allowing the air having been discharged on the fixed ring assembly to flow between the supply canal and traffic ramps to be evacuated.
  • Radial spacing between feed channel and ramps air flow control box provides a space for vent the air that has been discharged to the fixed ring assembly. In this way, the air that has been discharged is discharged radially and does not disturb the flow of air discharging on the fixed ring assembly.
  • This radial spacing also makes it possible to avoid any exchange between the supply channel and the air circulation ramps of the control box, which improves the efficiency of the control device of play
  • the fixed ring assembly comprises a housing internal which is surrounded by an outer casing of the gas turbine so to define an annular chamber in which is mounted the housing of piloting.
  • the steering box may be in waterproof support, at a axial end upstream, against the outer casing, and at one axial end downstream, against the inner casing in order to define, inside the chamber ring, an upstream air discharge chamber and a downstream chamber exhaust air tight relative to the upstream enclosure.
  • the arrangement, number and diameter of drilling Hollow distribution spacers regulate the airflow feeding the air circulation ramps and thus to homogenize the temperature of the fixed ring assembly.
  • the distribution spacers connecting the channel feeding at one of the air circulation ramps can be angularly aligned or offset from the spacers of distribution of other air circulation ramps, and spacing angle between two successive distribution spacers does not exceed preferably no more than 45 °.
  • FIG. 1 illustrates, in longitudinal section, a high-pressure turbine 2 turbomachine equipped with a game control device according to the invention.
  • the present invention could also apply to a turbomachine low-pressure turbine or any other type of machine equipped with a game control device.
  • the high-pressure turbine 2 is composed in particular of a plurality of blades 4 arranged in a flow passage of hot gases 6 from a combustion chamber (not shown) of the turbine engine. These blades 4 are arranged downstream of blades 8 of the turbine with respect to the flow direction of the hot gases in passage 6.
  • the blades 4 of the high-pressure turbine 2 are surrounded by a plurality of fixed ring segments 14 arranged circumferentially around the axis of the turbine so as to form a circular and continuous surface.
  • These ring segments 12 are mounted on an internal casing 14 of the turbomachine by means of a plurality 16.
  • the inner casing 14 of the fixed ring assembly is provided with vanes or annular bumps 18 which have a disk shape extending in a radial direction.
  • These fins 18 have the function principal to act as a heat exchanger. In Figure 1, the fins 18 There are two of them. However, we can imagine a number more important fins.
  • the fixed ring segments 12 have an inner surface 12a directly in contact with the hot gases and which partly defines the flow passage of hot gases 6.
  • a radial space is left between the inner surface 12a of the ring segments 12 and the top 4a of the turbine blades 4 of the turbine to allow rotation of the latter.
  • This radial space thus defines a game 20 that it is necessary to reduce as much as possible so to increase the efficiency of the turbine.
  • a game control device formed of a circular housing of steering 22 surrounding the fixed ring assembly, and more specifically the internal casing 14.
  • this pilot box 22 is intended to cool or heat the fins 18 of the inner casing 14 by discharge (or impact) of air thereon. Under the effect of this discharge of air, the inner casing 14 retracts or expands, which decreases or increases the diameter of the fixed ring segments 12 of the turbine.
  • control box 22 of the device game control comprises at least two annular traffic ramps air 24 spaced apart from each other in the axial direction. These ramps annular air circulation 24 surround the inner casing 14 of the fixed ring assembly.
  • the air circulation ramps 24 each comprise a plurality of perforations 26 for discharging air on the fins 18 of the internal casing 14.
  • perforations 26 of each ramp 24 are in the form of three rows of perforations.
  • the fins 18 of the inner casing 14 are at number of two, so that the pilot box 22 has three air circulation ramps 24 spaced from each other in the axial direction: a central ramp 24a disposed between the two fins 18, and a ramp upstream 24b and a downstream ramp 24c disposed respectively upstream and downstream of the central ramp 24a.
  • the air circulation ramps 24 marry approximately the shape of the fins 18. In this case, they present each a substantially rectangular cross section.
  • the control box 22 also comprises an annular channel supplying air 28 to supply air to the traffic ramps
  • the air supply channel 28 surrounds the ramps of circulation 24.
  • At least one air line 30 opens into the feed channel 28 to supply it with air.
  • the air circulating in the air duct 30 is taken from other levels parts of the turbomachine. For example, this air can be taken from level of one or more stages of high or low compressors pressure of the turbomachine, or at the blower thereof.
  • the air sampling is controlled by a valve of regulation (not shown) which allows to provide air more or less charge to the pilot box 22 according to the operating regime of the turbine engine.
  • the air supply channel 28 and the traffic ramps 24 are radially spaced and are interconnected by a plurality of hollow distribution spacers 32.
  • the hollow distribution spacers 32 supply the air with traffic ramps 24 while allowing the air having been discharged on the fins 18 of the inner casing 14 to circulate axially between the channel supply air 28 and the air circulation ramps 24 to be there evacuated.
  • Figure 2 illustrates more precisely the path of the air intended to be evacuated.
  • the arrows F1 represent the Tangential directions of air flow in the feed channel 28 and in the air circulation ramps 24, while the F2 arrow illustrates the axial direction of flow of the air having been discharged on the fins of the inner casing.
  • the turbine 2 is advantageously provided with an outer casing 34 surrounding the casing internal 14 of the fixed ring assembly. At an upstream axial end, this outer casing 34 is fixed to the inner casing 14 by a fastener 36 of the type screw nut.
  • the internal casings 14 and outer 34 define between them a annular chamber 38 in which is mounted the control box 22 of the game control device according to the invention. More precisely, the housing 22 is supported, at an upstream axial end 22a, against the outer casing 34, and, at a downstream axial end 22b, against the casing 14. Preferably, the support of the upstream ends 22a and downstream 22b of the control box 22 is effected in a sealed manner, via of seals 40.
  • control box 22 with respect to internal casings 14 and outer 34 and allows to define, inside of the annular chamber 38, an upstream chamber 42a called “discharge of air "and a downstream enclosure 42b called” exhaust air “which is waterproof in the air relative to the upstream chamber 42a.
  • the air that has been discharged by the air circulation ramps 24, and in particular by the upstream ramp 24b, is confined in the enclosure upstream discharge 42a and can be evacuated by circulating between the supply channel 28 and the traffic ramps 24.
  • the sealing performed at the upstream end 22a of the control box 22 prevents air from bypassing the pilot housing 22 to be evacuated.
  • the air that has been discharged by the downstream ramp 24c is constrained by the sealing performed at the downstream end 22b of the control box 22, circulate between the supply channel 28 and the traffic ramps 24 to be evacuated.
  • the air that has been discharged on fins 18 of the inner casing 14 and which is evacuated between the channel supply 28 and the traffic ramps 24 is then confined in the downstream exhaust air chamber 42b.
  • the inner casing 14 has, at one end axial downstream, an opening 44 opening in the downstream exhaust enclosure 42b air to evacuate the air confined therein.
  • This opening 44 which can provided with a sleeve 46, thus evacuate the air having been discharged on the fins 18 of the inner casing to feed for example the first floor a low-pressure distributor (not shown) of the turbomachine.
  • FIGS. 3A and 3B We will now describe two possible configurations of game control device according to the invention by referring more particularly in FIGS. 3A and 3B.
  • the steering box is composed of two distinct angular sectors housing 48 (or half-housings of 180 ° each) of which only one is shown in Figures 3A and 3B. These two casing sectors 48 are fixed together by fasteners of the type screw / nut which cooperate with orifices 50 (FIG. 1) arranged at each angular end of the housing sectors.
  • pilot box is composed of more than two distinct angular sectors of housing which, once put end to end, together form a 360 ° housing.
  • Housing sectors 48 shown in FIGS. 3A and 3B are closed at each of their angular ends, so that the air does not not move from one housing sector to another. However, it is also possible to make a connection between the housing sectors in order to allow a passage of air from one housing sector to another.
  • Each housing sector 48 is also powered by a single air duct 30 opening into the feed channel 28 to equidistant from the two angular ends of the housing sector.
  • the air duct could also lead to one of the angular ends housing sector.
  • air ducts are also conceivable.
  • each case sector 48 four hollow distribution spacers 32 connecting the feed channel 28 at the traffic ramp 24 shown.
  • These hollow spacers of distribution 32 are arranged on the half-circumference of the sector of casing 48 so that the angular distance between two spacers successive does not exceed preferably 45 °.
  • five hollow distribution spacers 32 connect the supply channel 28 to the circulation ramp 24 shown. More particularly, a distribution spacer is arranged at each angular end of the housing sector and the angular distance between two successive spacers preferably do not exceed preferably 45 ° about.
  • Hollow distribution spacers may vary for each boom air circulation of the same housing sector.
  • the hollow spacers distribution system connecting the feed channel to one of the air circulation can be angularly offset from hollow distribution spacers connecting the feed channel with least one of the other air circulation ramps.
  • the angular offset of the hollow distribution spacers between the air circulation ramps allows for better homogeneity of temperature in the control box and to avoid any distortion of the fixed ring assembly.
  • Such an angular offset can for example be obtained in the case of the same housing sector with three traffic ramps as in Figures 1 and 2.
  • the central ramp 24a (or conversely the upstream ramps 24b and downstream 24c) can have the configuration of Figure 3A
  • the upstream ramps 24b and downstream 24c (or conversely the central ramp 24a) can have the configuration of Figure 3B.
  • Such a provision is similar for the three ramps 24a, 24b and 24c, in a quincunx arrangement of distribution spacers 32 with a symmetry of arrangement between the upstream ramp 24b and the downstream ramp 24c.
  • This symmetry of arrangement makes it possible to obtain a dilation or a substantially identical thermal contraction between the two fins 18 of the internal casing 14 so as to improve the temperature homogeneity of the fixed ring assembly.
  • the hollow distribution spacers connecting the supply channel of the same sector of housing to one of the ramps of air circulation can be aligned angularly with respect to hollow distribution spacers connecting the feed channel with the other air circulation ramps.
  • an angular alignment of the hollow spacers of FIGS. distribution can be achieved by giving to the three traffic ramps of air the same configuration.
  • this configuration of the three air circulation ramps may be identical to that of Figure 3A or Figure 3B.
  • each air circulation of the same sector of housing is supplied with air than by a single hollow distribution spacer connected to the canal Power.
  • this distribution spacer is an angular end of the housing sector, the circulation of air in the ramp is carried out only in one and the same tangential direction.
  • the drilling diameter of the hollow distribution spacers may vary from one spacer to another for the same traffic ramp air.
  • the variation of the diameter of the distribution spacers thus offers the possibility of regulating the air flow supplying the next ramp the angular location of the spacer so as to improve the temperature homogeneity of the fixed ring assembly.
  • the number, the Drilling diameter and layout of the distribution spacers may vary for the same traffic ramp and for the same housing sector. These different parameters are chosen so as to minimize distortion of the fixed ring assembly.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The device has a circular control box (22) surrounding a fixed ring set of a gas turbine. The box has two annular air circulation rails that are spaced from each other. The rails have perforations that modify temperature of the ring set. Hollow spacers (32) connect an air supply channel (28) to the rails in order to supply air in the rails and permit the air to be discharged in the ring set.

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général du contrôle de jeu entre le sommet d'aubes rotatives et un ensemble à anneau fixe d'une turbine à gaz.The present invention relates to the general field of game control between the top of rotating blades and a set to fixed ring of a gas turbine.

Une turbine à gaz, par exemple une turbine haute-pression de turbomachine, comporte typiquement une pluralité d'aubes fixes disposées en alternance avec une pluralité d'aubes mobiles dans le passage de gaz chauds issus de la chambre de combustion de la turbomachine. Les aubes mobiles de la turbine sont entourées sur toute la circonférence de la turbine par un ensemble à anneau fixe. Cet ensemble à anneau fixe définit la veine d'écoulement des gaz chauds à travers les aubes de la turbine.A gas turbine, for example a high-pressure turbine of turbomachine, typically comprises a plurality of stationary vanes arranged alternating with a plurality of blades in the gas passage hot from the combustion chamber of the turbomachine. The blades movable turbine are surrounded on the entire circumference of the turbine by a set with fixed ring. This fixed ring set defines the flow of hot gases through the vanes of the turbine.

Afin d'accroítre le rendement d'une telle turbine, il est connu de réduire autant que possible le jeu existant entre le sommet des aubes mobiles de la turbine et les parties de l'ensemble à anneau fixe qui leur font face. Pour y parvenir, des moyens permettant de faire varier le diamètre de l'ensemble à anneau fixe ont été élaborés. De tels moyens se présentent généralement sous la forme de conduites annulaires qui entourent l'ensemble à anneau fixe et qui sont parcourues par de l'air prélevé sur d'autres parties de la turbomachine. Cet air est injecté sur la surface extérieure de l'ensemble à anneau fixe qui est opposée à la veine d'écoulement des gaz chauds et provoque ainsi des dilatations ou des contractions thermiques de l'ensemble à anneau fixe faisant varier son diamètre. Généralement, ces dilatations et contractions thermiques sont commandées selon le régime de fonctionnement de la turbine à gaz par l'intermédiaire d'une vanne qui permet de contrôler le débit et la température de l'air alimentant les conduites. L'ensemble constitué par les conduites et la vanne forme ainsi un boítier de pilotage du jeu en sommet d'aubes.In order to increase the efficiency of such a turbine, it is known to reduce as much as possible the existing gap between the top of the blades turbines and the parts of the fixed ring assembly which face. To achieve this, ways to vary the diameter of the fixed ring set were developed. Such means generally present in the form of annular conduits which surround the fixed ring assembly and are traversed by air taken from other parts of the turbomachine. This air is injected on the outer surface of the fixed ring assembly opposite the vein of hot gas flow and thus causes expansion or thermal contractions of the fixed ring assembly varying its diameter. Generally, these thermal dilations and contractions are controlled according to the operating speed of the gas turbine by through a valve that allows to control the flow and the temperature of the air supplying the pipes. The group consisting of pipes and the valve thus forms a game steering box at the top blade.

Les boítiers de pilotage connus jusqu'à présent ne permettent pas toujours d'obtenir une grande uniformité de température sur toute la circonférence de l'ensemble à anneau fixe. Un manque d'homogénéité de température engendre des distorsions de l'ensemble à anneau fixe qui sont particulièrement préjudiciables au rendement et à la durée de vie de la turbine à gaz.The steering boxes known until now do not allow not always to get a great temperature uniformity all over the circumference of the fixed ring assembly. A lack of homogeneity temperature causes distortions of the fixed ring assembly which are particularly detrimental to the performance and life of the the gas turbine.

Par ailleurs, l'air des boítiers de pilotage qui a été injecté sur la surface extérieure de l'ensemble à anneau fixe doit être évacué vers l'extérieur. Cette évacuation de l'air doit pouvoir se dérouler sans pour autant perturber l'écoulement de l'air qui est injecté sur la surface extérieure de l'ensemble à anneau fixe. Toutefois, dans les boítiers de pilotage connus, on constate que l'air à évacuer a généralement tendance à perturber l'écoulement de l'air qui est injecté, ce qui diminue l'efficacité du boítier de pilotage du jeu en sommet d'aubes.Moreover, the air of the steering boxes which was injected on the outer surface of the fixed ring assembly shall be evacuated to outside. This evacuation of the air must be able to take place without as much disturb the flow of air that is injected on the surface outer ring fixed assembly. However, in the boxes of piloting, it can be seen that the air to be evacuated generally tends to to disrupt the flow of air that is injected, which decreases the efficiency of the game steering box at the top of the blades.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention vise donc à pallier de tels inconvénients en proposant un dispositif de contrôle de jeu qui permet d'obtenir une grande homogénéité de température de l'ensemble à anneau fixe tout en évitant des perturbations entre l'air à évacuer et l'air à injecter.The present invention therefore aims to overcome such drawbacks by providing a game control device that allows you to obtain a high temperature homogeneity of the fixed ring assembly while avoiding disturbances between the air to be evacuated and the air to be injected.

A cet effet, il est prévu un dispositif de contrôle de jeu entre le sommet d'aubes rotatives et un ensemble à anneau fixe d'une turbine à gaz, le dispositif comprenant un boítier circulaire de pilotage entourant l'ensemble à anneau fixe, caractérisé en ce que le boítier de pilotage comporte au moins deux rampes annulaires de circulation d'air espacées l'une de l'autre dans le sens axial et comportant chacune une pluralité de perforations pour modifier la température de l'ensemble à anneau fixe par décharge d'air, un canal annulaire d'alimentation en air espacé radialement des rampes de circulation d'air, au moins une conduite d'air pour alimenter en air le canal d'alimentation, et une pluralité d'entretoises creuses de distribution reliant le canal d'alimentation en air aux rampes de circulation d'air afin d'alimenter en air ces dernières tout en permettant à l'air ayant été déchargé sur l'ensemble à anneau fixe de circuler entre le canal d'alimentation et les rampes de circulation pour y être évacué.For this purpose, there is provided a game control device between the top of rotating vanes and a fixed ring assembly of a turbine to gas, the device comprising a circular control casing surrounding the fixed ring assembly, characterized in that the control box has at least two spaced apart annular air circulation ramps each other in the axial direction and each comprising a plurality of perforations to change the temperature of the fixed ring assembly by air discharge, an annular channel of spaced air supply radially of the air circulation ramps, at least one air duct for supplying air to the supply channel, and a plurality of spacers distribution channels connecting the air supply channel to the ramps circulation of air to supply air to the air while allowing the air having been discharged on the fixed ring assembly to flow between the supply canal and traffic ramps to be evacuated.

L'espacement radial entre le canal d'alimentation et les rampes de circulation d'air du boítier de pilotage fournit ainsi un espace pour évacuer l'air ayant été déchargé sur l'ensemble à anneau fixe. De la sorte, l'air qui a été déchargé est évacué radialement et ne perturbe pas l'écoulement de l'air venant se décharger sur l'ensemble à anneau fixe.Radial spacing between feed channel and ramps air flow control box provides a space for vent the air that has been discharged to the fixed ring assembly. In this way, the air that has been discharged is discharged radially and does not disturb the flow of air discharging on the fixed ring assembly.

Cet espacement radial permet également d'éviter tout échange thermique entre le canal d'alimentation et les rampes de circulation d'air du boítier de pilotage, ce qui améliore l'efficacité du dispositif de contrôle de jeu.This radial spacing also makes it possible to avoid any exchange between the supply channel and the air circulation ramps of the control box, which improves the efficiency of the control device of play

De préférence, l'ensemble à anneau fixe comporte un carter interne qui est entouré par un carter externe de la turbine à gaz de façon à définir une chambre annulaire dans laquelle est monté le boítier de pilotage.Preferably, the fixed ring assembly comprises a housing internal which is surrounded by an outer casing of the gas turbine so to define an annular chamber in which is mounted the housing of piloting.

Le boítier de pilotage peut être en appui étanche, à une extrémité axiale amont, contre le carter externe, et, à une extrémité axiale aval, contre le carter interne afin de définir, à l'intérieur de la chambre annulaire, une enceinte amont de décharge d'air et une enceinte aval d'évacuation d'air étanche par rapport à l'enceinte amont.The steering box may be in waterproof support, at a axial end upstream, against the outer casing, and at one axial end downstream, against the inner casing in order to define, inside the chamber ring, an upstream air discharge chamber and a downstream chamber exhaust air tight relative to the upstream enclosure.

La disposition, le nombre et le diamètre de perçage des entretoises creuses de distribution permet de réguler le débit d'air alimentant les rampes de circulation d'air et donc d'homogénéiser la température de l'ensemble à anneau fixe.The arrangement, number and diameter of drilling Hollow distribution spacers regulate the airflow feeding the air circulation ramps and thus to homogenize the temperature of the fixed ring assembly.

Notamment, les entretoises de distribution reliant le canal d'alimentation à l'une des rampes de circulation d'air peuvent être angulairement alignées ou décalées par rapport aux entretoises de distribution des autres rampes de circulation d'air, et l'espacement angulaire entre deux entretoises de distribution successives ne dépasse pas de préférence 45° environ.In particular, the distribution spacers connecting the channel feeding at one of the air circulation ramps can be angularly aligned or offset from the spacers of distribution of other air circulation ramps, and spacing angle between two successive distribution spacers does not exceed preferably no more than 45 °.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue en coupe longitudinale d'un dispositif de contrôle de jeu selon l'invention ;
  • la figure 2 est une vue partielle en perspective et en écorché du dispositif de contrôle de jeu de la figure 1 ; et
  • les figures 3A et 3B illustrent partiellement en coupe transversale deux configurations possibles du dispositif de contrôle de jeu selon l'invention.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • Figure 1 is a longitudinal sectional view of a game control device according to the invention;
  • Figure 2 is a partial perspective and cutaway view of the game control device of Figure 1; and
  • Figures 3A and 3B partially illustrate in cross section two possible configurations of the game control device according to the invention.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

La figure 1 illustre, en coupe longitudinale, une turbine haute-pression 2 de turbomachine équipée d'un dispositif de contrôle de jeu selon l'invention. Toutefois, la présente invention pourrait également s'appliquer à une turbine basse-pression de turbomachine ou à tout autre type de machine équipée d'un dispositif de contrôle de jeu.FIG. 1 illustrates, in longitudinal section, a high-pressure turbine 2 turbomachine equipped with a game control device according to the invention. However, the present invention could also apply to a turbomachine low-pressure turbine or any other type of machine equipped with a game control device.

La turbine haute-pression 2 se compose notamment d'une pluralité d'aubes mobiles 4 disposées dans un passage d'écoulement de gaz chauds 6 issus d'une chambre de combustion (non représentée) de la turbomachine. Ces aubes mobiles 4 sont disposées en aval d'aubes fixes 8 de la turbine par rapport à la direction d'écoulement 10 des gaz chauds dans le passage 6.The high-pressure turbine 2 is composed in particular of a plurality of blades 4 arranged in a flow passage of hot gases 6 from a combustion chamber (not shown) of the turbine engine. These blades 4 are arranged downstream of blades 8 of the turbine with respect to the flow direction of the hot gases in passage 6.

Les aubes mobiles 4 de la turbine haute-pression 2 sont entourées par une pluralité de segments d'anneau fixe 14 disposés circonférentiellement autour de l'axe de la turbine de façon à former une surface circulaire et continue. Ces segments d'anneau 12 sont montés sur un carter interne 14 de la turbomachine par l'intermédiaire d'une pluralité d'entretoises 16. Pour la suite de la description, on désignera l'ensemble formé des segments d'anneau fixe 12, du carter interne 14 et des entretoises 16 par l'expression « ensemble à anneau fixe ».The blades 4 of the high-pressure turbine 2 are surrounded by a plurality of fixed ring segments 14 arranged circumferentially around the axis of the turbine so as to form a circular and continuous surface. These ring segments 12 are mounted on an internal casing 14 of the turbomachine by means of a plurality 16. For the rest of the description, we will designate the whole formed of the fixed ring segments 12, the inner casing 14 and the spacers 16 by the term "fixed ring assembly".

Le carter interne 14 de l'ensemble à anneau fixe est muni d'ailettes ou bosses annulaires 18 qui présentent une forme de disque s'étendant selon une direction radiale. Ces ailettes 18 ont pour fonction principale d'agir en échangeur de chaleur. Sur la figure 1, les ailettes 18 sont au nombre de deux. On peut toutefois imaginer un nombre plus important d'ailettes.The inner casing 14 of the fixed ring assembly is provided with vanes or annular bumps 18 which have a disk shape extending in a radial direction. These fins 18 have the function principal to act as a heat exchanger. In Figure 1, the fins 18 There are two of them. However, we can imagine a number more important fins.

Les segments d'anneau fixe 12 présentent une surface interne 12a directement en contact avec les gaz chauds et qui définit en partie le passage d'écoulement des gaz chauds 6.The fixed ring segments 12 have an inner surface 12a directly in contact with the hot gases and which partly defines the flow passage of hot gases 6.

Un espace radial est laissé entre la surface interne 12a des segments d'anneau 12 et le sommet 4a des aubes mobiles 4 de la turbine pour permettre la rotation de ces dernières. Cet espace radial définit ainsi un jeu 20 qu'il est nécessaire de réduire autant que possible afin d'accroítre le rendement de la turbine.A radial space is left between the inner surface 12a of the ring segments 12 and the top 4a of the turbine blades 4 of the turbine to allow rotation of the latter. This radial space thus defines a game 20 that it is necessary to reduce as much as possible so to increase the efficiency of the turbine.

Afin de réduire le jeu 20 en sommet des aubes mobiles 4, il est prévu un dispositif de contrôle de jeu formé d'un boítier circulaire de pilotage 22 entourant l'ensemble à anneau fixe, et plus précisément le carter interne 14.In order to reduce the clearance 20 at the top of the blades 4, it is provided a game control device formed of a circular housing of steering 22 surrounding the fixed ring assembly, and more specifically the internal casing 14.

Selon les régimes de fonctionnement de la turbomachine, ce boítier de pilotage 22 est destiné à refroidir ou à réchauffer les ailettes 18 du carter interne 14 par décharge (ou impact) d'air sur celles-ci. Sous l'effet de cette décharge d'air, le carter interne 14 se rétracte ou se dilate, ce qui diminue ou augmente le diamètre des segments d'anneau fixe 12 de la turbine.According to the operating modes of the turbomachine, this pilot box 22 is intended to cool or heat the fins 18 of the inner casing 14 by discharge (or impact) of air thereon. Under the effect of this discharge of air, the inner casing 14 retracts or expands, which decreases or increases the diameter of the fixed ring segments 12 of the turbine.

Selon l'invention, le boítier de pilotage 22 du dispositif de contrôle de jeu comporte au moins deux rampes annulaires de circulation d'air 24 espacées l'une de l'autre dans le sens axial. Ces rampes annulaires de circulation d'air 24 entourent le carter interne 14 de l'ensemble à anneau fixe.According to the invention, the control box 22 of the device game control comprises at least two annular traffic ramps air 24 spaced apart from each other in the axial direction. These ramps annular air circulation 24 surround the inner casing 14 of the fixed ring assembly.

Les rampes de circulation d'air 24 comportent chacune une pluralité de perforations 26 pour décharger de l'air sur les ailettes 18 du carter interne 14. Sur l'exemple de réalisation de la figure 1, les perforations 26 de chaque rampe 24 se présentent sous la forme de trois rangées de perforations.The air circulation ramps 24 each comprise a plurality of perforations 26 for discharging air on the fins 18 of the internal casing 14. In the embodiment of FIG. perforations 26 of each ramp 24 are in the form of three rows of perforations.

Sur la figure 1, les ailettes 18 du carter interne 14 sont au nombre de deux, de sorte que le boítier de pilotage 22 comporte trois rampes de circulation d'air 24 espacées l'une de l'autre dans le sens axial : une rampe centrale 24a disposée entre les deux ailettes 18, et une rampe amont 24b et une rampe aval 24c disposées respectivement en amont et en aval de la rampe centrale 24a.In FIG. 1, the fins 18 of the inner casing 14 are at number of two, so that the pilot box 22 has three air circulation ramps 24 spaced from each other in the axial direction: a central ramp 24a disposed between the two fins 18, and a ramp upstream 24b and a downstream ramp 24c disposed respectively upstream and downstream of the central ramp 24a.

Avantageusement, les rampes de circulation d'air 24 épousent approximativement la forme des ailettes 18. En l'espèce, elles présentent chacune une section droite sensiblement rectangulaire.Advantageously, the air circulation ramps 24 marry approximately the shape of the fins 18. In this case, they present each a substantially rectangular cross section.

Le boítier de pilotage 22 comporte également un canal annulaire d'alimentation en air 28 pour fournir de l'air aux rampes de circulation d'air 24. Le canal d'alimentation en air 28 entoure les rampes de circulation 24. The control box 22 also comprises an annular channel supplying air 28 to supply air to the traffic ramps The air supply channel 28 surrounds the ramps of circulation 24.

De plus, au moins une conduite d'air 30 (figures 3A et 3B) débouche dans le canal d'alimentation 28 afin d'alimenter celui-ci en air. L'air circulant dans la conduite d'air 30 est prélevé au niveau d'autres parties de la turbomachine. Par exemple, cet air peut être prélevé au niveau d'un ou de plusieurs étages des compresseurs haute ou basse pression de la turbomachine, ou bien au niveau de la soufflante de celle-ci.In addition, at least one air line 30 (FIGS. 3A and 3B) opens into the feed channel 28 to supply it with air. The air circulating in the air duct 30 is taken from other levels parts of the turbomachine. For example, this air can be taken from level of one or more stages of high or low compressors pressure of the turbomachine, or at the blower thereof.

Le prélèvement de l'air est commandé par une vanne de régulation (non représentée) qui permet de fournir de l'air plus ou moins frais au boítier de pilotage 22 selon le régime de fonctionnement de la turbomachine.The air sampling is controlled by a valve of regulation (not shown) which allows to provide air more or less charge to the pilot box 22 according to the operating regime of the turbine engine.

Le canal d'alimentation en air 28 et les rampes de circulation d'air 24 sont espacés dans le sens radial et sont reliés entre eux par une pluralité d'entretoises creuses de distribution 32.The air supply channel 28 and the traffic ramps 24 are radially spaced and are interconnected by a plurality of hollow distribution spacers 32.

Les entretoises creuses de distribution 32 alimentent en air les rampes de circulation 24 tout en permettant à l'air ayant été déchargé sur les ailettes 18 du carter interne 14 de circuler axialement entre le canal d'alimentation en air 28 et les rampes de circulation d'air 24 pour y être évacué.The hollow distribution spacers 32 supply the air with traffic ramps 24 while allowing the air having been discharged on the fins 18 of the inner casing 14 to circulate axially between the channel supply air 28 and the air circulation ramps 24 to be there evacuated.

La figure 2 illustre plus précisément le cheminement de l'air destiné à être évacué. Sur cette figure, les flèches F1 représentent les directions tangentielles d'écoulement de l'air dans le canal d'alimentation 28 et dans les rampes de circulation d'air 24, tandis que la flèche F2 illustre la direction axiale d'écoulement de l'air ayant été déchargé sur les ailettes du carter interne.Figure 2 illustrates more precisely the path of the air intended to be evacuated. In this figure, the arrows F1 represent the Tangential directions of air flow in the feed channel 28 and in the air circulation ramps 24, while the F2 arrow illustrates the axial direction of flow of the air having been discharged on the fins of the inner casing.

De la sorte, l'air qui a été déchargé sur les ailettes 18 du carter interne 14 ne perturbe pas l'écoulement de l'air traversant les perforations 26 des rampes de circulation 24. Cette disposition particulière permet ainsi d'améliorer l'efficacité du dispositif de contrôle du jeu 20 en sommet des aubes mobiles 4 de la turbine.In this way, the air that has been discharged on the fins 18 of the housing internal 14 does not disturb the flow of air through the perforations 24 of the circulation ramps. This particular provision allows to improve the efficiency of the game control device 20 at the top of the moving blades 4 of the turbine.

Afin de s'assurer que l'air qui a été déchargé sur les ailettes 18 soit effectivement évacué en circulant axialement entre le canal d'alimentation en air 28 et les rampes de circulation d'air 24, la turbine 2 est avantageusement munie d'un carter externe 34 entourant le carter interne 14 de l'ensemble à anneau fixe. A une extrémité axiale amont, ce carter externe 34 est fixé au carter interne 14 par une attache 36 de type vis/écrou.To ensure that the air that has been discharged on the fins 18 is effectively evacuated by flowing axially between the canal supply air 28 and the air circulation ramps 24, the turbine 2 is advantageously provided with an outer casing 34 surrounding the casing internal 14 of the fixed ring assembly. At an upstream axial end, this outer casing 34 is fixed to the inner casing 14 by a fastener 36 of the type screw nut.

Les carters interne 14 et externe 34 définissent entre eux une chambre annulaire 38 dans laquelle est monté le boítier de pilotage 22 du dispositif de contrôle de jeu selon l'invention. Plus précisément, le boítier de pilotage 22 est en appui, à une extrémité axiale amont 22a, contre le carter externe 34, et, à une extrémité axiale aval 22b, contre le carter interne 14. De préférence, l'appui des extrémités amont 22a et aval 22b du boítier de pilotage 22 s'effectue de façon étanche, par l'intermédiaire de joints d'étanchéité 40.The internal casings 14 and outer 34 define between them a annular chamber 38 in which is mounted the control box 22 of the game control device according to the invention. More precisely, the housing 22 is supported, at an upstream axial end 22a, against the outer casing 34, and, at a downstream axial end 22b, against the casing 14. Preferably, the support of the upstream ends 22a and downstream 22b of the control box 22 is effected in a sealed manner, via of seals 40.

La disposition particulière du boítier de pilotage 22 par rapport aux carters interne 14 et externe 34 permet ainsi de définir, à l'intérieur de la chambre annulaire 38, une enceinte amont 42a dite « de décharge d'air » et une enceinte aval 42b dite « d'évacuation d'air » qui est étanche à l'air par rapport à l'enceinte amont 42a.The particular arrangement of the control box 22 with respect to internal casings 14 and outer 34 and allows to define, inside of the annular chamber 38, an upstream chamber 42a called "discharge of air "and a downstream enclosure 42b called" exhaust air "which is waterproof in the air relative to the upstream chamber 42a.

Ainsi, l'air qui a été déchargé par les rampes de circulation d'air 24, et notamment par la rampe amont 24b, est confiné dans l'enceinte amont de décharge d'air 42a et ne peut être évacué qu'en circulant entre le canal d'alimentation 28 et les rampes de circulation 24. En effet, l'étanchéité réalisée à l'extrémité amont 22a du boítier de pilotage 22 empêche l'air de contourner le boítier de pilotage 22 pour être évacué. De même, l'air qui a été déchargé par la rampe aval 24c est contraint, par l'étanchéité réalisée à l'extrémité aval 22b du boítier de pilotage 22, de circuler entre le canal d'alimentation 28 et les rampes de circulation 24 pour être évacué.Thus, the air that has been discharged by the air circulation ramps 24, and in particular by the upstream ramp 24b, is confined in the enclosure upstream discharge 42a and can be evacuated by circulating between the supply channel 28 and the traffic ramps 24. Indeed, the sealing performed at the upstream end 22a of the control box 22 prevents air from bypassing the pilot housing 22 to be evacuated. Of same, the air that has been discharged by the downstream ramp 24c is constrained by the sealing performed at the downstream end 22b of the control box 22, circulate between the supply channel 28 and the traffic ramps 24 to be evacuated.

Comme illustré par la figure 1, l'air qui a été déchargé sur les ailettes 18 du carter interne 14 et qui est évacué entre le canal d'alimentation 28 et les rampes de circulation 24 est alors confiné dans l'enceinte aval d'évacuation d'air 42b.As illustrated in Figure 1, the air that has been discharged on fins 18 of the inner casing 14 and which is evacuated between the channel supply 28 and the traffic ramps 24 is then confined in the downstream exhaust air chamber 42b.

De préférence, le carter interne 14 présente, à une extrémité axiale aval, une ouverture 44 s'ouvrant dans l'enceinte aval d'évacuation d'air 42b afin d'évacuer l'air qui y est confiné. Cette ouverture 44, qui peut être munie d'une douille 46, évacue ainsi l'air ayant été déchargé sur les ailettes 18 du carter interne afin d'alimenter par exemple le premier étage d'un distributeur basse-pression (non représenté) de la turbomachine. Preferably, the inner casing 14 has, at one end axial downstream, an opening 44 opening in the downstream exhaust enclosure 42b air to evacuate the air confined therein. This opening 44, which can provided with a sleeve 46, thus evacuate the air having been discharged on the fins 18 of the inner casing to feed for example the first floor a low-pressure distributor (not shown) of the turbomachine.

On décrira maintenant deux configurations possibles du dispositif de contrôle de jeu selon l'invention en se référant plus particulièrement aux figures 3A et 3B.We will now describe two possible configurations of game control device according to the invention by referring more particularly in FIGS. 3A and 3B.

Dans ces deux configurations, le boítier de pilotage se compose de deux secteurs angulaires distincts de boítier 48 (ou demi-boítiers de 180° chacun) dont un seul est représenté sur les figures 3A et 3B. Ces deux secteurs de boítier 48 sont fixés entre eux par des attaches de type vis/écrou qui coopèrent avec des orifices 50 (figure 1) disposés à chaque extrémité angulaire des secteurs de boítier.In these two configurations, the steering box is composed of two distinct angular sectors housing 48 (or half-housings of 180 ° each) of which only one is shown in Figures 3A and 3B. These two casing sectors 48 are fixed together by fasteners of the type screw / nut which cooperate with orifices 50 (FIG. 1) arranged at each angular end of the housing sectors.

On pourrait aussi imaginer que le boítier de pilotage se compose de plus de deux secteurs angulaires distincts de boítier qui, une fois mis bout à bout, forment ensemble un boítier de 360°.We could also imagine that the pilot box is composed of more than two distinct angular sectors of housing which, once put end to end, together form a 360 ° housing.

Les secteurs de boítier 48 représentés sur les figures 3A et 3B sont fermés à chacune de leurs extrémités angulaires, de sorte que l'air ne circule pas d'un secteur de boítier à l'autre. Toutefois, il est également possible de réaliser une connexion entre les secteurs de boítier afin de permettre un passage de l'air d'un secteur de boítier vers un autre.Housing sectors 48 shown in FIGS. 3A and 3B are closed at each of their angular ends, so that the air does not not move from one housing sector to another. However, it is also possible to make a connection between the housing sectors in order to allow a passage of air from one housing sector to another.

Chaque secteur de boítier 48 est par ailleurs alimenté par une unique conduite d'air 30 débouchant dans le canal d'alimentation 28 à égale distance des deux extrémités angulaires du secteur de boítier. La conduite d'air pourrait aussi déboucher à l'une des extrémités angulaires du secteur de boítier. Plusieurs conduites d'air sont également envisageables.Each housing sector 48 is also powered by a single air duct 30 opening into the feed channel 28 to equidistant from the two angular ends of the housing sector. The air duct could also lead to one of the angular ends housing sector. Several air ducts are also conceivable.

Sur la figure 3A, il est prévu, pour chaque secteur de boítier 48, quatre entretoises creuses de distribution 32 reliant le canal d'alimentation 28 à la rampe de circulation 24 représentée. Ces entretoises creuses de distribution 32 sont disposées sur la demi-circonférence du secteur de boítier 48 de sorte que la distance angulaire entre deux entretoises successives ne dépasse pas de préférence 45° environ.In FIG. 3A, provision is made for each case sector 48, four hollow distribution spacers 32 connecting the feed channel 28 at the traffic ramp 24 shown. These hollow spacers of distribution 32 are arranged on the half-circumference of the sector of casing 48 so that the angular distance between two spacers successive does not exceed preferably 45 °.

Sur la figure 3B, cinq entretoises creuses de distribution 32 relient le canal d'alimentation 28 à la rampe de circulation 24 représentée. Plus particulièrement, une entretoise de distribution est disposée à chaque extrémité angulaire du secteur de boítier et la distance angulaire entre deux entretoises successives ne dépasse pas non plus de préférence 45° environ. In FIG. 3B, five hollow distribution spacers 32 connect the supply channel 28 to the circulation ramp 24 shown. More particularly, a distribution spacer is arranged at each angular end of the housing sector and the angular distance between two successive spacers preferably do not exceed preferably 45 ° about.

On remarquera que, dans ces deux configurations, l'air qui pénètre dans chaque rampe de circulation 24 par chaque entretoise creuse de distribution 32 s'écoule dans deux directions tangentielles opposées.It will be noted that, in these two configurations, the air which enters each traffic ramp 24 through each spacer hollow distribution 32 flows in two tangential directions opposed.

On notera également que le nombre et la disposition des entretoises creuses de distribution peut varier pour chaque rampe de circulation d'air d'un même secteur de boítier.It should also be noted that the number and layout of Hollow distribution spacers may vary for each boom air circulation of the same housing sector.

Ainsi, pour un même secteur de boítier, les entretoises creuses de distribution reliant le canal d'alimentation à l'une des rampes de circulation d'air peuvent être décalées angulairement par rapport aux entretoises creuses de distribution reliant le canal d'alimentation avec au moins l'une des autres rampes de circulation d'air.Thus, for the same housing sector, the hollow spacers distribution system connecting the feed channel to one of the air circulation can be angularly offset from hollow distribution spacers connecting the feed channel with least one of the other air circulation ramps.

Le décalage angulaire des entretoises creuses de distribution entre les rampes de circulation d'air permet d'obtenir une meilleure homogénéité de température dans le boítier de pilotage et d'éviter ainsi toute distorsion de l'ensemble à anneau fixe.The angular offset of the hollow distribution spacers between the air circulation ramps allows for better homogeneity of temperature in the control box and to avoid any distortion of the fixed ring assembly.

Un tel décalage angulaire peut par exemple être obtenu dans le cas d'un même secteur de boítier comportant trois rampes de circulation d'air comme illustré sur les figures 1 et 2. Dans ce cas, la rampe centrale 24a (ou réciproquement les rampes amont 24b et aval 24c) peut avoir la configuration de la figure 3A, tandis que les rampes amont 24b et aval 24c (ou réciproquement la rampe centrale 24a) peuvent avoir la configuration de la figure 3B.Such an angular offset can for example be obtained in the case of the same housing sector with three traffic ramps as in Figures 1 and 2. In this case, the central ramp 24a (or conversely the upstream ramps 24b and downstream 24c) can have the configuration of Figure 3A, while the upstream ramps 24b and downstream 24c (or conversely the central ramp 24a) can have the configuration of Figure 3B.

Une telle disposition s'apparente, pour les trois rampes 24a, 24b et 24c, à une disposition en quinconce des entretoises de distribution 32 avec une symétrie de disposition entre les rampes amont 24b et aval 24c. Cette symétrie de disposition permet d'obtenir une dilatation ou une contraction thermique sensiblement identique entre les deux ailettes 18 du carter interne 14 de façon à améliorer l'homogénéité de température de l'ensemble à anneau fixe.Such a provision is similar for the three ramps 24a, 24b and 24c, in a quincunx arrangement of distribution spacers 32 with a symmetry of arrangement between the upstream ramp 24b and the downstream ramp 24c. This symmetry of arrangement makes it possible to obtain a dilation or a substantially identical thermal contraction between the two fins 18 of the internal casing 14 so as to improve the temperature homogeneity of the fixed ring assembly.

Alternativement, les entretoises creuses de distribution reliant le canal d'alimentation d'un même secteur de boítier à l'une des rampes de circulation d'air peuvent être alignées angulairement par rapport aux entretoises creuses de distribution reliant le canal d'alimentation avec les autres rampes de circulation d'air. Alternatively, the hollow distribution spacers connecting the supply channel of the same sector of housing to one of the ramps of air circulation can be aligned angularly with respect to hollow distribution spacers connecting the feed channel with the other air circulation ramps.

Toujours dans le cas d'un même secteur de boítier comportant trois rampes de circulation d'air 24a, 24b et 24c comme illustré sur les figures 1 et 2, un alignement angulaire des entretoises creuses de distribution peut être obtenu en donnant aux trois rampes de circulation d'air la même configuration. Par exemple, cette configuration des trois rampes de circulation d'air peut être identique à celle de la figure 3A ou de la figure 3B.Still in the case of the same housing sector comprising three air circulation ramps 24a, 24b and 24c as illustrated on the FIGS. 1 and 2, an angular alignment of the hollow spacers of FIGS. distribution can be achieved by giving to the three traffic ramps of air the same configuration. For example, this configuration of the three air circulation ramps may be identical to that of Figure 3A or Figure 3B.

Il est également possible d'envisager que chaque rampe de circulation d'air d'un même secteur de boítier ne soit alimentée en air que par une seule entretoise creuse de distribution reliée au canal d'alimentation. De plus, si cette entretoise de distribution est disposée à une extrémité angulaire du secteur de boítier, la circulation de l'air dans la rampe ne s'effectue que selon une seule et même direction tangentielle.It is also possible to envisage that each air circulation of the same sector of housing is supplied with air than by a single hollow distribution spacer connected to the canal Power. In addition, if this distribution spacer is an angular end of the housing sector, the circulation of air in the ramp is carried out only in one and the same tangential direction.

Le diamètre de perçage des entretoises creuses de distribution peut varier d'une entretoise à l'autre pour une même rampe de circulation d'air. La variation du diamètre des entretoises de distribution offre ainsi la possibilité de réguler le débit d'air alimentant la rampe suivant l'emplacement angulaire de l'entretoise de façon à améliorer l'homogénéité de température de l'ensemble à anneau fixe.The drilling diameter of the hollow distribution spacers may vary from one spacer to another for the same traffic ramp air. The variation of the diameter of the distribution spacers thus offers the possibility of regulating the air flow supplying the next ramp the angular location of the spacer so as to improve the temperature homogeneity of the fixed ring assembly.

De manière générale, en fonction des besoins, le nombre, le diamètre de perçage et la disposition des entretoises de distribution peuvent varier pour une même rampe de circulation et pour un même secteur de boítier. Ces différents paramètres sont choisis de façon à limiter au maximum la distorsion de l'ensemble à anneau fixe.In general, depending on the needs, the number, the Drilling diameter and layout of the distribution spacers may vary for the same traffic ramp and for the same housing sector. These different parameters are chosen so as to minimize distortion of the fixed ring assembly.

Claims (9)

Dispositif de contrôle de jeu entre le sommet (4a) d'aubes rotatives (4) et un ensemble à anneau fixe d'une turbine à gaz (2), ledit dispositif comprenant un boítier circulaire de pilotage (22) entourant ledit ensemble à anneau fixe,
   caractérisé en ce que ledit boítier de pilotage (22) comporte : au moins deux rampes annulaires de circulation d'air (24a, 24b, 24c) espacées l'une de l'autre dans le sens axial et comportant chacune une pluralité de perforations (26) pour modifier la température de l'ensemble à anneau fixe par décharge d'air ; un canal annulaire d'alimentation en air (28) espacé radialement desdites rampes de circulation d'air (24a, 24b, 24c) ; au moins une conduite d'air (30) pour alimenter en air ledit canal d'alimentation (28) ; et une pluralité d'entretoises creuses de distribution (32) reliant ledit canal d'alimentation en air (28) auxdites rampes de circulation d'air (24a, 24b, 24c) afin d'alimenter en air ces dernières tout en permettant à l'air ayant été déchargé sur l'ensemble à anneau fixe de circuler entre ledit canal d'alimentation (28) et lesdites rampes de circulation (24a, 24b, 24c) pour y être évacué. Device for controlling clearance between the vertex (4a) of rotary vanes (4) and a stationary ring assembly of a gas turbine (2), said device comprising a circular piloting housing (22) surrounding said ring assembly fixed,
characterized in that said pilot housing (22) comprises: at least two annular air circulation ramps (24a, 24b, 24c) axially spaced from each other and each having a plurality of perforations (26) for varying the temperature of the fixed ring assembly by air discharge; an annular air supply channel (28) radially spaced from said air circulation ramps (24a, 24b, 24c); at least one air duct (30) for supplying air to said supply duct (28); and a plurality of hollow distribution spacers (32) connecting said air supply channel (28) to said air circulation ramps (24a, 24b, 24c) for supplying air thereto while permitting air having been discharged on the stationary ring assembly from circulating between said supply channel (28) and said circulation ramps (24a, 24b, 24c) for evacuation therefrom. Dispositif selon la revendication 1, caractérisé en ce que l'ensemble à anneau fixe comporte un carter interne (14) qui est entouré par un carter externe (34) de la turbine à gaz (2) de façon à définir une chambre annulaire (38) dans laquelle est monté ledit boítier de pilotage (22).Device according to claim 1, characterized in that the fixed ring assembly comprises an inner casing (14) which is surrounded by an outer casing (34) of the gas turbine (2) so as to define an annular chamber (38). ) in which is mounted said pilot housing (22). Dispositif selon la revendication 2, caractérisé en ce que ledit boítier de pilotage (28) est en appui étanche, à une extrémité axiale amont (22a), contre le carter externe (34), et, à une extrémité axiale aval (22b), contre le carter interne (14) afin de définir, à l'intérieur de ladite chambre annulaire (38), une enceinte amont de décharge d'air (42a) et une enceinte aval d'évacuation d'air (42b) étanche par rapport à ladite enceinte amont (42a). Device according to claim 2, characterized in that said pilot housing (28) is in sealing engagement, at an upstream axial end (22a), against the outer casing (34), and at a downstream axial end (22b), against the inner casing (14) to define, inside said annular chamber (38), an upstream air discharge chamber (42a) and a downstream air exhaust chamber (42b) sealed against to said upstream enclosure (42a). Dispositif selon la revendication 3, caractérisé en ce que ledit carter interne (14) présente, à une extrémité axiale aval, une ouverture d'air (44) s'ouvrant dans l'enceinte aval d'évacuation d'air (42b) afin d'évacuer l'air ayant été déchargé sur l'ensemble à anneau fixe.Device according to claim 3, characterized in that said inner casing (14) has, at a downstream axial end, an air opening (44) opening in the downstream exhaust air enclosure (42b) so to evacuate the air having been discharged on the fixed ring assembly. Dispositif selon l'une quelconque des revendications 2 à 4, caractérisé en ce que le carter interne (14) comprend des ailettes annulaires (18) et en ce que les rampes de circulation d'air (24a, 24b, 24c) épousent sensiblement la forme desdites ailettes (18).Device according to any one of claims 2 to 4, characterized in that the inner casing (14) comprises annular fins (18) and in that the air circulation ramps (24a, 24b, 24c) substantially match the form of said fins (18). Dispositif selon l'une quelconque des revendications 1 à 5, caractérisé en ce que ledit boítier de pilotage (22) se compose d'au moins deux secteurs angulaires distincts de boítier (48).Device according to any one of claims 1 to 5, characterized in that said control box (22) consists of at least two separate angular sectors housing (48). Dispositif selon l'une quelconque des revendications 1 à 6, caractérisé en ce que les entretoises creuses de distribution (32) reliant le canal d'alimentation (28) à l'une des rampes de circulation d'air (24a, 24b, 24c) sont décalées angulairement par rapport aux entretoises creuses de distribution (32) reliant ledit canal d'alimentation (28) avec au moins l'une des autres rampes de circulation d'air (24a, 24b, 24c).Device according to any one of claims 1 to 6, characterized in that the hollow distribution spacers (32) connecting the feed channel (28) to one of the air circulation ramps (24a, 24b, 24c ) are angularly offset relative to the hollow distribution spacers (32) connecting said feed channel (28) with at least one of the other air circulation ramps (24a, 24b, 24c). Dispositif selon l'une quelconque des revendications 1 à 6, caractérisé en ce que les entretoises creuses de distribution (32) reliant le canal d'alimentation (28) à l'une des rampes de circulation d'air (24a, 24b, 24c) sont alignées angulairement par rapport aux entretoises creuses de distribution (32) reliant ledit canal d'alimentation (28) avec les autres rampes de circulation d'air (24a, 24b, 24c).Device according to any one of claims 1 to 6, characterized in that the hollow distribution spacers (32) connecting the feed channel (28) to one of the air circulation ramps (24a, 24b, 24c ) are aligned angularly with respect to the hollow distribution spacers (32) connecting said feed channel (28) with the other air circulation ramps (24a, 24b, 24c). Dispositif selon l'une quelconque des revendications 1 à 8, caractérisé en ce que l'espacement angulaire entre deux entretoises creuses de distribution successives (32) ne dépasse pas 45° environ.Device according to any one of claims 1 to 8, characterized in that the angular spacing between two successive hollow spacers distribution (32) does not exceed 45 °.
EP04291818A 2003-08-06 2004-07-16 Device to control clearances in a gas turbine Expired - Lifetime EP1505261B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0309686A FR2858652B1 (en) 2003-08-06 2003-08-06 DEVICE FOR CONTROLLING PLAY IN A GAS TURBINE
FR0309686 2003-08-06

Publications (2)

Publication Number Publication Date
EP1505261A1 true EP1505261A1 (en) 2005-02-09
EP1505261B1 EP1505261B1 (en) 2008-02-20

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EP04291818A Expired - Lifetime EP1505261B1 (en) 2003-08-06 2004-07-16 Device to control clearances in a gas turbine

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US (1) US7114914B2 (en)
EP (1) EP1505261B1 (en)
JP (1) JP4185476B2 (en)
CA (1) CA2475081C (en)
DE (1) DE602004011859T2 (en)
ES (1) ES2300722T3 (en)
FR (1) FR2858652B1 (en)
RU (1) RU2290515C2 (en)
UA (1) UA83188C2 (en)

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WO2009144191A1 (en) * 2008-05-28 2009-12-03 Snecma High pressure turbine for turbine engine with improved mounting of the housing for controlling the radial clearance of mobile blades
EP2243931A3 (en) * 2009-04-16 2013-09-18 Rolls-Royce plc Turbine casing cooling
GB2518946A (en) * 2013-08-07 2015-04-08 Snecma Turbine casing made of two materials
EP2987966A1 (en) * 2014-08-21 2016-02-24 Siemens Aktiengesellschaft Gas turbine with cooling ring channel divided into ring sectors
EP2987965A1 (en) * 2014-08-21 2016-02-24 Siemens Aktiengesellschaft Gas turbine with ring channel and a distributor pipe within same
EP3091195A1 (en) * 2015-05-08 2016-11-09 General Electric Company System and method for waste heat powered active clearance control
EP2372105A3 (en) * 2010-03-17 2016-11-16 Rolls-Royce plc Rotor blade tip clearance control
WO2018229385A1 (en) 2017-06-15 2018-12-20 Safran Aircraft Engines Device for cooling an annular outer turbine casing
FR3114345A1 (en) * 2020-09-23 2022-03-25 Safran Aircraft Engines Game control device for a turbomachine turbine

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FR2965583B1 (en) * 2010-10-04 2012-09-14 Snecma DEVICE FOR CONTROLLING PLAY IN A TURBOMACHINE TURBINE
FR2972483B1 (en) * 2011-03-07 2013-04-19 Snecma TURBINE HOUSING COMPRISING MEANS FOR FIXING RING SECTIONS
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Publication number Priority date Publication date Assignee Title
WO2009144191A1 (en) * 2008-05-28 2009-12-03 Snecma High pressure turbine for turbine engine with improved mounting of the housing for controlling the radial clearance of mobile blades
FR2931872A1 (en) * 2008-05-28 2009-12-04 Snecma HIGH PRESSURE TURBINE OF A TURBOMACHINE WITH IMPROVED MOUNTING OF THE PILOTAGE HOUSING OF THE MOBILE RADIAL GAMES.
US8662828B2 (en) 2008-05-28 2014-03-04 Snecma High pressure turbine of a turbomachine with improved assembly of the mobile blade radial clearance control box
EP2243931A3 (en) * 2009-04-16 2013-09-18 Rolls-Royce plc Turbine casing cooling
US8668438B2 (en) 2009-04-16 2014-03-11 Rolls-Royce Plc Turbine casing cooling
EP2372105A3 (en) * 2010-03-17 2016-11-16 Rolls-Royce plc Rotor blade tip clearance control
GB2518946A (en) * 2013-08-07 2015-04-08 Snecma Turbine casing made of two materials
GB2518946B (en) * 2013-08-07 2020-09-09 Snecma Turbine casing made of two materials
WO2016026752A1 (en) * 2014-08-21 2016-02-25 Siemens Aktiengesellschaft Gas turbine having a ring channel divided into ring sectors
EP2987965A1 (en) * 2014-08-21 2016-02-24 Siemens Aktiengesellschaft Gas turbine with ring channel and a distributor pipe within same
US10294818B2 (en) 2014-08-21 2019-05-21 Siemens Aktiengesellschaft Gas turbine having an annular passage subdivided into annulus sectors
EP2987966A1 (en) * 2014-08-21 2016-02-24 Siemens Aktiengesellschaft Gas turbine with cooling ring channel divided into ring sectors
EP3091195A1 (en) * 2015-05-08 2016-11-09 General Electric Company System and method for waste heat powered active clearance control
WO2018229385A1 (en) 2017-06-15 2018-12-20 Safran Aircraft Engines Device for cooling an annular outer turbine casing
FR3067751A1 (en) * 2017-06-15 2018-12-21 Safran Aircraft Engines COOLING DEVICE FOR AN EXTERNAL TURBINE ANNULAR CASTER
US11542833B2 (en) 2017-06-15 2023-01-03 Safran Aircraft Engines Device for cooling an annular outer turbine casing
FR3114345A1 (en) * 2020-09-23 2022-03-25 Safran Aircraft Engines Game control device for a turbomachine turbine

Also Published As

Publication number Publication date
CA2475081A1 (en) 2005-02-06
DE602004011859D1 (en) 2008-04-03
US7114914B2 (en) 2006-10-03
JP2005054777A (en) 2005-03-03
UA83188C2 (en) 2008-06-25
CA2475081C (en) 2011-09-13
JP4185476B2 (en) 2008-11-26
FR2858652A1 (en) 2005-02-11
ES2300722T3 (en) 2008-06-16
FR2858652B1 (en) 2006-02-10
EP1505261B1 (en) 2008-02-20
US20050042080A1 (en) 2005-02-24
RU2004122668A (en) 2006-01-27
DE602004011859T2 (en) 2009-02-12
RU2290515C2 (en) 2006-12-27

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