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EP2307738B1 - Verdichterabdeckung für einen turbomotor mit axialanschlag - Google Patents

Verdichterabdeckung für einen turbomotor mit axialanschlag Download PDF

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Publication number
EP2307738B1
EP2307738B1 EP09766040.1A EP09766040A EP2307738B1 EP 2307738 B1 EP2307738 B1 EP 2307738B1 EP 09766040 A EP09766040 A EP 09766040A EP 2307738 B1 EP2307738 B1 EP 2307738B1
Authority
EP
European Patent Office
Prior art keywords
cover
casing
downstream
downstream end
edge
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.)
Active
Application number
EP09766040.1A
Other languages
English (en)
French (fr)
Other versions
EP2307738A2 (de
Inventor
Philippe Joubert
Patrice Laborde
Yann Mouze
Philippe Perot
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines 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 Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to PL09766040T priority Critical patent/PL2307738T3/pl
Publication of EP2307738A2 publication Critical patent/EP2307738A2/de
Application granted granted Critical
Publication of EP2307738B1 publication Critical patent/EP2307738B1/de
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Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel

Definitions

  • the present invention relates to the field of gas turbines, especially those found in turbomachines, for example but not only helicopter turboshaft engines or turbojet engines for aircraft.
  • the present invention more specifically relates to the compression stage of such gas turbines which constitute the main engine of a flying machine.
  • the compressor is disposed between a fresh air intake and a combustion chamber, the role of the compressor being to compress the fresh air entering the gas turbine and to bring this compressed air into the combustion chamber to be mixed with fuel.
  • the impeller comprises a plurality of blades extending generally radially from a wheel hub, which is fixed to a rotary shaft of the gas turbine.
  • the flow of gas firstly enters the compressor casing through an upstream inlet and then flows into the gas stream delimited between its outer surface defined by the cover and its inner surface defined by a surface.
  • the hub of the wheel while being compressed and rotated about the axis of the wheel, before being discharged through a downstream outlet of the compressor, it being specified that the terms "upstream” and "downstream” are taken with reference to the meaning of gas circulation in the gas stream of the compressor.
  • the stream of compressed gas exiting the impeller then enters a diffuser before entering the combustion chamber.
  • the cover defines the outer surface of the vein, the inner surface thereof being formed by a surface of the wheel hub from which the blades extend.
  • This configuration makes it possible to avoid a hyperstatic fixing of the cover which would be potentially harmful to the control of the games between the impeller and the lid.
  • An object of the invention is therefore to provide a cover for avoiding contact with the impeller blades during degraded operation of the compressor.
  • WO 00/34628 discloses a turbine containment system for containing the explosion of a turbine or one or more of its blades which would detach from the hub.
  • the invention achieves its goal by the fact that the cover further comprises a stop intended to limit the axial displacement of the downstream end of the cover with respect to the downstream edge of the casing during operation of the compressor.
  • the stop is disposed at the downstream end of the cover.
  • the axial displacement of the downstream end of the cover is limited.
  • the downstream end of the cover and the downstream edge of the casing are arranged in such a way that when the downstream end of the cover abuts against the downstream edge of the casing, there is still a clearance between the impeller blades and the cover, As a result, contact is advantageously avoided.
  • the cover is mounted while leaving a calibrated axial clearance between the downstream end of the cover and the downstream edge of the housing.
  • the abutment preferably annular, forms a radial extension extending from the downstream end of the cover. It therefore extends orthogonally with respect to an axis of the wheel when the lid is mounted.
  • the abutment consists of a plurality of radial tabs.
  • the stop thus covers radially a circumferential portion of the edge of the housing.
  • downstream end of the cover further comprises an axial extension forming an annular rib capable of almost touching the downstream edge of the housing when the cover is mounted.
  • a small calibrated radial clearance is thus provided between the downstream end of the cover and an inner end of the downstream edge of the casing so as to limit the accidents of shape in the air stream, which are detrimental to the efficiency of the compressor.
  • the present invention finally relates to a gas turbine, in particular a helicopter, comprising one or more compressors in accordance with the present invention.
  • the Figure 1A is an overall sectional view of a helicopter turbine engine 10 known elsewhere.
  • the turbine engine 10 consists of a gas turbine which comprises a compressor 12 , also called compression stage, an air inlet 14 for the admission of fresh air into the compressor 12 and a chamber combustion system 16 in which takes place the combustion of a mixture of fuel and compressed air by the compressor 12 .
  • the turbine engine 10 further comprises a turbine 18 fixed to a rotor wheel 20 of the compressor 12 via a shaft 22 , which turbine 18 , set in motion by the flow of flue gas leaving the combustion chamber 16 , rotates the wheel 20 .
  • the turbine engine 10 further comprises a free turbine 24 which is rotated by the flow of gas leaving the turbine 18 , said free turbine allowing in turn to rotate the rotors of the helicopter (not shown here). ).
  • the impeller with blades 20 of the centrifugal impeller type, is well known elsewhere. It comprises a hub 26 from which radially extend a plurality of blades 28 which may have curved shapes, whose radial ends are contained in a geometrical envelope which has the shape of a hyperboloid of revolution.
  • the wheel 20 also has an axis of rotation A and the term "axial" will be considered with reference to this axis.
  • the compressor 12 comprises a casing 30 which preferably forms a constituent part of the casing of the turbine engine 10 .
  • the casing 30 is the structure that holds the elements of the compressor; as such, the wheel 20 is rotatably mounted in the casing 30 .
  • This casing 30 has an upstream edge 32 and a downstream edge 34 , it being specified that the terms "upstream” and “downstream” are considered as references.
  • the flow direction of the gas flow inside the compressor 20 is illustrated by the arrows F in the different figures.
  • vein 38 is delimited between a surface 26a constituted by the hub 26 , from which the blades 28 extend and a cover 40 defining an outer surface of the vein 38 .
  • the cover 40 covers the blades 28 of the impeller 20 so that it extends between the upstream edge 32 of the casing and the downstream edge 34 of the casing 30 while substantially matching the shape of the geometric envelope mentioned above. above. In other words, there is a small clearance between each of the blades 28 and the lid 40 .
  • the cover 40 has an upstream end 40a and a downstream end 40b , the upstream end 40a being fixed to the upstream edge 32 of the casing via a fastener 42 , while the downstream end 40b is free.
  • downstream end 40b of the cover 40 is not attached to the downstream edge 34 of the housing 30 .
  • downstream edge 34 of the casing 30 is in continuity with the downstream end 40b of the cover 40 .
  • FIG. 2 which illustrates a detail of a turbine engine according to the invention, will now be described a cover 100 of a centrifugal compressor 200 according to the present invention, the other components of the turbine engine 10 being identical to those described above and bearing the same numerical references.
  • downstream end 100b of the cover 100 further comprises a stop 102 forming a radial extension which extends orthogonally with respect to the axis A of the wheel 20 .
  • This stop 102 which is preferably annular, is intended to limit the axial displacement of the downstream end 100b of the cover 100 .
  • the abutment 102 has a contact face 103 adapted to bear against the downstream edge 34 of the casing 30 if the downstream end 100b of the cover 100 bends towards the blades 28 of the impeller, so that the cover 100 can be further deformed, whereby it is advantageously avoided contact between the cover 100 and the blades 28 of the wheel 20 .
  • an axial clearance Ja is provided between the contact face 103 and the downstream edge 34 of the casing 30 .
  • the downstream end 100b of the cover 100 also comprises an axial bulge 104 extending in a direction opposite to that of the contact face 103 .
  • This axial bulge has an annular shape and its role is to reinforce the mechanical strength of the abutment 102 on which mechanical stresses are exerted when it comes into contact with the downstream edge 34 of the casing 30 .
  • downstream end 100b further comprises an axial extension 106 in the form of an annular rib, which is intended to come almost touching the downstream edge 34 of the casing 30 . More specifically, a small radial clearance Jr is provided between this annular rib 106 and the downstream edge 34 so as to prevent the flow of gas being disturbed in the gap between the downstream end 100b of the cover 100 and the downstream edge. 34 of the housing 30 .
  • the annular rib 106 is arranged so that it has a radial height greater than that of the trailing edge of the blades.
  • the inner surface of the cover 100 , wheel side is covered with an abradable material, known moreover, in order to avoid damage to the cover and the blades during possible contacts between them.

Landscapes

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

Claims (6)

  1. Kreiselverdichter eines Turbomotors, umfassend:
    - einen Deckel, der ein vorgelagertes Ende (40a) und ein nachgelagertes Ende (100b) aufweist,
    - ein Gehäuse (30), das einen vorgelagerten Rand (32) und einen nachgelagerten Rand (34) aufweist,
    - ein Schaufellaufrad (20), das drehbar in dem Gehäuse befestigt ist, wobei der Deckel dazu bestimmt ist, die Schaufeln des Laufrads (28) derart abzudecken, um eine äußere Oberfläche eines Gasstroms (38) zu definieren, der sich zwischen dem vorgelagerten und dem nachgelagerten Rand des Gehäuses erstreckt, während er gleichzeitig an dem vorgelagerten Rand (32) des Gehäuses durch sein vorgelagertes Ende befestigt ist, während sein nachgelagertes Ende (100b) frei bleibt, dadurch gekennzeichnet, dass der Deckel ferner einen Anschlag (102) aufweist, der dazu bestimmt ist, die axiale Verschiebung seines nachgelagerten Endes (100b) relativ zu dem nachgelagerten Rand (34) des Gehäuses während des Betriebs des Kompressors zu begrenzen.
  2. Kreiselverdichter gemäß Anspruch 1, dadurch gekennzeichnet, dass der Anschlag (102) eine radiale Ausdehnung bildet, die sich von dem nachgelagerten Ende des Deckels erstreckt.
  3. Kreiselverdichter gemäß Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Anschlag (102) ringförmig ist.
  4. Kreiselverdichter gemäß einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der Anschlag (102) aus mehreren radialen Zungen gebildet ist.
  5. Kreiselverdichter gemäß einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass das nachgelagerte Ende (100b) des Deckels ferner eine axiale Ausdehnung (106) aufweist, die eine ringförmige Rippe bildet.
  6. Gasturbine, umfassend einen Kreiselverdichter (200) gemäß einem der Ansprüche 1 bis 5.
EP09766040.1A 2008-05-26 2009-05-20 Verdichterabdeckung für einen turbomotor mit axialanschlag Active EP2307738B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09766040T PL2307738T3 (pl) 2008-05-26 2009-05-20 Pokrywa sprężarki silnika turbinowego z osiowym elementem oporowym

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0853394A FR2931521B1 (fr) 2008-05-26 2008-05-26 Couvercle de compresseur a butee axiale.
PCT/FR2009/050939 WO2009153478A2 (fr) 2008-05-26 2009-05-20 Couvercle de compresseur de turbomoteur a butee axiale

Publications (2)

Publication Number Publication Date
EP2307738A2 EP2307738A2 (de) 2011-04-13
EP2307738B1 true EP2307738B1 (de) 2018-10-10

Family

ID=40394038

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09766040.1A Active EP2307738B1 (de) 2008-05-26 2009-05-20 Verdichterabdeckung für einen turbomotor mit axialanschlag

Country Status (11)

Country Link
US (1) US8721261B2 (de)
EP (1) EP2307738B1 (de)
JP (1) JP5497012B2 (de)
KR (1) KR101629524B1 (de)
CN (1) CN102046984B (de)
CA (1) CA2726905C (de)
ES (1) ES2695902T3 (de)
FR (1) FR2931521B1 (de)
PL (1) PL2307738T3 (de)
RU (1) RU2509232C2 (de)
WO (1) WO2009153478A2 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3008750B1 (fr) 2013-07-18 2015-07-17 Snecma Couvercle de compresseur centrifuge de turbomachine apte a etre fixe par l'aval pres de son bord amont, turbomachine comportant ce couvercle.
CN111120656B (zh) * 2019-12-25 2022-05-27 中国航空工业集团公司西安飞机设计研究所 一种进气道防火密封结构

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2656096A (en) * 1946-01-04 1953-10-20 Rateau Soc Centrifugal pump and compressor
US3613360A (en) * 1969-10-30 1971-10-19 Garrett Corp Combustion chamber construction
US4264271A (en) * 1979-03-15 1981-04-28 Avco Corporation Impeller shroud of a centrifugal compressor
US4687412A (en) * 1985-07-03 1987-08-18 Pratt & Whitney Canada Inc. Impeller shroud
FR2698666B1 (fr) * 1992-11-30 1995-02-17 Europ Propulsion Pompe centrifuge hautement performante à rouet ouvert.
US6224321B1 (en) * 1998-12-07 2001-05-01 Pratt & Whitney Canada Inc. Impeller containment system
JP2003120591A (ja) * 2001-10-12 2003-04-23 Mitsubishi Heavy Ind Ltd ターボ機械
US7908869B2 (en) * 2006-09-18 2011-03-22 Pratt & Whitney Canada Corp. Thermal and external load isolating impeller shroud
RU2352826C2 (ru) * 2007-04-03 2009-04-20 Открытое акционерное общество "Производственное объединение "Северное машиностроительное предприятие" Центробежный гидравлический и воздушный насос-компрессор

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
WO2009153478A3 (fr) 2010-05-27
KR101629524B1 (ko) 2016-06-13
WO2009153478A2 (fr) 2009-12-23
JP2011521172A (ja) 2011-07-21
CA2726905C (fr) 2016-10-25
CA2726905A1 (fr) 2009-12-23
RU2010153329A (ru) 2012-07-10
US8721261B2 (en) 2014-05-13
CN102046984A (zh) 2011-05-04
CN102046984B (zh) 2014-04-30
KR20110016954A (ko) 2011-02-18
ES2695902T3 (es) 2019-01-11
US20110076141A1 (en) 2011-03-31
FR2931521A1 (fr) 2009-11-27
RU2509232C2 (ru) 2014-03-10
FR2931521B1 (fr) 2017-06-23
JP5497012B2 (ja) 2014-05-21
PL2307738T3 (pl) 2019-01-31
EP2307738A2 (de) 2011-04-13

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