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EP1793093B1 - Leitschaufeln einer verbesserten Turbomaschine - Google Patents

Leitschaufeln einer verbesserten Turbomaschine Download PDF

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Publication number
EP1793093B1
EP1793093B1 EP06077140A EP06077140A EP1793093B1 EP 1793093 B1 EP1793093 B1 EP 1793093B1 EP 06077140 A EP06077140 A EP 06077140A EP 06077140 A EP06077140 A EP 06077140A EP 1793093 B1 EP1793093 B1 EP 1793093B1
Authority
EP
European Patent Office
Prior art keywords
flange
distributor
sector
nozzle segment
turbomachine
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
EP06077140A
Other languages
English (en)
French (fr)
Other versions
EP1793093A2 (de
EP1793093A3 (de
Inventor
Alexandre Nicolas Dervaux
Patrick Joseph Marie Girard
Gael Loro
Guillaume Jean-Claude Robert Renon
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 SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1793093A2 publication Critical patent/EP1793093A2/de
Publication of EP1793093A3 publication Critical patent/EP1793093A3/de
Application granted granted Critical
Publication of EP1793093B1 publication Critical patent/EP1793093B1/de
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Anticipated expiration legal-status Critical

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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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Definitions

  • the present invention relates to the field of turbomachines, in particular an improved turbomachine turbine distributor.
  • An aviation turbine engine typically comprises a compressor, a combustion chamber and a turbine.
  • the role of the turbine is to ensure the rotational drive of the compressor by taking a portion of the pressure energy of the hot gases leaving the combustion chamber and converting it into mechanical energy.
  • the turbine located downstream of the combustion chamber, is the organ of the turbomachine that works in the most severe conditions. It is particularly subjected to significant thermal and mechanical stresses generated by the hot gases at the chamber outlet.
  • An axial turbine conventionally comprises at least one distributor, consisting of a vanes grid fixed relative to the casing of the turbomachine, and at least one movable wheel, comprising a set of vanes capable of being rotated.
  • the nozzle vanes are generally fixed radially with respect to the axis of rotation of the turbomachine on two concentric annular shrouds, called inner shroud and outer shroud, one end of the blades being integral with the inner shroud and another end of the blades being integral with the outer shell.
  • the dispenser may be sectored, each sector being provided with a plurality of blades.
  • the distributor sectors are fixed on a fixed annular casing.
  • the assembly of a plurality of identical sectors connected end to end ring on a fixed annular casing makes it possible to reconstitute the distributor.
  • the valve sectors comprise an axis of revolution coaxial with the axis of rotation of the turbomachine.
  • the inner ferrule and outer ferrule portions are respectively called inner platform and outer deck.
  • the space defined between the inner platform and the platform Outer is a stream of air in which flows air from the combustion chamber.
  • the platforms have portions exposed directly to the air stream and other unexposed portions.
  • the hot gas-exposed portions such as the surfaces delimiting the airstream, will expand more rapidly than the unexposed portions, such as flanges described in detail below.
  • the platforms are more massive parts than the blades. Consequently, the platforms have a greater thermal inertia than the blades, which implies two consequences: under the effect of an increase in temperature, the blades will, on the one hand, expand more rapidly than the blades. platforms, and on the other hand, the platforms will impose their deformation at the blades. This phenomenon is also called bimetallic effect.
  • the distributor undergoes heating and cooling deforming the inner and outer platforms. Under the effect of these deformations, the vanes of the distributor are subjected to a succession of traction and compression which induce the appearance of cracks affecting the life of the blades.
  • the present invention aims to solve the aforementioned problems by providing a distributor having more flexibility.
  • the invention relates to a turbomachine turbine nozzle sector comprising an inner platform and an outer platform, at least one blade fixed between said platforms, at least one of said platforms comprising at least one flange, having a first end fixed to the platform and a second free end, characterized in that said flange comprises at least one free softening recess consisting of a reduction in the thickness of said flange.
  • the flange may be either a radial flange or a semi-cylindrical flange.
  • such a recess can easily relate to existing distributor sectors by different known machining techniques. It is therefore possible to relax the distributor sectors already in circulation.
  • the present application therefore also relates to a process for softening distributor sectors characterized in that it consists in machining at least one recess in at least one flange of a distributor sector, the recess being constituted by a reduction of the thickness of said flange.
  • the figure 1 illustrates, in a sectional view, a distributor sector 1 installed on a turbomachine. At least one guide vane 2 is fixed on this distributor sector 1 radially with respect to the axis of revolution X of said distributor sector 1, between an inner platform 3 and an outer platform 4. On a radial axis Y orthogonally cutting the axis of revolution X, an inner platform 3 is located at a smaller distance from this axis X than an outer platform 4.
  • This blade 2 is directly exposed to hot gases from the combustion chamber.
  • the platforms 3 and 4 comprise parts exposed directly to the air from the combustion chamber, in particular the surfaces 3a and 4a delimiting the air stream 12, and other parts not exposed to this air.
  • FIGS. 2, 3 and 4 represent different operating phases of a distributor sector 1.
  • the figure 2 schematically illustrates a valve sector 1 at rest, that is to say when the turbine engine is stopped. No thermal or mechanical stress is exerted on the distributor sector 1.
  • the figure 3 schematically illustrates a distributor sector 1 during a heating phase.
  • the warm-up phase the most important during a flight, is noted at the time of takeoff of the aircraft.
  • the inner 3 and outer 4 platforms deform and their surfaces 3a and 4a exposed to the air stream 12 tend to become convex with respect to this vein 12.
  • the blades 2a located in the center of the dispenser sector 1 undergo compression and that the blades 2b located at the periphery are subjected to traction.
  • the figure 4 schematically illustrates a distributor sector 1 during a cooling phase.
  • the inner platforms 3 and outer 4 deform and their surfaces 3a and 4a exposed to the air stream 12 tend to become concave facing this vein 12.
  • the blades 2a located in the center of the dispenser sector 1 are pulled and the blades 2b at the periphery undergo compression.
  • the deformations of the inner platforms 3 and outer 4 promote the appearance of cracks on the distributor areas. It is therefore necessary to reduce the deformation of the platforms 3 and 4 to increase the service life of the valve sectors and in particular blades 2, a blade being generally the part with the shortest service life on a distributor sector 1 .
  • the platforms 3 or 4 of a distributor sector 1 may comprise at least one so-called radial flange 5 or at least one semi-cylindrical flange 6, as shown in FIGS. figures 5 and 6 .
  • a flange 5 or 6 has a first end 5a or 6a fixed on the platform 3 or 4 and a second end 5b or 6b free, that is to say a non-fixed end on the platform 3 or 4.
  • a radial flange 5 extends in a plane orthogonally intersecting the axis of revolution X of the distributor sector 1.
  • the radial flange 5 provides axial blocking and sealing in the vicinity of the platforms 3 or 4 of the distributor sector 1.
  • the axial locking is the limitation of any translational movement of the distributor sector 1 relative to the fixed annular casing 13 in a direction parallel to the axis of revolution X.
  • a semi-cylindrical flange 6 extends cylindrically with respect to the axis of revolution X of the distributor sector 1.
  • a flange is semi-cylindrical in that it extends only over a portion of a cylinder corresponding to a distributor sector.
  • the semi-cylindrical flange 6 provides a radial blocking and sealing in the vicinity of the platforms 3 or 4 of the distributor sector 1.
  • the radial blocking is the limitation of any translational movement of the distributor sector 1 in a direction of a radial axis Y orthogonally cutting the axis of revolution X.
  • At least one locking means on these flanges allows the tangential locking relative to the fixed annular casing 13, the latter comprising a complementary means cooperating with the tangential blocking means.
  • Tangential blocking is the limitation of any lateral movement of a manifold sector 1 to the adjacent manifold sectors.
  • This tangential locking means may be a notch 7 intended to cooperate with a complementary lug 8 on the fixed annular casing 13 of the turbomachine, as shown in FIG. figure 5 or, conversely, a lug intended to cooperate with a complementary notch on the fixed annular casing 13 of the turbomachine.
  • At least one flange 5 or 6 of the distributor sector 1 further comprises at least one non-emerging free softening recess.
  • a recess is a removal of material in a room. It can be opening or not.
  • the term "free recess” means a recess which is not intended for cooperate with complementary means, for example to ensure any blocking.
  • the figure 5 represents an outer platform 4 of distributor sector 1 comprising a radial flange 5 and semi-cylindrical flanges 6. These flanges 5 or 6 may also be present on an inner platform 3.
  • the inner platform 3, operating according to the same principles, will not be described in detail.
  • the recess 9 is open and is in the form of a notch 9.
  • These notches 9 soften the platform 4 of the distributor sector 1. They reduce the sensitivity of the blades to the deformations of the sector. Distributor 1 evoked above-high and increase its service life.
  • these free softening notches 9 are located on the second free end 5b or 6b of a flange 5 or 6.
  • Such opening openings are known documents US 3781125 and US 6210108 .
  • the figure 6 represents an outer platform 4 of distributor sector 1, according to the invention, comprising a radial flange 5 and semi-cylindrical flanges 6.
  • the recess 10 is non-opening. These recesses 10 consist of recesses 10 made on the flanges 5 and 6 of the distributor sector 1. Such recesses 10 also make it possible to improve the resistance to the deformations referred to above of the distributor sector 1 and to increase its duration. life. Preferably, these recesses 10 are located on the first end 5a or 6a, fixed on the platform 3 or 4, of a flange 5 or 6.
  • Each distributor sector 1 is fixed on a fixed annular casing 13 of the turbomachine.
  • the assembly of the distributor sectors 1 and the annular housing 13 constitutes a turbine distributor.
  • These recesses 10 can be obtained by different machining techniques known per se.
  • these recesses 10 can be realized on existing distributor sectors. It is therefore possible to relax the distributor sectors already in circulation.
  • the present application also relates to a method of softening a distributor sector 1 comprising at least one blade 2 and at least one flange 5 or 6 characterized in that it consists in machining at least one recess 10 in at least one flange 5 or 6 of the distributor sector 1.

Landscapes

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

Claims (11)

  1. Leitschaufelkranz-Sektor (1) einer Turbine einer Turbomaschine, umfassend eine innere Plattform (3) und eine äußere Plattform (4), wenigstens eine zwischen den Plattformen (3, 4) befestigte Schaufel (2), wobei wenigstens eine der Plattformen (3, 4) wenigstens einen Flansch (5, 6) mit einem an der Plattform (3, 4) befestigten ersten Ende (5a, 6a) und einem freien zweiten Ende (5b, 6b) umfaßt, dadurch gekennzeichnet, daß der Flansch (5, 6) wenigstens eine freie Flexibilisierungsausnehmung (9, 10) aufweist, die durch eine Verringerung der Dicke des Flansches gebildet ist.
  2. Leitschaufelkranz-Sektor (1) nach Anspruch 1, dadurch gekennzeichnet, daß die Ausnehmung (10) eine Vertiefung (10) ist.
  3. Leitschaufelkranz-Sektor (1) nach Anspruch 2, dadurch gekennzeichnet, daß die Vertiefung (10) sich an dem ersten Ende (5a, 6a) des Flansches (5, 6) befindet.
  4. Leitschaufelkranz-Sektor (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Flansch (5) sich in einer radialen Ebene zu einer Rotationsachse (X) des Leitschaufelkranz-Sektors (1) erstreckt.
  5. Leitschaufelkranz-Sektor (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der Flansch (6) halbzylindrisch zu einer Rotationsachse (X) des Leitschaufelkranz-Sektors (1) ist.
  6. Leitschaufelkranz-Sektor (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß er wenigstens ein Tangentialblockierungsmittel (7) umfaßt.
  7. Leitschaufelkranz-Sektor (1) nach Anspruch 6, dadurch gekennzeichnet, daß das Tangentialblockierungsmittel eine Einkerbung (7) ist.
  8. Leitschaufelkranz einer Turbine, der wenigstens einen Laufschaufelkranz-Sektor (1) nach einem der vorhergehenden Ansprüche umfaßt.
  9. Turbine, die wenigstens einen Leitschaufelkranz nach Anspruch 8 umfaßt.
  10. Turbomaschine, die eine Turbine nach Anspruch 9 umfaßt.
  11. Verfahren zum Flexibilisieren eines Leitschaufelkranz-Sektors (1) einer Turbine einer Turbomaschine, der wenigstens eine Schaufel (2) und wenigstens einen Flansch (5, 6) umfaßt, dadurch gekennzeichnet, daß es darin besteht, wenigstens eine Ausnehmung (10) in wenigstens einen Flansch (5, 6) des Leitschaufelkranz-Sektors (1) zu arbeiten, wobei die Ausnehmung durch eine Verringerung der Dicke des Flansches gebildet ist.
EP06077140A 2005-12-05 2006-11-30 Leitschaufeln einer verbesserten Turbomaschine Active EP1793093B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0512295A FR2894282A1 (fr) 2005-12-05 2005-12-05 Distributeur de turbine de turbomachine ameliore

Publications (3)

Publication Number Publication Date
EP1793093A2 EP1793093A2 (de) 2007-06-06
EP1793093A3 EP1793093A3 (de) 2008-12-03
EP1793093B1 true EP1793093B1 (de) 2010-03-17

Family

ID=36950510

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06077140A Active EP1793093B1 (de) 2005-12-05 2006-11-30 Leitschaufeln einer verbesserten Turbomaschine

Country Status (8)

Country Link
US (1) US7780398B2 (de)
EP (1) EP1793093B1 (de)
JP (1) JP4794420B2 (de)
CN (1) CN1978870B (de)
CA (1) CA2569564C (de)
DE (1) DE602006012915D1 (de)
FR (1) FR2894282A1 (de)
RU (1) RU2006142824A (de)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5214128B2 (ja) * 2005-11-22 2013-06-19 シャープ株式会社 発光素子及び発光素子を備えたバックライトユニット
FR2928962B1 (fr) * 2008-03-19 2013-10-18 Snecma Distributeur de turbine a pales creuses.
EP2236761A1 (de) * 2009-04-02 2010-10-06 Siemens Aktiengesellschaft Leitschaufelträger
US8684683B2 (en) * 2010-11-30 2014-04-01 General Electric Company Gas turbine nozzle attachment scheme and removal/installation method
US8684689B2 (en) * 2011-01-14 2014-04-01 Hamilton Sundstrand Corporation Turbomachine shroud
FR2975771B1 (fr) * 2011-05-27 2014-03-14 Snecma Dispositif de mesure d'une piece dans une turbomachine
FR2979272B1 (fr) * 2011-08-24 2013-09-27 Snecma Outillage de prise de piece de turbomachine
US8888442B2 (en) 2012-01-30 2014-11-18 Pratt & Whitney Canada Corp. Stress relieving slots for turbine vane ring
US9291064B2 (en) 2012-01-31 2016-03-22 United Technologies Corporation Anti-icing core inlet stator assembly for a gas turbine engine
EP2706196A1 (de) 2012-09-07 2014-03-12 Siemens Aktiengesellschaft Turbinenleitschaufelanordnung
US20170298751A1 (en) * 2014-10-28 2017-10-19 Siemens Energy, Inc. Modular turbine vane
DE102016215784A1 (de) 2016-08-23 2018-03-01 MTU Aero Engines AG Positionierungselement mit Aussparungen für eine Leitschaufelanordnung
FR3084106B1 (fr) * 2018-07-23 2022-06-24 Safran Aircraft Engines Distributeur basse pression avec pales coulissantes
JP7284737B2 (ja) 2020-08-06 2023-05-31 三菱重工業株式会社 ガスタービン静翼
KR20230035614A (ko) 2020-08-13 2023-03-14 미츠비시 파워 가부시키가이샤 정익 세그먼트, 및 이것을 구비하는 증기 터빈
US11519283B2 (en) * 2021-03-25 2022-12-06 Raytheon Technologies Corporation Attachment region for CMC components

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
US3781125A (en) * 1972-04-07 1973-12-25 Westinghouse Electric Corp Gas turbine nozzle vane structure
US4511306A (en) * 1982-02-02 1985-04-16 Westinghouse Electric Corp. Combustion turbine single airfoil stator vane structure
US5071313A (en) * 1990-01-16 1991-12-10 General Electric Company Rotor blade shroud segment
CA2070511C (en) * 1991-07-22 2001-08-21 Steven Milo Toborg Turbine nozzle support
US6210108B1 (en) * 1999-08-16 2001-04-03 General Electric Company Method for making an article portion subject to tensile stress and stress relieved article
FR2817285B1 (fr) * 2000-11-30 2003-06-13 Snecma Moteurs Virole interne de stator

Also Published As

Publication number Publication date
JP4794420B2 (ja) 2011-10-19
RU2006142824A (ru) 2008-06-20
CN1978870B (zh) 2012-05-30
CA2569564C (fr) 2013-12-24
US20070128020A1 (en) 2007-06-07
FR2894282A1 (fr) 2007-06-08
EP1793093A2 (de) 2007-06-06
CN1978870A (zh) 2007-06-13
JP2007154890A (ja) 2007-06-21
CA2569564A1 (fr) 2007-06-05
US7780398B2 (en) 2010-08-24
DE602006012915D1 (de) 2010-04-29
EP1793093A3 (de) 2008-12-03

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