EP1903186B1 - Turbinengehäusevorrichtung mit thermischer Abdeckung zum Kontrollieren eines Blattspitzenspalts - Google Patents

Turbinengehäusevorrichtung mit thermischer Abdeckung zum Kontrollieren eines Blattspitzenspalts Download PDF

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Publication number
EP1903186B1
EP1903186B1 EP07116773.8A EP07116773A EP1903186B1 EP 1903186 B1 EP1903186 B1 EP 1903186B1 EP 07116773 A EP07116773 A EP 07116773A EP 1903186 B1 EP1903186 B1 EP 1903186B1
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EP
European Patent Office
Prior art keywords
turbine
support
stator
casing
heat shield
Prior art date
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Active
Application number
EP07116773.8A
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English (en)
French (fr)
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EP1903186A1 (de
Inventor
Vincent Philippot
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
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Safran Aircraft Engines SAS
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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
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Definitions

  • the present invention relates to the field of turbomachines and aims a means for controlling the clearance between the top of the turbine blades and the housing.
  • a gas turbine engine typically comprises a compressor, in one or more stages, a combustion chamber and one or more turbine stages.
  • the compressor connected to the turbine, supplies air to the combustion chamber and the hot gases produced are directed on the turbine to extract the energy.
  • the compressor and turbine rotors are provided with vanes at their periphery moving perpendicularly to the motor axis inside annular stator pieces forming sealing rings with which they provide an operating clearance. This clearance must be sufficient so that friction does not slow down the rotation of the moving parts but it must be controlled to prevent a large amount of fluid is diverted from the active surfaces of the blades. To ensure as high a return as possible it is important to master this game.
  • the present invention relates to the operating clearance of a turbine rotor and more particularly of the rotor disposed immediately downstream of the combustion chamber.
  • a turbine rotor that is to say having two or more independent shafts, generally at most three, it is the high pressure body.
  • the radial clearances at the top of the blades are the consequence of the different radial thermomechanical displacements between the rotors and the stators.
  • the turbine rotor 3 comprises a disc 31, provided with blades 33 distributed on its rim, and mounted transversely on a central shaft.
  • the rotor is disposed downstream of a stationary distributor stage 5 communicating with the combustion chamber 7, of which only the bottom is visible here.
  • the housing 9 is composed of several ferrules assembled by flanges.
  • the combustion chamber casing 91 and the high pressure turbine casing 96 are distinguished.
  • the two housings are retained by a flanged assembly 95.
  • the casing supports the elements of the combustion chamber, the upstream and downstream distributors 15 and 15. a support 11 of sealing ring 13.
  • Discs, blades and stator elements are subjected to both mechanical and thermal displacements.
  • the radial clearance is not so not constant.
  • the rotor and the stator do not have the same amplitudes of displacement nor the same thermal response time.
  • the game at the top of the blade in this case is set in such a way that the maximum wear of the blades during the life of the engine does not exceed capabilities of the machine.
  • This maximum wear is determined according to the maximum play consumption seen during the life of the engine and which is based on the displacements of the stator and the rotor.
  • This maximum consumption is generally observed during cycles that are designated in the field by the terms: critical re-acceleration.
  • Such a cycle consists of starting from a stabilized full-throttle operating mode, reducing the engine speed to idle in a short time and then controlling a re-acceleration to full throttle in a short period of time as well.
  • a first object of the invention is to find a solution to this problem.
  • Another objective is to find a solution that does not involve a major transformation of the existing structure and that is inexpensive to implement.
  • the gas turbine engine turbine stator comprises a turbine casing, a turbine sealing ring and a sealing ring support connecting the sealing ring to the casing as characterized in FIG. claim 1.
  • the solution therefore consisted in increasing the thermal response time of the stator by means of a heat shield which delays the influence of the temperature of the hot gases of the stream coming from the combustion chamber.
  • This solution is particularly advantageous because it has proved effective.
  • it can be implemented by relatively simple means.
  • the heat shielding member comprises a sheet forming a gap with the surface of the support.
  • the space forms a dead cavity, not swept by gases.
  • the space contains a thermally insulating material.
  • the invention applies to a stator whose support comprises on one side a radial flange for attachment to the turbine casing and on the other side a means for fixing the elements of the sealing ring.
  • the support advantageously forms a generally frustoconical web and the means for fixing the elements of the sealing ring comprises two radial flanges enclosing the elements of the sealing ring.
  • the heat shield element comprises a first sheet fixed between the two radial flanges. It also comprises a second sheet disposed axially between the means for fixing the elements of the sealing ring and the radial flange for fixing the support to the housing.
  • the patent FR2832178 discloses a cooling means of a stator ring with air distribution plates but without mention of steering the support of the ring.
  • the patent FR 2428141 describes a ring support fixed to the housing by upstream and downstream flanges with selective adjustment of its cooling and heating. A sheet protects the support thermally.
  • vanes 5 of the upstream distributor are fixed by bolts to the radial flange 11b.
  • the support 11 is itself mounted on the turbine casing 93 via a radial transverse flange 11c. This flange is inserted into the flange assembly 95 which connects the various elements of the housing 9.
  • the support 11 is not subject to any active play control and does not include any means of ventilation for this purpose.
  • a heat shield has been arranged on the inner face of the support 11. That is to say the face turned towards the vein of engine gas.
  • the heat shield is advantageously constituted by a first sheet placed parallel to the web of the support 11 between the two radial flanges 11a and 11b. This sheet is made integral by welding, brazing, screwing or any other means of attachment to the support.
  • the sheet 21 is distant from the web 11 so as to provide a cavity 21A.
  • This cavity is preferably dead, that is to say that the gases it contains do not circulate. For example, it is closed.
  • the gaseous layer thus forms a thermally insulating mass. However, this cavity may optionally contain another thermally insulating material.
  • a second sheet is disposed in the same way, upstream of the flange 11b, on the inner face of the web 11 at a distance from the latter. It is welded, brazed, screwed or other to the veil and Maintains a dead cavity 22A with the web 11. The gaseous mass contained in this cavity also forms a thermally insulating layer.
  • the support 11 is metal as well as the plates 21 and 22.
  • the clearance between the top of the blades 33 and the ring 13 is fixed and determined value.
  • This game results from a balance between the deformations of mechanical and thermal origin to which the moving and fixed parts are subjected. During a transient regime this equilibrium is disturbed. In particular in the case of a critical re-acceleration, as presented above, during the rapid reduction phase of the regime the temperature of the gases in the motor vein drops. Due to the heat shield, the response to the temperature drop of the support is slowed compared to that of the prior art assembly.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Claims (8)

  1. Stator einer Turbine einer Gasturbinenmaschine, ein Turbinengehäuse (9), einen Turbinendichtring (13) und eine Dichtringhalterung (11) umfassend, welche den Dichtring (13) mit dem Gehäuse (9) verbindet, wobei die Halterung (11) keiner aktiven Spielsteuerung unterworfen ist und keine Lüftungseinrichtung zu diesem Zweck umfasst, wobei die Halterung Folgendes umfasst
    auf der einen Seite lediglich einen radialen Flansch (11c), mit dem sie am Turbinengehäuse (9) befestigt ist, und auf der Seite gegenüber dem besagten radialen Flansch (11c) zwei radiale Flansche (11a, 11b) zur Befestigung der Elemente des Dichtringes (13),
    dadurch gekennzeichnet, dass die Halterung (11) mit einem Element (21, 22) versehen ist, das einen Hiltzeschild bildet, der auf Seiten der Turbine an der Innenfläche der Halterung (11) angeordnet ist.
  2. Stator nach dem vorhergehenden Anspruch, dessen Element (11), das einen Hiltzeschild bildet, ein Blech (21, 22) umfasst, das einen Raum (21A; 22A) zur Oberfläche der Halterung freihält.
  3. Stator nach Anspruch 2, dessen Raum (21A; 22A) eine ungenutzte Vertiefung bildet, durch die keine Gase strömen.
  4. Stator nach Anspruch 2, dessen besagter Raum (21A; 22A) ein wärmeisolierendes Material umfasst.
  5. Stator nach Anspruch 1, dessen Halterung (11) die Form eines kegelstumpfförmigen Deckmantels aufweist.
  6. Stator nach Anspruch 1, dessen Element, das einen Hiltzeschild bildet, ein erstes Blech (21) umfasst, das zwischen den beiden radialen Flanschen (11a, 11b) befestigt ist.
  7. Stator nach dem vorhergehenden Anspruch, dessen Element, das einen Hiltzeschild bildet, ein zweites Blech (22) umfasst, das axial zwischen dem Mittel zum Befestigen der Elemente (13) des Dichtringes und dem radialen Flansch (11c) zur Befestigung der Gehäusehalterung angeordnet ist.
  8. Gasturbinentriebwerk, einen Stator einer Turbine nach einem der vorhergehenden Ansprüche umfassend.
EP07116773.8A 2006-09-22 2007-09-19 Turbinengehäusevorrichtung mit thermischer Abdeckung zum Kontrollieren eines Blattspitzenspalts Active EP1903186B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0653901A FR2906295B1 (fr) 2006-09-22 2006-09-22 Dispositif de toles isolantes sur carter pour amelioration du jeu en sommet d'aube

Publications (2)

Publication Number Publication Date
EP1903186A1 EP1903186A1 (de) 2008-03-26
EP1903186B1 true EP1903186B1 (de) 2017-01-25

Family

ID=38069160

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07116773.8A Active EP1903186B1 (de) 2006-09-22 2007-09-19 Turbinengehäusevorrichtung mit thermischer Abdeckung zum Kontrollieren eines Blattspitzenspalts

Country Status (7)

Country Link
US (1) US7946807B2 (de)
EP (1) EP1903186B1 (de)
JP (1) JP2008075657A (de)
CN (1) CN101178016B (de)
CA (1) CA2602940C (de)
FR (1) FR2906295B1 (de)
RU (1) RU2449131C2 (de)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953556B1 (fr) * 2009-12-07 2012-01-13 Snecma Turbine haute pression d'un turboreacteur
US20110293407A1 (en) * 2010-06-01 2011-12-01 Wagner Joel H Seal and airfoil tip clearance control
FR2972483B1 (fr) 2011-03-07 2013-04-19 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
FR2972484B1 (fr) * 2011-03-07 2013-04-19 Snecma Ensemble statorique de turbine comportant des moyens de protection thermique
US9121301B2 (en) 2012-03-20 2015-09-01 General Electric Company Thermal isolation apparatus
RU2500894C1 (ru) * 2012-04-27 2013-12-10 Николай Борисович Болотин Турбина газотурбинного двигателя
US9151226B2 (en) * 2012-07-06 2015-10-06 United Technologies Corporation Corrugated mid-turbine frame thermal radiation shield
EP2696036A1 (de) * 2012-08-09 2014-02-12 MTU Aero Engines GmbH Klemmring für eine Strömungsmaschine
WO2015069338A2 (en) * 2013-10-07 2015-05-14 United Technologies Corporation Gas turbine engine blade outer air seal thermal control system
CN103541777B (zh) * 2013-11-05 2015-05-06 南京航空航天大学 用于叶轮机械的叶片式无泄漏封严结构
US10240475B2 (en) 2013-12-03 2019-03-26 United Technologies Corporation Heat shields for air seals
RU172776U1 (ru) * 2016-10-31 2017-07-24 Публичное акционерное общество "Научно-производственное объединение "Сатурн" Статор турбины
US10801359B2 (en) * 2017-03-14 2020-10-13 General Electric Company Method and system for identifying rub events
FR3086323B1 (fr) * 2018-09-24 2020-12-11 Safran Aircraft Engines Carter interne de turmomachine a isolation thermique amelioree
CN111312058B (zh) * 2019-11-29 2022-02-25 中国科学院工程热物理研究所 压气机试验件结构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1225445A (de) * 1968-10-28 1971-03-17
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
EP0522834A1 (de) * 1991-07-09 1993-01-13 General Electric Company Hitzeschild für Turbinenmotoren

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1484936A (en) * 1974-12-07 1977-09-08 Rolls Royce Gas turbine engines
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
US4303371A (en) * 1978-06-05 1981-12-01 General Electric Company Shroud support with impingement baffle
GB2047354B (en) * 1979-04-26 1983-03-30 Rolls Royce Gas turbine engines
GB2251895B (en) * 1980-10-03 1992-12-09 Rolls Royce Gas turbine engine
FR2576637B1 (fr) * 1985-01-30 1988-11-18 Snecma Anneau de turbine a gaz.
US5562408A (en) * 1995-06-06 1996-10-08 General Electric Company Isolated turbine shroud
FR2832178B1 (fr) * 2001-11-15 2004-07-09 Snecma Moteurs Dispositif de refroidissement pour anneaux de turbine a gaz
US6726448B2 (en) * 2002-05-15 2004-04-27 General Electric Company Ceramic turbine shroud
FR2857406B1 (fr) * 2003-07-10 2005-09-30 Snecma Moteurs Refroidissement des anneaux de turbine
FR2867224B1 (fr) * 2004-03-04 2006-05-19 Snecma Moteurs Dispositif de maintien axial de secteur d'entretoise pour anneau d'une turbine haute-pression de turbomachine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1225445A (de) * 1968-10-28 1971-03-17
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
EP0522834A1 (de) * 1991-07-09 1993-01-13 General Electric Company Hitzeschild für Turbinenmotoren

Also Published As

Publication number Publication date
CA2602940A1 (fr) 2008-03-22
RU2007135200A (ru) 2009-03-27
FR2906295A1 (fr) 2008-03-28
CN101178016A (zh) 2008-05-14
RU2449131C2 (ru) 2012-04-27
JP2008075657A (ja) 2008-04-03
EP1903186A1 (de) 2008-03-26
CN101178016B (zh) 2013-08-21
US20080075584A1 (en) 2008-03-27
FR2906295B1 (fr) 2011-11-18
US7946807B2 (en) 2011-05-24
CA2602940C (fr) 2014-09-02

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