EP1903186A1 - 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
EP1903186A1
EP1903186A1 EP07116773A EP07116773A EP1903186A1 EP 1903186 A1 EP1903186 A1 EP 1903186A1 EP 07116773 A EP07116773 A EP 07116773A EP 07116773 A EP07116773 A EP 07116773A EP 1903186 A1 EP1903186 A1 EP 1903186A1
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EP
European Patent Office
Prior art keywords
turbine
support
sealing ring
stator
stator according
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
EP07116773A
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English (en)
French (fr)
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EP1903186B1 (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
Original Assignee
SNECMA SAS
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Publication date
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Publication of EP1903186A1 publication Critical patent/EP1903186A1/de
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Publication of EP1903186B1 publication Critical patent/EP1903186B1/de
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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.
  • FIG. 1 shows the axial half-section of a gas turbine engine 1, seen at the level of the high-pressure turbine.
  • 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.
  • FIG. 2 shows a representation of the evolution of the displacement of the rotor R and of the stator S respectively as a function of the variation of the engine speed over time.
  • the transient game consumption A is greater than that B obtained after thermal stabilization.
  • game consumption means the measurement of the movement of the rotor less that of the displacement of the stator.
  • 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 comprising a turbine casing, a turbine sealing ring and a sealing ring support connecting the sealing ring to the casing, is characterized by the carrier is provided with a heat shield element disposed on the turbine side, and comprises on one side only a radial flange through which it is attached to the turbine housing.
  • 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 more particularly 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.
  • FIG 3 shows an enlarged detail of the mounting of the sealing ring 13 in the housing 9 and incorporating the solution of the invention.
  • the ring support 11 according to the example consists of a metal web, such as an annular shell, of substantially frustoconical shape of the same axis as the motor.
  • the support is here formed of a single piece but it can also consist of several ring sectors interconnected to form an annular assembly.
  • the support 11 comprises radial flanges 11a and 11b for fixing the elements 13 forming the sealing ring of the high-pressure turbine or HP.
  • the attachment according to this example is of tongue and groove type. For upstream attachment, to the combustion chamber.
  • the back of the elements 13 is shaped to provide an axial opening groove 13a which cooperates with an axial return 11b1 of the radial flange 11b.
  • the downstream attachment of the elements 13 is also ensured by a groove 13b whose outer leg bears against an axial return 11a1 of the flange 11a and is held in position by clamps 17.
  • 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
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 true EP1903186A1 (de) 2008-03-26
EP1903186B1 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)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953556A1 (fr) * 2009-12-07 2011-06-10 Snecma Turbine haute pression d'un turboreacteur
WO2012120228A1 (fr) 2011-03-07 2012-09-13 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
FR2972484A1 (fr) * 2011-03-07 2012-09-14 Snecma Ensemble statorique de turbine comportant des moyens de protection thermique

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110293407A1 (en) * 2010-06-01 2011-12-01 Wagner Joel H Seal and airfoil tip clearance control
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
US10247028B2 (en) * 2013-10-07 2019-04-02 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
WO2015084550A1 (en) * 2013-12-03 2015-06-11 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 (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2293594A1 (fr) * 1974-12-07 1976-07-02 Rolls Royce Perfectionnements aux turbomoteurs
FR2428141A1 (fr) * 1978-06-05 1980-01-04 Gen Electric Dispositif perfectionne de support de virole de turbine
GB2251895A (en) * 1980-10-03 1992-07-22 Rolls Royce Gas turbine shroud ring
FR2832178A1 (fr) * 2001-11-15 2003-05-16 Snecma Moteurs Dispositif de refroidissement pour anneaux de turbine a gaz

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3736069A (en) * 1968-10-28 1973-05-29 Gen Motors Corp Turbine stator cooling control
GB1501916A (en) * 1975-06-20 1978-02-22 Rolls Royce Matching thermal expansions of components of turbo-machines
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
GB2047354B (en) * 1979-04-26 1983-03-30 Rolls Royce Gas turbine engines
FR2576637B1 (fr) * 1985-01-30 1988-11-18 Snecma Anneau de turbine a gaz.
US5174714A (en) * 1991-07-09 1992-12-29 General Electric Company Heat shield mechanism for turbine engines
US5562408A (en) * 1995-06-06 1996-10-08 General Electric Company Isolated turbine shroud
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 (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2293594A1 (fr) * 1974-12-07 1976-07-02 Rolls Royce Perfectionnements aux turbomoteurs
FR2428141A1 (fr) * 1978-06-05 1980-01-04 Gen Electric Dispositif perfectionne de support de virole de turbine
GB2251895A (en) * 1980-10-03 1992-07-22 Rolls Royce Gas turbine shroud ring
FR2832178A1 (fr) * 2001-11-15 2003-05-16 Snecma Moteurs Dispositif de refroidissement pour anneaux de turbine a gaz

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953556A1 (fr) * 2009-12-07 2011-06-10 Snecma Turbine haute pression d'un turboreacteur
WO2012120228A1 (fr) 2011-03-07 2012-09-13 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
FR2972483A1 (fr) * 2011-03-07 2012-09-14 Snecma Carter de turbine comportant des moyens de fixation de secteurs d'anneau
FR2972484A1 (fr) * 2011-03-07 2012-09-14 Snecma Ensemble statorique de turbine comportant des moyens de protection thermique
CN103380268A (zh) * 2011-03-07 2013-10-30 斯奈克玛 包括环形扇体连接装置的涡轮机壳体
CN103380268B (zh) * 2011-03-07 2016-04-20 斯奈克玛 包括环形扇体连接装置的涡轮机壳体
US10487689B2 (en) 2011-03-07 2019-11-26 Safran Aircraft Engines Turbine casing comprising ring sector attachment means

Also Published As

Publication number Publication date
CA2602940C (fr) 2014-09-02
US20080075584A1 (en) 2008-03-27
JP2008075657A (ja) 2008-04-03
RU2449131C2 (ru) 2012-04-27
RU2007135200A (ru) 2009-03-27
CN101178016A (zh) 2008-05-14
US7946807B2 (en) 2011-05-24
FR2906295B1 (fr) 2011-11-18
CA2602940A1 (fr) 2008-03-22
EP1903186B1 (de) 2017-01-25
CN101178016B (zh) 2013-08-21
FR2906295A1 (fr) 2008-03-28

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