EP1496207A1 - Dispositif pour piloter passivement la dilatation thermique du carter d'un turboréacteur - Google Patents
Dispositif pour piloter passivement la dilatation thermique du carter d'un turboréacteur Download PDFInfo
- Publication number
- EP1496207A1 EP1496207A1 EP04291648A EP04291648A EP1496207A1 EP 1496207 A1 EP1496207 A1 EP 1496207A1 EP 04291648 A EP04291648 A EP 04291648A EP 04291648 A EP04291648 A EP 04291648A EP 1496207 A1 EP1496207 A1 EP 1496207A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flange
- housing
- recess
- flanges
- casing
- 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
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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
- 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
- F01D25/243—Flange connections; Bolting arrangements
-
- 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 turbojet engines and concerns in particular the high pressure compressor extension housing of turbojet.
- Turbojets generally comprise at least one low pressure compressor and a high pressure compressor. It is frequent to take gas at a compressor stage so to feed relatively cold fluid from other downstream parts of the turbomachine, for example a turbine distributor, for cooling them or upstream parts, for example for defrosting at the level of low pressure compressor.
- upstream and downstream will be used to indicate the position of a part in relation to the overall flow of gas during operation of the turbojet engine.
- the high pressure compressor is located upstream of the chamber of combustion.
- the compressor comprises a inner casing 2, around which extends a casing 3 said extension.
- the crankcase extension 3 comprises a downstream flange 4, to secure it with the housing 5 of the combustion chamber 6, and which supports a wall 7 of separation between the two volumes.
- the downstream flange 4 of the expansion casing 3 is fixedly connected to the upstream flange 8 of the combustion chamber housing 5, by bolts of link 9 located at the level of the distributed flange holes 10 circumferentially to the flange 4.
- the two flanges 4, 8 of the housing 3 and the combustion chamber 6, enclose an upstream flange 11 of a diffuser cone 12, which is a perforated cone located in the enclosure of the combustion chamber 6.
- the downstream face 14 of the flange 4 of the casing 3 is flat, pressed against the flange 11 of the diffuser cone 12.
- the cooling fluid of other elements of the turbojet engine is taken from the seventh stage of the compressor 1, not shown, by orifices provided for this purpose, both on the housing 2 of the compressor and on the expansion casing 3.
- the space annular 13 located between these two casings 2, 3 is bathed in this fluid.
- the high speed imposed on the engine causes a high rise the temperature of the air taken from the compressor and thus from the crankcase extension 3, whose skin is quite thin and has low thermal inertia and undergoes significant dilation. It reaches in a short time the temperature about 550 ° C.
- the flange 4 of this housing 3, more massive and more bathed in the enclosure 15 of the nacelle, remains at this time at a temperature about 200 ° C, especially at its outer periphery.
- the service life of the expansion case is much longer weak than the goal. It follows during the life of the engine a need in maintenance and a high cost of use related to the removal of the engine outside planned visits.
- the present invention aims to overcome these disadvantages.
- the invention relates to a device for driving passively the thermal expansion of the expansion casing of a turbojet engine and relieve stress, said extension housing enveloping the housing high pressure compressor interior of the turbojet, and comprising a flange for fixing to an upstream flange of the housing of the chamber of combustion.
- This device is characterized by the fact that at least one cavity circumferential is formed between said two flanges in which circulates a stream taken at the inlet of the combustion chamber.
- the flange of the housing is allowed to expand in depending on the higher temperature of the air taken downstream. Expansion of the piloted flange thus passively accompanies that of the skin of the crankcase and reduces the source of stress between the two parts of the crankcase.
- the two flanges enclose a holding flange of a diffuser cone, the cavity being formed between one of the crankcase flanges and the flange of the cone diffuser.
- the cavity is formed by a recess formed in one of said flanges.
- the recess providing an internal transverse flange and an external transverse support flange on the face of the adjacent flange, the internal axial flange has calibrated perforations forming grooves radial, gas inlet, and the flange includes calibrated perforations forming outlet channels of the gas stream.
- the channels comprise an inlet orifice located in the recess and an outlet opening into the space ring located between the compressor housing and the expansion housing.
- the cavity is formed of several recesses arranged circumferentially in sectors, each recess communicating with a radial groove and a channel.
- the throat radial is located at a transverse end of the recess and the channel is located at the other transverse end of the recess.
- the turbojet engine comprises a high pressure compressor 21 and a combustion chamber 26.
- the compressor comprises a casing 22, wrapped by an expansion casing 23.
- the compressor housing 22 and the extension casing 23 are connected by a wall 27 with a Y-shaped section, the two branches of the Y being directed towards the downstream part of the turbojet, one supporting the compressor housing 22 and the other being supported by an inlet flange 24 of the extension casing 23.
- the combustion chamber 26 comprises a housing 25, which comprises an upstream flange 28.
- the upstream flange of the combustion chamber 28 and the downstream flange of the extension casing 24 are connected by connecting bolts 29, through, in particular, holes 30 in the flange of the extension casing 24.
- the two flanges grip, in a fixed manner, an upstream flange 31 of a cone diffuser 32.
- This diffuser cone 32 is a perforated cone extending into the chamber of the combustion chamber 26, and whose role is to guide and to diffuse gas flows.
- the flange of the extension casing 24 of the invention comprises, on its downstream face 34, a circumferential recess 40, providing a flange internal transverse 41 and an external transverse flange 42 bearing on the face upstream of the upstream flange of the diffuser cone 31.
- the internal transverse flange 41 of the flange of the extension casing 24 has calibrated perforations forming radial grooves 43. Furthermore, the flange of the extension casing 24 comprises calibrated perforations forming channels 44, the inlet port is in the recess 40 and the outlet orifice in the annular space 33 located between the housing of the compressor 22 and the extension housing 23.
- Each groove 43 and each channel 44 is drilled, at the recess 40, to the right of a flange hole 30, in order to limit overstressing on board.
- the annular space 33 located between the compressor housing 22 and the extension housing 23 is bathed in gas taken downstream of the last compressor stage 21, here on the seventh floor, which supplies fluid from a relative point of view, other downstream parts of the turbomachine, for example example a turbine distributor, for cooling, or in hot fluid, from a relative point of view, parts upstream, for example for the defrosting at the low pressure compressor. Ports are provided for this purpose, both on the compressor housing 22 and on the housing extension 23.
- the rear flange of the extension casing 24 is circumferentially divided into sectors 50, 51, 52, for example, in the case of the invention of eight.
- Each sector comprises a recess 40, a groove 43 at one end transverse of the recess 40 and a channel 44 at the other end of the recess 40.
- the sectors are separated by radial walls 53, 54.
- the enclosure of the combustion chamber is bathed in a gas at the temperature of 650 ° C and at the pressure of 40 bar, while the annular space 33 located between the compressor housing 22 and the extension housing 23 is bathed in a gas at a temperature of 550 ° C and a pressure of 25 bar.
- the housing flange extension 24 is bathed in the enclosure 35 of the nacelle of the turbojet engine.
- the cavity 45 formed by the recess 40 between the downstream face 34 of the housing flange extension 24, its transverse inner rim 41, its transverse flange 42 and the upstream face of the front flange of the diffuser cone 31, is flow of gas from the enclosure of the chamber of combustion 26.
- This gas flow maintained by the pressure difference will heat the flange 24, because of its high temperature compared to that of this last.
- the invention thus makes it possible to assist the expansion of the flange 24 and to reduce the thermal gradient between it and the expansion case 23.
- the invention has been described in the context of the flange between the housing extension and the chamber cover but it applies to any flange subject to significant thermal gradients.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- la figure 1 représente une vue de côté en coupe d'une bride de l'art antérieur ;
- la figure 2 représente une vue en coupe et en perspective de la bride de la figure 1 ;
- la figure 3 représente une vue de côté en coupe de la forme de réalisation préférée d'une bride de l'invention ;
- la figure 4 représente une vue en coupe et en perspective de la bride de la figure 3, et
- la figure 5 représente une vue en perspective de la bride de l'invention.
Claims (10)
- Dispositif pour piloter passivement la dilation thermique du carter d'extension (23) d'un turboréacteur et en soulager les contraintes, ledit carter d'extension (23) enveloppant le carter intérieur (2) de compresseur haute pression (1) du turboréacteur, et comportant une bride (24) de fixation à une bride amont (28) du carter (25) de la chambre de combustion (26), caractérisé par le fait qu'au moins une cavité (45) circonférentielle est ménagée entre les dites deux brides (24 et 28) dans laquelle circule du gaz prélevé en entrée de la chambre de combustion (26).
- Dispositif selon la revendication 1 dans lequel les deux brides enserrent une bride (31) de maintien d'un cône diffuseur (32), la cavité étant ménagée entre une (24) des brides de carter et la bride du cône diffuseur.
- Dispositif selon l'une des revendications 1 ou 2 dans lequel la cavité est formée par un évidement (40) ménagé dans une (24) des dites brides.
- Dispositif selon la revendication 1, 2 ou 3 dans lequel la circulation du flux de gaz se fait grâce à des perforations calibrées (43, 44) ménagées dans une bride.
- Dispositif selon la revendication 4, dans lequel, l'évidement (40) ménageant un rebord transversal interne (41) et un rebord transversal externe (42) d'appui sur la face de la bride adjacente, le rebord axial interne (41) comporte des perforations calibrées formant des gorges radiales (43), d'entrée de gaz, et la bride (24) comprend des perforations calibrées formant des canaux (44), de sortie du flux de gaz.
- Dispositif selon la revendication 5, dans lequel les canaux (44) comprennent un orifice d'entrée se situant dans l'évidement (40) et un orifice de sortie débouchant dans l'espace annulaire (33) situé entre le carter du compresseur (22) et le carter d'extension (23).
- Dispositif selon l'une des revendications 3 à 6, dont la cavité est formée de plusieurs évidements disposés circonférentiellement en secteurs (50, 51, 52), chaque évidement (40) communiquant avec une gorge radiale (43) et un canal (44).
- Dispositif selon l'une des revendications 1 à 7, dont les brides comportent des trous de bride (30) disposés circonférentiellement, destinés à permettre le passage de liaisons boulons (29) pour la fixation de la bride (24) avec la bride amont (31) du cône diffuseur (32) et la bride amont (28) du carter (25) de la chambre de combustion (26).
- Dispositif selon la revendication 8, dans lequel les gorges radiales (43) sont percées au droit d'un trou de bride (30).
- Dispositif selon la revendication 9, dans lequel les canaux (44) sont percés au droit d'un trou de bride (30).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0308584 | 2003-07-11 | ||
FR0308584A FR2857409B1 (fr) | 2003-07-11 | 2003-07-11 | Dispositif pour piloter passivement la dilatation thermique du carter d'extension d'un turboreacteur |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1496207A1 true EP1496207A1 (fr) | 2005-01-12 |
EP1496207B1 EP1496207B1 (fr) | 2006-12-20 |
Family
ID=33443282
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04291648A Active EP1496207B1 (fr) | 2003-07-11 | 2004-06-30 | Dispositif pour piloter passivement la dilatation thermique du carter d'un turboréacteur |
Country Status (7)
Country | Link |
---|---|
US (1) | US7185499B2 (fr) |
EP (1) | EP1496207B1 (fr) |
JP (1) | JP4174039B2 (fr) |
CA (1) | CA2472939C (fr) |
DE (1) | DE602004003749T2 (fr) |
FR (1) | FR2857409B1 (fr) |
RU (1) | RU2343298C2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014105492A1 (fr) | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Passages permettant de faciliter un écoulement secondaire entre des éléments |
Families Citing this family (22)
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---|---|---|---|---|
US20090067917A1 (en) * | 2007-09-07 | 2009-03-12 | The Boeing Company | Bipod Flexure Ring |
FR2925122B1 (fr) * | 2007-12-14 | 2015-09-04 | Snecma | Dispositif de decouplage d'un support de palier |
US8875520B2 (en) * | 2008-12-31 | 2014-11-04 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine device |
US8459941B2 (en) * | 2009-06-15 | 2013-06-11 | General Electric Company | Mechanical joint for a gas turbine engine |
ITMI20102195A1 (it) * | 2010-11-26 | 2012-05-26 | Alstom Technology Ltd | "sistema di collegamento" |
JP5662566B2 (ja) * | 2011-04-26 | 2015-02-04 | 株式会社Ihi | 成形部品 |
GB201111666D0 (en) * | 2011-07-08 | 2011-08-24 | Rolls Royce Plc | A joint assembly for an annular structure |
FR2978732B1 (fr) * | 2011-08-05 | 2013-09-06 | Airbus Operations Sas | Dispositif de liaison plus particulierement adapte pour assurer la liaison entre une entree d'air et une motorisation d'une nacelle d'aeronef |
US9850780B2 (en) | 2012-12-29 | 2017-12-26 | United Technologies Corporation | Plate for directing flow and film cooling of components |
US8920109B2 (en) | 2013-03-12 | 2014-12-30 | Siemens Aktiengesellschaft | Vane carrier thermal management arrangement and method for clearance control |
WO2014150353A1 (fr) | 2013-03-15 | 2014-09-25 | United Technologies Corporation | Segment de conduit à faible niveau de fuite utilisant un ensemble joint de dilatation |
ITCO20130044A1 (it) * | 2013-10-08 | 2015-04-09 | Nuovo Pignone Srl | Cassa per macchina rotativa e macchina rotativa includente tale cassa |
DE102013226490A1 (de) | 2013-12-18 | 2015-06-18 | Rolls-Royce Deutschland Ltd & Co Kg | Gekühlte Flanschverbindung eines Gasturbinentriebwerks |
FR3019210B1 (fr) * | 2014-04-01 | 2016-05-13 | Snecma | Partie de turbomachine comportant une bride avec un dispositif de drainage |
US9611760B2 (en) | 2014-06-16 | 2017-04-04 | Solar Turbines Incorporated | Cutback aft clamp ring |
US9879565B2 (en) | 2015-01-20 | 2018-01-30 | United Technologies Corporation | Enclosed jacking insert |
US10415622B2 (en) * | 2016-05-03 | 2019-09-17 | General Electric Company | Method and system for hybrid gang channel bolted joint |
US10697300B2 (en) * | 2017-12-14 | 2020-06-30 | Raytheon Technologies Corporation | Rotor balance weight system |
US20190368381A1 (en) * | 2018-05-30 | 2019-12-05 | General Electric Company | Combustion System Deflection Mitigation Structure |
US20230003141A1 (en) * | 2021-06-30 | 2023-01-05 | Pratt & Whitney Canada Corp. | Outside fit flange for aircraft engine |
CN114017202B (zh) * | 2021-11-12 | 2023-04-18 | 中国航发沈阳发动机研究所 | 一种喷管复材中心锥连接结构 |
US11814977B1 (en) | 2022-08-29 | 2023-11-14 | Rtx Corporation | Thermal conditioning of flange with secondary flow |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1058936A (en) * | 1912-04-18 | 1913-04-15 | Paul A Bancel | Casing for steam-turbines. |
FR2007422A1 (fr) * | 1968-04-10 | 1970-01-09 | Licentia Gmbh | |
FR2468740A1 (fr) * | 1979-10-31 | 1981-05-08 | Gen Electric | Turbomachine comportant une structure de reglage du jeu entre le rotor et la virole qui l'entoure |
EP0559420A1 (fr) * | 1992-03-06 | 1993-09-08 | General Electric Company | Virole de réglage contrôlé thermiquement pour turbine à gaz |
US5593277A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Smart turbine shroud |
US6352404B1 (en) * | 2000-02-18 | 2002-03-05 | General Electric Company | Thermal control passages for horizontal split-line flanges of gas turbine engine casings |
FR2828908A1 (fr) * | 2001-08-23 | 2003-02-28 | Snecma Moteurs | Controle des jeux de turbine haute pression |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3372542A (en) * | 1966-11-25 | 1968-03-12 | United Aircraft Corp | Annular burner for a gas turbine |
US5127793A (en) * | 1990-05-31 | 1992-07-07 | General Electric Company | Turbine shroud clearance control assembly |
US6439616B1 (en) * | 2001-03-29 | 2002-08-27 | General Electric Company | Anti-rotation retainer for a conduit |
-
2003
- 2003-07-11 FR FR0308584A patent/FR2857409B1/fr not_active Expired - Fee Related
-
2004
- 2004-06-30 DE DE602004003749T patent/DE602004003749T2/de active Active
- 2004-06-30 EP EP04291648A patent/EP1496207B1/fr active Active
- 2004-07-08 CA CA2472939A patent/CA2472939C/fr active Active
- 2004-07-08 JP JP2004201650A patent/JP4174039B2/ja active Active
- 2004-07-08 US US10/885,757 patent/US7185499B2/en active Active
- 2004-07-09 RU RU2004121114/06A patent/RU2343298C2/ru active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1058936A (en) * | 1912-04-18 | 1913-04-15 | Paul A Bancel | Casing for steam-turbines. |
FR2007422A1 (fr) * | 1968-04-10 | 1970-01-09 | Licentia Gmbh | |
FR2468740A1 (fr) * | 1979-10-31 | 1981-05-08 | Gen Electric | Turbomachine comportant une structure de reglage du jeu entre le rotor et la virole qui l'entoure |
EP0559420A1 (fr) * | 1992-03-06 | 1993-09-08 | General Electric Company | Virole de réglage contrôlé thermiquement pour turbine à gaz |
US5593277A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Smart turbine shroud |
US6352404B1 (en) * | 2000-02-18 | 2002-03-05 | General Electric Company | Thermal control passages for horizontal split-line flanges of gas turbine engine casings |
FR2828908A1 (fr) * | 2001-08-23 | 2003-02-28 | Snecma Moteurs | Controle des jeux de turbine haute pression |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014105492A1 (fr) | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Passages permettant de faciliter un écoulement secondaire entre des éléments |
EP2938841A4 (fr) * | 2012-12-29 | 2015-12-30 | United Technologies Corp | Passages permettant de faciliter un écoulement secondaire entre des éléments |
Also Published As
Publication number | Publication date |
---|---|
JP2005030402A (ja) | 2005-02-03 |
CA2472939C (fr) | 2012-03-27 |
US7185499B2 (en) | 2007-03-06 |
US20050204746A1 (en) | 2005-09-22 |
DE602004003749D1 (de) | 2007-02-01 |
FR2857409B1 (fr) | 2006-07-28 |
CA2472939A1 (fr) | 2005-01-11 |
JP4174039B2 (ja) | 2008-10-29 |
RU2343298C2 (ru) | 2009-01-10 |
DE602004003749T2 (de) | 2007-10-11 |
EP1496207B1 (fr) | 2006-12-20 |
RU2004121114A (ru) | 2006-01-10 |
FR2857409A1 (fr) | 2005-01-14 |
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