EP1059420A1 - Stator de compresseur à haute pression - Google Patents
Stator de compresseur à haute pression Download PDFInfo
- Publication number
- EP1059420A1 EP1059420A1 EP00401609A EP00401609A EP1059420A1 EP 1059420 A1 EP1059420 A1 EP 1059420A1 EP 00401609 A EP00401609 A EP 00401609A EP 00401609 A EP00401609 A EP 00401609A EP 1059420 A1 EP1059420 A1 EP 1059420A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ventilation
- ferrule
- sectors
- rings
- 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
Links
Images
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
-
- 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
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/545—Ducts
Definitions
- the subject of this invention is a stator heterogeneous structure likely to apply in particular to high pressure compressors of gas turbines.
- the rotor and stator structure of gas turbine is often cooled or ventilated by the air taken from the flow which flows through the machine.
- air taken from the flow which flows through the machine There are even double breakdowns associated with double samples, where a breakdown of a downstream part of the stator and rotor follows a first ventilation of the stator and rotor carried out further upstream.
- the air taken for ventilation in downstream comes from a part of the machine where it has already been compressed, which made it much warmer than the air from the upstream ventilation.
- the invention consists of a compressor stator fitted with a upstream ventilation and downstream ventilation warmer than upstream ventilation and including a ferrule defining a gas flow stream, characterized in that it comprises a first portion ferrule, subject to upstream ventilation, to continuous ring structure on a circumference and in a first material, and a second portion of ferrule, subjected to downstream ventilation, with structure formed of juxtaposed angular sectors and in one second material having a coefficient of expansion larger than the first material.
- the first and second materials can be chosen, respectively, from materials with a lower coefficient of expansion such as TA6V and titanium alloys, INC0909, intermetallic of the TiAl type, having an average coefficient of linear expansion of less than 10.10 -6 m per degree; and among materials with a greater coefficient of expansion such as nickel-based alloys of the type INC0718, RENE77 and derivatives, having an average coefficient of linear expansion close to 15.10 -6 m per degree.
- materials with a lower coefficient of expansion such as TA6V and titanium alloys, INC0909, intermetallic of the TiAl type, having an average coefficient of linear expansion of less than 10.10 -6 m per degree
- materials with a greater coefficient of expansion such as nickel-based alloys of the type INC0718, RENE77 and derivatives, having an average coefficient of linear expansion close to 15.10 -6 m per degree.
- figure 1 is an overview of a high pressure compressor a gas turbine
- Figure 2 is an enlarged view the downstream part of the stator of this compressor
- Figure 2A a similar view of another embodiment possible of the invention
- Figures 3 and 4 are two sections of the upstream part and the downstream part of the compressor
- Figure 5 is an enlarged view of the upstream part of the compressor.
- a high pressure compressor such as that of FIG. 1 comprises a central rotor 1 driven by a line of trees 2 and composed of a envelope 3 of tapered shape composed of rings 4 juxtaposed and separated by 5 discs at right stages of movable blades 6.
- a stator 7 surrounds the rotor 1 and comprises, in internal lining of a carcass 8, a portion 9 to which the invention relates and which consists of a support casing 10 and a ferrule 11 supported by the casing 10, facing the rotor 1 and which is used to define an annular vein 12 of gas flow in which the movable blade stages 6 and blade stages stationary 13 flow straightening, which are attached to the ferrule 11 and alternate with the previously mentioned floors.
- tips of stationary vanes 13, located in front the casing 3 of the rotor 1, carry rings of connection 14 furnished with circular bands of said material abradable 15, formed of a honeycomb structure or more generally of easy erosion, which is dug by facing ribs 16 erected on the casing 3 and which form with it a seal at labyrinth.
- the tips of the moving blades 6 are free of all equipment and end up close of the shell 11.
- the internal portion 9 of the stator 7 has discontinuities, which are openings of air sampling from vein 12, noted by references 17, 18 and which give in rooms 19 and 20 respectively established between portion 9 and carcass 8 and through which the air taken from the vein 12 to ventilate in particular the casing 10 and subject it to temperature and expansion determined thermal.
- the inside of rotor 1 is also ventilated, firstly through a bore 21 of the casing 3 located upstream of the rotor 1 and by which fresh air at about the same temperature as whoever enters room 19 is sucked out, then by another bore 22 of the casing 3, substantially at the right of the second opening 18.
- the rooms 19 and 20 divide stator 7 into two zones of ventilation, in front of which they extend respectively and which are located on both sides of the opening 19 for entry into the downstream chamber 20, which divide portion 9 in half.
- Sectors 23 and 23 'adjacent are joined by flexible tabs 24 sealing, extending in grooves longitudinal edges of the sectors and joining by their ends 25, between circles of sectors 23 and 23 'consecutive; and other tabs 26 flexible established in grooves purely or obliquely radial from the edges of sectors 23 and 23 ', and extending from the first tabs 24 to the casing 10.
- This arrangement effectively prevents gases, very hot in this place, from the vein 12 to leak between the sectors 23 and 23 'to reach the housing 10 and risk damaging it.
- the tabs 24 and 26 isolate empty volumes 27 (which can be filled with insulation at the heat) that appear between each of the circles of sectors 23 and 23 'and associated rings 28 of the casing 10.
- each of them includes a rear lip 31, projecting towards inside and back, and which is enclosed between a lip 32 of one of the rings 28, located radially outwards, and a lip 33 or 33 ' pointing forward and drawn either in front of sectors 23, either at the front of the ring 28 located on further downstream; and sectors 23 and 23 'include another outer lip 34 at the front, which cooperates with the lips 33 to grip the lips together 31 and 32 directed towards the rear.
- Sectors 23 ' differ in that they only understand one lip single at the front, bearing the reference 35 and oriented backwards, and which is housed in a groove 36 of the ring 28 located furthest forward.
- This mode is simpler than a fashion inspired by more traditional ring attachment designs ferrule, illustrated in FIG. 2A, where the lips 31 and 32 are joined by separate seals 37 with a cross-section clip and where the ferrule elements include a relatively high rib 38 ending in a lip 39 facing forward and housed in a groove of the adjacent ring; however, it is possible to adopt this less favorable conception if desired.
- Of 50 stud systems allow in all the cases of linking sectors 23 and 23 'to the rings 28 in angular direction; many achievements are within the reach of the skilled person.
- the mode of connection of sectors 23 and 23 'to rings 28 is quite flexible and absorbs deformations without receiving strong constraints.
- the rings 28 are preferably continuous on the circumference for give a simpler structure and better mechanical resistance.
- rotor 1 in the same material opposite the rings 28 of the stator 7.
- a nickel-based alloy, type INCO718, with high coefficient of expansion can be used for this downstream part of the compressor.
- the housing 10 is at this place composed of 40 rings, united between them by bolts 42 enclosing flanges 41 which complete, as well as the carcass 8, in the manner of rings 28; but these 40 rings still include protrusions 43 and 43 'radially inside, which lead to the air flow vein 12 and are therefore exposed to its temperature. Two of these outgrowths 43 are wide enough to extend opposite a stage of movable blades 6 respective.
- the ferrule 11 is therefore here formed at the same time by the protrusions 43 and 43 'and by the rings 44 supporting stationary vanes 13; the rings 44 end front and back with lips 45 which enter the grooves of the protuberances 43 and 43 '.
- mechanical systems 46 with nesting of tenon join the rings 40 to the rings 44 concentric against mutual rotations.
- the major difference with the downstream design is that the rings 44 are continuous on a circumference while like the rings 40. It is indeed estimated that like the heating is less important upstream, and that the temperature differences between the housing 10 and the ferrule 11 are less important also it's more simple and more advantageous to have a structure similar for both, the risks of deformation and excessive stresses being reduced.
- the material used has a coefficient of less expansion than that used for build the downstream of the casing, because we observe that the slower expansions these materials undergo slightly regulate the evolution of dilation during the transitional phases and allow finally to better control the games at the end of the blade moving blades 6.
- An alloy of the Inconel 909 type may be recommended or a TiAl type intermetallic.
- the rotor 1 can be constructed in a material with a coefficient of expansion close of that used for the stator rings 40 in look, for example a titanium alloy.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims (8)
- Stator de compresseur muni d'une ventilation en amont (17, 19) et une ventilation en aval (18, 20) d'air plus chaud qu'à la ventilation amont et comprenant une virole (11) délimitant une veine (12) d'écoulement de gaz, caractérisé en ce qu'il comprend une première portion de virole, soumise à la ventilation en amont (17), à structure annulaire (44) continue sur une circonférence et en un premier matériau, et une deuxième portion de virole, soumise à la ventilation aval, à structure formée de secteurs (23) angulaires juxtaposés et en un deuxième matériau ayant un coefficient de dilatation plus grand que le premier matériau.
- Stator suivant la revendication 1, caractérisé en ce que les premier et deuxième matériaux sont choisis, respectivement, parmi un groupe de matériaux à coefficient de dilatation plus bas tels que TA6V et alliages de titane, INC0909, intermétalliques du type TiAl, ayant un coefficient moyen de dilatation linéique inférieur à 10.10-6 m par degré ; et parmi un groupe de matériaux à coefficient de dilatation plus grand tels que des alliages à base de nickel du type INC0718, RENE77 et dérivés, ayant un coefficient moyen de dilatation linéique voisin de 15.10-6 m par degré.
- Stator suivant l'une quelconque des revendications 1 ou 2, caractérisé en ce qu'il comprend un carter (10) soutenant la virole (11), le carter (10) délimitant une chambre (19) appartenant à la ventilation amont et une chambre (20) appartenant à la ventilation aval, et en ce que le carter est formé en structure annulaire continue (28, 40) sur une circonférence devant les deux chambres.
- Stator suivant la revendication 3, caractérisé en ce que le carter (10) est composé d'anneaux (28, 40) venant en prolongement et formant un ensemble continu devant la première portion de virole et devant la deuxième portion de virole.
- Stator suivant la revendication 4, caractérisé en ce que les anneaux du carter devant la deuxième partie de la virole sont respectivement associés à des ensembles annulaires des secteurs juxtaposés (23, 23') de la virole, et les secteurs (23) comprennent pour la plupart une paire de lèvres concentriques (33, 34) à une extrémité, enserrant une lèvre (31) d'une extrémité opposée de secteurs (23, 23') d'un ensemble annulaire voisin et une lèvre (32) d'un anneau du carter associé audit ensemble annulaire voisin.
- Stator suivant la revendication 3, caractérisé en ce que les anneaux du carter devant la première partie de la virole présentent des excroissances (43, 43') s'étendant entre les anneaux de virole et délimitant aussi la veine d'écoulement (12), les anneaux de virole étant imbriqués entre les excroissances.
- Stator suivant l'une quelconque des revendications 1 à 6, caractérisé en ce que les secteurs (23, 23') sont réunis par des languettes souples (24, 26).
- Stator suivant l'une quelconque des revendication 1 à 7, caractérisé en ce que les première et deuxième portions de virole sont situées devant des portions d'un rotor (1) respectivement construites dans le premier matériau et le second matériau.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9907315 | 1999-06-10 | ||
FR9907315A FR2794816B1 (fr) | 1999-06-10 | 1999-06-10 | Stator de compresseur a haute pression |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1059420A1 true EP1059420A1 (fr) | 2000-12-13 |
EP1059420B1 EP1059420B1 (fr) | 2004-12-08 |
Family
ID=9546602
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00401609A Expired - Lifetime EP1059420B1 (fr) | 1999-06-10 | 2000-06-08 | Stator de compresseur à haute pression |
Country Status (5)
Country | Link |
---|---|
US (1) | US6390771B1 (fr) |
EP (1) | EP1059420B1 (fr) |
JP (1) | JP4124552B2 (fr) |
DE (1) | DE60016505T2 (fr) |
FR (1) | FR2794816B1 (fr) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1561998A1 (fr) | 2004-02-05 | 2005-08-10 | Snecma Moteurs | Diffuseur pour turboréacteur |
FR2913051A1 (fr) * | 2007-02-28 | 2008-08-29 | Snecma Sa | Etage de turbine dans une turbomachine |
EP2071133A1 (fr) * | 2007-12-14 | 2009-06-17 | Snecma | Module de turbomachine muni d'un dispositif d'amélioration des jeux radiaux |
WO2009123301A2 (fr) * | 2008-03-31 | 2009-10-08 | Mitsubishi Heavy Industries, Ltd. | Machine rotative |
WO2010026182A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane obtenu selon ce procede |
WO2010026179A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane obtenu selon ce procede |
WO2010026181A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane obtenu selon ce procede |
CN102705254A (zh) * | 2010-11-05 | 2012-10-03 | 通用电气公司 | 防护罩渗漏盖 |
WO2013162752A1 (fr) | 2012-04-24 | 2013-10-31 | United Technologies Corporation | Système de gestion thermique pour turbine à gaz |
FR3086323A1 (fr) | 2018-09-24 | 2020-03-27 | Safran Aircraft Engines | Carter interne de turmomachine a isolation thermique amelioree |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1118806A1 (fr) * | 2000-01-20 | 2001-07-25 | Siemens Aktiengesellschaft | Structure de paroi sous charge thermique et méthode pour fermer des fentes dans une tel structure |
DE102004016222A1 (de) * | 2004-03-26 | 2005-10-06 | Rolls-Royce Deutschland Ltd & Co Kg | Anordnung zur selbsttätigen Laufspalteinstellung bei einer zwei- oder mehrstufigen Turbine |
FR2887939B1 (fr) * | 2005-06-29 | 2016-09-30 | Soc Nat D'etude Et De Construction De Moteurs D'aviation Snecma | Compresseur multi-etages de turbomachine |
US7604455B2 (en) * | 2006-08-15 | 2009-10-20 | Siemens Energy, Inc. | Rotor disc assembly with abrasive insert |
US7704038B2 (en) * | 2006-11-28 | 2010-04-27 | General Electric Company | Method and apparatus to facilitate reducing losses in turbine engines |
FR2925108B1 (fr) * | 2007-12-14 | 2013-05-03 | Snecma | Module de turbomachine muni d'un dispositif d'amelioration des jeux radiaux |
US8613593B2 (en) * | 2008-12-30 | 2013-12-24 | Rolls-Royce North American Technologies Inc. | Engine case system for a gas turbine engine |
JP4856257B2 (ja) * | 2010-03-24 | 2012-01-18 | 川崎重工業株式会社 | タービンロータのシール構造 |
US9091172B2 (en) | 2010-12-28 | 2015-07-28 | Rolls-Royce Corporation | Rotor with cooling passage |
US9115600B2 (en) * | 2011-08-30 | 2015-08-25 | Siemens Energy, Inc. | Insulated wall section |
US20140286766A1 (en) * | 2012-09-11 | 2014-09-25 | General Electric Company | Compressor Casing Assembly Providing Access To Compressor Blade Sealing Assembly |
US10539153B2 (en) * | 2017-03-14 | 2020-01-21 | General Electric Company | Clipped heat shield assembly |
US10767485B2 (en) * | 2018-01-08 | 2020-09-08 | Raytheon Technologies Corporation | Radial cooling system for gas turbine engine compressors |
US20200072070A1 (en) * | 2018-09-05 | 2020-03-05 | United Technologies Corporation | Unified boas support and vane platform |
US11174742B2 (en) | 2019-07-19 | 2021-11-16 | Rolls-Royce Plc | Turbine section of a gas turbine engine with ceramic matrix composite vanes |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3854843A (en) * | 1971-12-01 | 1974-12-17 | R Penny | Composite elongate member having a predetermined effective coefficient of linear expansion |
US4101242A (en) * | 1975-06-20 | 1978-07-18 | Rolls-Royce Limited | Matching thermal expansion of components of turbo-machines |
US4578942A (en) * | 1983-05-02 | 1986-04-01 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Gas turbine engine having a minimal blade tip clearance |
US4805398A (en) * | 1986-10-01 | 1989-02-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S. N. E. C. M. A." | Turbo-machine with device for automatically controlling the rate of flow of turbine ventilation air |
US5127794A (en) * | 1990-09-12 | 1992-07-07 | United Technologies Corporation | Compressor case with controlled thermal environment |
US5160241A (en) * | 1991-09-09 | 1992-11-03 | General Electric Company | Multi-port air channeling assembly |
US5314303A (en) * | 1992-01-08 | 1994-05-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Device for checking the clearances of a gas turbine compressor casing |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1285255B (de) * | 1964-10-28 | 1968-12-12 | Bergmann Borsig Veb | Waermebeweglich aufgehaengte Leitgittersegmente von Axialgasturbinen |
US5351478A (en) * | 1992-05-29 | 1994-10-04 | General Electric Company | Compressor casing assembly |
FR2695164B1 (fr) * | 1992-08-26 | 1994-11-04 | Snecma | Turbomachine munie d'un dispositif empêchant une circulation longitudinale de gaz autour des étages d'aubes de redressement. |
US5653581A (en) * | 1994-11-29 | 1997-08-05 | United Technologies Corporation | Case-tied joint for compressor stators |
US5553999A (en) * | 1995-06-06 | 1996-09-10 | General Electric Company | Sealable turbine shroud hanger |
US6109868A (en) * | 1998-12-07 | 2000-08-29 | General Electric Company | Reduced-length high flow interstage air extraction |
-
1999
- 1999-06-10 FR FR9907315A patent/FR2794816B1/fr not_active Expired - Fee Related
-
2000
- 2000-05-25 JP JP2000154077A patent/JP4124552B2/ja not_active Expired - Lifetime
- 2000-06-05 US US09/586,791 patent/US6390771B1/en not_active Expired - Lifetime
- 2000-06-08 EP EP00401609A patent/EP1059420B1/fr not_active Expired - Lifetime
- 2000-06-08 DE DE60016505T patent/DE60016505T2/de not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3854843A (en) * | 1971-12-01 | 1974-12-17 | R Penny | Composite elongate member having a predetermined effective coefficient of linear expansion |
US4101242A (en) * | 1975-06-20 | 1978-07-18 | Rolls-Royce Limited | Matching thermal expansion of components of turbo-machines |
US4578942A (en) * | 1983-05-02 | 1986-04-01 | Mtu Motoren-Und Turbinen-Union Muenchen Gmbh | Gas turbine engine having a minimal blade tip clearance |
US4805398A (en) * | 1986-10-01 | 1989-02-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S. N. E. C. M. A." | Turbo-machine with device for automatically controlling the rate of flow of turbine ventilation air |
US5127794A (en) * | 1990-09-12 | 1992-07-07 | United Technologies Corporation | Compressor case with controlled thermal environment |
US5160241A (en) * | 1991-09-09 | 1992-11-03 | General Electric Company | Multi-port air channeling assembly |
US5314303A (en) * | 1992-01-08 | 1994-05-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Device for checking the clearances of a gas turbine compressor casing |
Cited By (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1561998A1 (fr) | 2004-02-05 | 2005-08-10 | Snecma Moteurs | Diffuseur pour turboréacteur |
EP1561998B1 (fr) * | 2004-02-05 | 2012-03-07 | Snecma | Diffuseur pour turboréacteur |
FR2913051A1 (fr) * | 2007-02-28 | 2008-08-29 | Snecma Sa | Etage de turbine dans une turbomachine |
EP1965034A1 (fr) | 2007-02-28 | 2008-09-03 | Snecma | Etage de turbine dans une turbomachine |
US8403636B2 (en) | 2007-02-28 | 2013-03-26 | Snecma | Turbine stage in a turbomachine |
EP2071133A1 (fr) * | 2007-12-14 | 2009-06-17 | Snecma | Module de turbomachine muni d'un dispositif d'amélioration des jeux radiaux |
FR2925109A1 (fr) * | 2007-12-14 | 2009-06-19 | Snecma Sa | Module de turbomachine muni d'un dispositif d'amelioration des jeux radiaux |
CN101952557A (zh) * | 2008-03-31 | 2011-01-19 | 三菱重工业株式会社 | 回转机械 |
WO2009123301A2 (fr) * | 2008-03-31 | 2009-10-08 | Mitsubishi Heavy Industries, Ltd. | Machine rotative |
WO2009123301A3 (fr) * | 2008-03-31 | 2010-09-16 | Mitsubishi Heavy Industries, Ltd. | Machine rotative |
RU2483218C2 (ru) * | 2008-03-31 | 2013-05-27 | Мицубиси Хеви Индастрис, Лтд. | Турбина |
WO2010026182A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane obtenu selon ce procede |
WO2010026181A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane obtenu selon ce procede |
WO2010026179A1 (fr) * | 2008-09-05 | 2010-03-11 | Snecma | Procede de fabrication d'une piece thermomecanique de revolution circulaire comportant un substrat porteur a base de titane revetu d'acier ou superalliage, carter de compresseur de turbomachine resistant au feu de titane obtenu selon ce procede |
US8888448B2 (en) | 2008-09-05 | 2014-11-18 | Snecma | Method for the manufacture of a circular revolution thermomechanical part including a titanium-based load-bearing substrate lined with steel or superalloy, a turbomachine compressor housing which is resistant to titanium fire obtained according to this method |
CN102705254A (zh) * | 2010-11-05 | 2012-10-03 | 通用电气公司 | 防护罩渗漏盖 |
CN102705254B (zh) * | 2010-11-05 | 2016-08-31 | 通用电气公司 | 用于引导漏出空气的***及方法 |
WO2013162752A1 (fr) | 2012-04-24 | 2013-10-31 | United Technologies Corporation | Système de gestion thermique pour turbine à gaz |
EP2841753A4 (fr) * | 2012-04-24 | 2016-10-19 | United Technologies Corp | Système de gestion thermique pour turbine à gaz |
FR3086323A1 (fr) | 2018-09-24 | 2020-03-27 | Safran Aircraft Engines | Carter interne de turmomachine a isolation thermique amelioree |
WO2020065178A1 (fr) | 2018-09-24 | 2020-04-02 | Safran Aircraft Engines | Carter interne de turbomachine à isolation thermique améliorée |
US11566538B2 (en) | 2018-09-24 | 2023-01-31 | Safran Aircraft Engines | Internal turbomachine casing having improved thermal insulation |
Also Published As
Publication number | Publication date |
---|---|
JP4124552B2 (ja) | 2008-07-23 |
JP2001012396A (ja) | 2001-01-16 |
FR2794816B1 (fr) | 2001-07-06 |
FR2794816A1 (fr) | 2000-12-15 |
US6390771B1 (en) | 2002-05-21 |
DE60016505T2 (de) | 2005-11-03 |
EP1059420B1 (fr) | 2004-12-08 |
DE60016505D1 (de) | 2005-01-13 |
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