FR2356000A1 - TURBOMACHINE COMBUSTION CHAMBER SUPPORT DEVICE - Google Patents
TURBOMACHINE COMBUSTION CHAMBER SUPPORT DEVICEInfo
- Publication number
- FR2356000A1 FR2356000A1 FR7708378A FR7708378A FR2356000A1 FR 2356000 A1 FR2356000 A1 FR 2356000A1 FR 7708378 A FR7708378 A FR 7708378A FR 7708378 A FR7708378 A FR 7708378A FR 2356000 A1 FR2356000 A1 FR 2356000A1
- Authority
- FR
- France
- Prior art keywords
- combustion chamber
- support device
- chamber support
- turbomachine combustion
- supporting structure
- 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.)
- Pending
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Dispositif permettant un jeu radial tout en maintenant une position axiale e fixe. Il comprend un support 31 reliant la chambre de combustion 13 à une structure porteuse 21 et qui se compose d'au moins deux branches assemblées sous un certain angle pour permettre des déplacements relatifs, causés par la dilatation thermique, entre la chambre de combustion et la structure porteuse. Application aux moteurs à turbine à gaz.Device allowing radial play while maintaining a fixed axial position. It comprises a support 31 connecting the combustion chamber 13 to a supporting structure 21 and which consists of at least two branches assembled at a certain angle to allow relative displacements, caused by thermal expansion, between the combustion chamber and the supporting structure. Application to gas turbine engines.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US69828376A | 1976-06-21 | 1976-06-21 |
Publications (1)
Publication Number | Publication Date |
---|---|
FR2356000A1 true FR2356000A1 (en) | 1978-01-20 |
Family
ID=24804624
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR7708378A Pending FR2356000A1 (en) | 1976-06-21 | 1977-03-21 | TURBOMACHINE COMBUSTION CHAMBER SUPPORT DEVICE |
Country Status (4)
Country | Link |
---|---|
JP (1) | JPS52156213A (en) |
DE (1) | DE2711564A1 (en) |
FR (1) | FR2356000A1 (en) |
GB (1) | GB1578474A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2523646A1 (en) * | 1982-03-20 | 1983-09-23 | Rolls Royce | COMBUSTION EQUIPMENT SUPPORT DEVICE FOR GAS TURBINE ENGINE |
FR2825782A1 (en) * | 2001-06-06 | 2002-12-13 | Snecma Moteurs | Turbine with metal casing has composition combustion chamber fitted with sliding coupling to allow for differences in expansion coefficients |
FR2869094A1 (en) * | 2004-04-15 | 2005-10-21 | Snecma Moteurs Sa | ANNULAR COMBUSTION CHAMBER OF INTERNAL FLANGE TURBOMACHINE WITH IMPROVED FASTENING |
FR2890156A1 (en) * | 2005-08-31 | 2007-03-02 | Snecma | Turbomachine e.g. aircraft turbojet, combustion chamber, has internal and external flanges with orifices of triangular shape, where successive triangular orifices are arranged in staggered and head-to-tail configuration |
FR2944090A1 (en) * | 2009-04-07 | 2010-10-08 | Snecma | TURBOMACHINE WITH ANNULAR COMBUSTION CHAMBER |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5619340U (en) * | 1979-07-25 | 1981-02-20 | ||
DE19745683A1 (en) * | 1997-10-16 | 1999-04-22 | Bmw Rolls Royce Gmbh | Suspension of an annular gas turbine combustion chamber |
US6672833B2 (en) * | 2001-12-18 | 2004-01-06 | General Electric Company | Gas turbine engine frame flowpath liner support |
US6931855B2 (en) | 2003-05-12 | 2005-08-23 | Siemens Westinghouse Power Corporation | Attachment system for coupling combustor liners to a carrier of a turbine combustor |
EP1741877A1 (en) * | 2005-07-04 | 2007-01-10 | Siemens Aktiengesellschaft | Heat shield and stator vane for a gas turbine |
FR2892181B1 (en) | 2005-10-18 | 2008-02-01 | Snecma Sa | FIXING A COMBUSTION CHAMBER WITHIN ITS CARTER |
US8141370B2 (en) | 2006-08-08 | 2012-03-27 | General Electric Company | Methods and apparatus for radially compliant component mounting |
EP3078914A1 (en) * | 2015-04-09 | 2016-10-12 | Siemens Aktiengesellschaft | Annular combustor for a gas turbine engine |
RU2715634C2 (en) * | 2016-11-21 | 2020-03-02 | Дженерал Электрик Текнолоджи Гмбх | Device and method for forced cooling of gas turbine plant components |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2447482A (en) * | 1945-04-25 | 1948-08-24 | Westinghouse Electric Corp | Turbine apparatus |
FR941475A (en) * | 1946-02-12 | 1949-01-12 | Lucas Ltd Joseph | Combustion chamber for engines |
GB620270A (en) * | 1945-11-20 | 1949-03-22 | Westinghouse Electric Int Co | Improvements in or relating to turbine apparatus |
GB698539A (en) * | 1951-08-23 | 1953-10-14 | Svenska Turbinfab Ab | Expansible connecting element |
US2795108A (en) * | 1953-10-07 | 1957-06-11 | Westinghouse Electric Corp | Combustion apparatus |
FR1368570A (en) * | 1962-09-11 | 1964-07-31 | Lucas Industries Ltd | Support of the downstream end of the combustion chamber of a gas turbo-engine |
FR2246733A1 (en) * | 1973-10-05 | 1975-05-02 | Rolls Royce | |
FR2283321A1 (en) * | 1974-08-29 | 1976-03-26 | United Technologies Corp | COMBUSTION CHAMBER HAVING PREMIX TUBES STAGE |
-
1977
- 1977-03-07 GB GB955377A patent/GB1578474A/en not_active Expired
- 1977-03-17 DE DE19772711564 patent/DE2711564A1/en not_active Withdrawn
- 1977-03-18 JP JP2936877A patent/JPS52156213A/en active Pending
- 1977-03-21 FR FR7708378A patent/FR2356000A1/en active Pending
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2447482A (en) * | 1945-04-25 | 1948-08-24 | Westinghouse Electric Corp | Turbine apparatus |
GB620270A (en) * | 1945-11-20 | 1949-03-22 | Westinghouse Electric Int Co | Improvements in or relating to turbine apparatus |
FR941475A (en) * | 1946-02-12 | 1949-01-12 | Lucas Ltd Joseph | Combustion chamber for engines |
GB698539A (en) * | 1951-08-23 | 1953-10-14 | Svenska Turbinfab Ab | Expansible connecting element |
US2795108A (en) * | 1953-10-07 | 1957-06-11 | Westinghouse Electric Corp | Combustion apparatus |
FR1368570A (en) * | 1962-09-11 | 1964-07-31 | Lucas Industries Ltd | Support of the downstream end of the combustion chamber of a gas turbo-engine |
FR2246733A1 (en) * | 1973-10-05 | 1975-05-02 | Rolls Royce | |
FR2283321A1 (en) * | 1974-08-29 | 1976-03-26 | United Technologies Corp | COMBUSTION CHAMBER HAVING PREMIX TUBES STAGE |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2523646A1 (en) * | 1982-03-20 | 1983-09-23 | Rolls Royce | COMBUSTION EQUIPMENT SUPPORT DEVICE FOR GAS TURBINE ENGINE |
FR2825782A1 (en) * | 2001-06-06 | 2002-12-13 | Snecma Moteurs | Turbine with metal casing has composition combustion chamber fitted with sliding coupling to allow for differences in expansion coefficients |
FR2869094A1 (en) * | 2004-04-15 | 2005-10-21 | Snecma Moteurs Sa | ANNULAR COMBUSTION CHAMBER OF INTERNAL FLANGE TURBOMACHINE WITH IMPROVED FASTENING |
EP1593913A1 (en) * | 2004-04-15 | 2005-11-09 | Snecma | Gas turbine annular combustion chamber with improved inner support flange |
US7412834B2 (en) | 2004-04-15 | 2008-08-19 | Snecma | Annular combustion chamber for a turbomachine with an improved inner fastening flange |
FR2890156A1 (en) * | 2005-08-31 | 2007-03-02 | Snecma | Turbomachine e.g. aircraft turbojet, combustion chamber, has internal and external flanges with orifices of triangular shape, where successive triangular orifices are arranged in staggered and head-to-tail configuration |
EP1760404A1 (en) * | 2005-08-31 | 2007-03-07 | Snecma | Combustion chamber of a gas turbine |
US7568350B2 (en) | 2005-08-31 | 2009-08-04 | Snecma | Combustion chamber for a turbomachine |
FR2944090A1 (en) * | 2009-04-07 | 2010-10-08 | Snecma | TURBOMACHINE WITH ANNULAR COMBUSTION CHAMBER |
WO2010116051A3 (en) * | 2009-04-07 | 2011-05-19 | Snecma | Turbine engine with an annular combustion chamber |
Also Published As
Publication number | Publication date |
---|---|
GB1578474A (en) | 1980-11-05 |
JPS52156213A (en) | 1977-12-26 |
DE2711564A1 (en) | 1977-12-29 |
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