FR2946413B1 - Chambre de combustion de moteur a turbine a gaz avec element de paroi multi-perfore - Google Patents
Chambre de combustion de moteur a turbine a gaz avec element de paroi multi-perforeInfo
- Publication number
- FR2946413B1 FR2946413B1 FR0953684A FR0953684A FR2946413B1 FR 2946413 B1 FR2946413 B1 FR 2946413B1 FR 0953684 A FR0953684 A FR 0953684A FR 0953684 A FR0953684 A FR 0953684A FR 2946413 B1 FR2946413 B1 FR 2946413B1
- Authority
- FR
- France
- Prior art keywords
- combustion chamber
- gas turbine
- turbine engine
- wall element
- engine combustion
- 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.)
- Active
Links
- 238000002485 combustion reaction Methods 0.000 title 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 title 1
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
- F23R3/002—Wall structures
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
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)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0953684A FR2946413B1 (fr) | 2009-06-04 | 2009-06-04 | Chambre de combustion de moteur a turbine a gaz avec element de paroi multi-perfore |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0953684A FR2946413B1 (fr) | 2009-06-04 | 2009-06-04 | Chambre de combustion de moteur a turbine a gaz avec element de paroi multi-perfore |
Publications (2)
Publication Number | Publication Date |
---|---|
FR2946413A1 FR2946413A1 (fr) | 2010-12-10 |
FR2946413B1 true FR2946413B1 (fr) | 2011-07-15 |
Family
ID=41510493
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR0953684A Active FR2946413B1 (fr) | 2009-06-04 | 2009-06-04 | Chambre de combustion de moteur a turbine a gaz avec element de paroi multi-perfore |
Country Status (1)
Country | Link |
---|---|
FR (1) | FR2946413B1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB201412460D0 (en) | 2014-07-14 | 2014-08-27 | Rolls Royce Plc | An Annular Combustion Chamber Wall Arrangement |
FR3037107B1 (fr) * | 2015-06-03 | 2019-11-15 | Safran Aircraft Engines | Paroi annulaire de chambre de combustion a refroidissement optimise |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5233828A (en) * | 1990-11-15 | 1993-08-10 | General Electric Company | Combustor liner with circumferentially angled film cooling holes |
US5261223A (en) * | 1992-10-07 | 1993-11-16 | General Electric Company | Multi-hole film cooled combustor liner with rectangular film restarting holes |
US6640547B2 (en) * | 2001-12-10 | 2003-11-04 | Power Systems Mfg, Llc | Effusion cooled transition duct with shaped cooling holes |
-
2009
- 2009-06-04 FR FR0953684A patent/FR2946413B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
FR2946413A1 (fr) | 2010-12-10 |
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Legal Events
Date | Code | Title | Description |
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PLFP | Fee payment |
Year of fee payment: 7 |
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PLFP | Fee payment |
Year of fee payment: 8 |
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Year of fee payment: 9 |
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PLFP | Fee payment |
Year of fee payment: 10 |
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CD | Change of name or company name |
Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
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PLFP | Fee payment |
Year of fee payment: 11 |
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Year of fee payment: 12 |
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Year of fee payment: 16 |