WO1996008679B1 - Hybrid combustor - Google Patents
Hybrid combustorInfo
- Publication number
- WO1996008679B1 WO1996008679B1 PCT/US1995/011583 US9511583W WO9608679B1 WO 1996008679 B1 WO1996008679 B1 WO 1996008679B1 US 9511583 W US9511583 W US 9511583W WO 9608679 B1 WO9608679 B1 WO 9608679B1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- combustor
- combustors
- annular
- set forth
- fuel
- Prior art date
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract 12
- 239000000919 ceramic Substances 0.000 claims abstract 9
- 239000000446 fuel Substances 0.000 claims abstract 8
- 239000002184 metal Substances 0.000 claims abstract 7
- 239000011153 ceramic matrix composite Substances 0.000 claims 1
- 230000001939 inductive effect Effects 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 238000007789 sealing Methods 0.000 claims 1
- 230000008646 thermal stress Effects 0.000 claims 1
Abstract
A hybrid combustor (10) of a gas turbine engine includes a plurality of circularly arrayed ceramic can combustors (12) whose outlets communicate with the inlet of an annular, metal combustor (16). The combustion process is continuous through the plurality of can combustors (12) and into the single annular combustor (16). Preferably only fuel-rich combustion occurs within each of the can combustors (12), and fuel-lean combustion continues within the single annular combustor (16).
Claims
1. A gas turbine engine combustor comprising:
an annular casing having a pressurized air inlet, an exhaust, and a fuel supply duct;
a plurality of thin wall, ceramic, can combustors in said casing receiving air from said inlet and fuel from said fuel duct to establish combustion within said can combustors, each of said can combustors including a continuous, non-perforated, cylindrical ceramic wall; and
a metallic, annular combustor between said can combustors and said exhaust, said annular combustor receiving air from said inlet and combustion products from said can combustors to continue said combustion within said annular combustor,
said can combustors and said annular combustor relatively arranged and configured whereby substantially only fuel-rich combustion occurs in each of said can combustors and substantially only fuel-lean combustion occurs in said annular combustor, and whereby the flame front of said fuel rich combustion in each of said can combustors extends into said annular combustor such that said fuel-lean combustion in said annular combustor is a continuation of said fuel-rich combustion.
2. A combustor as set forth in Claim 1, wherein said can combustors are distributed in a circular array about said annular combustor.
3. A combustor as set forth in Claim 2, wherein said can combustors are equally spaced about said annular combustor.
4. A combustor as set forth in Claim 1, wherein said air and said combustion products flow through said can combustors and said annular combustor primarily parallel to the central axis of said annular combustor.
5. A combustor as set forth in Claim 1, wherein each of said can combustors includes an outer, cylindrical, metal liner surrounding said ceramic wall
6. A combustor as set forth in Claim 5, wherein each of said outer metal liners is spaced outwardly from the associated ceramic wall to define an annular air passage extending from said inlet to said annular combustor.
7. A combustor as set forth in Claim 6, further including a fuel nozzle at the inlet end of each of said can combustors, and a metallic grommet between each of said nozzles and the associated outer metal liner for sealing therebetween.
8. A combustor as set forth in Claim 5, wherein said inlet end of said annular combustor includes openings for receiving each of said can combustors.
9. A combustor as set forth in Claim 8, wherein said outer metal liner of each of said can combustors is rigidly secured to said annular combustor.
10. A combustor as set forth in Claim 9, further including supports extending across said annular air space to said outer metal liner for supporting said ceramic wall of each of said can combustors while permitting differential thermal expansion between said metal liner and ceramic wall without inducing thermal stresses on said ceramic wall.
11. A combustor as set forth in Claim 1, wherein said ceramic walls of said can combustors are comprised of a ceramic matrix composite material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP95933085A EP0781392A1 (en) | 1994-09-14 | 1995-09-13 | Hybrid combustor |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US08/306,090 | 1994-09-14 | ||
| US08/306,090 US6182451B1 (en) | 1994-09-14 | 1994-09-14 | Gas turbine combustor waving ceramic combustor cans and an annular metallic combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| WO1996008679A1 WO1996008679A1 (en) | 1996-03-21 |
| WO1996008679B1 true WO1996008679B1 (en) | 1996-05-09 |
Family
ID=23183759
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US1995/011583 WO1996008679A1 (en) | 1994-09-14 | 1995-09-13 | Hybrid combustor |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US6182451B1 (en) |
| EP (1) | EP0781392A1 (en) |
| WO (1) | WO1996008679A1 (en) |
Families Citing this family (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020157400A1 (en) * | 2001-04-27 | 2002-10-31 | Siemens Aktiengesellschaft | Gas turbine with combined can-type and annular combustor and method of operating a gas turbine |
| FR2825787B1 (en) * | 2001-06-06 | 2004-08-27 | Snecma Moteurs | FITTING OF CMC COMBUSTION CHAMBER OF TURBOMACHINE BY FLEXIBLE LINKS |
| FR2825784B1 (en) * | 2001-06-06 | 2003-08-29 | Snecma Moteurs | HANGING THE TURBOMACHINE CMC COMBUSTION CHAMBER USING THE DILUTION HOLES |
| EP1288574A1 (en) * | 2001-09-03 | 2003-03-05 | Siemens Aktiengesellschaft | Combustion chamber arrangement |
| US6495207B1 (en) | 2001-12-21 | 2002-12-17 | Pratt & Whitney Canada Corp. | Method of manufacturing a composite wall |
| EP1508761A1 (en) * | 2003-08-22 | 2005-02-23 | Siemens Aktiengesellschaft | Thermal shielding brick for lining a combustion chamber wall, combustion chamber and a gas turbine |
| US7043921B2 (en) * | 2003-08-26 | 2006-05-16 | Honeywell International, Inc. | Tube cooled combustor |
| US7093441B2 (en) * | 2003-10-09 | 2006-08-22 | United Technologies Corporation | Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume |
| US20050210862A1 (en) * | 2004-03-25 | 2005-09-29 | Paterro Von Friedrich C | Quantum jet turbine propulsion system |
| US7954325B2 (en) * | 2005-12-06 | 2011-06-07 | United Technologies Corporation | Gas turbine combustor |
| US7665307B2 (en) * | 2005-12-22 | 2010-02-23 | United Technologies Corporation | Dual wall combustor liner |
| US8863528B2 (en) * | 2006-07-27 | 2014-10-21 | United Technologies Corporation | Ceramic combustor can for a gas turbine engine |
| US9127565B2 (en) * | 2008-04-16 | 2015-09-08 | Siemens Energy, Inc. | Apparatus comprising a CMC-comprising body and compliant porous element preloaded within an outer metal shell |
| EP2233835A1 (en) * | 2009-03-23 | 2010-09-29 | Siemens Aktiengesellschaft | Combustion chamber brazed with ceramic inserts |
| US8745989B2 (en) | 2009-04-09 | 2014-06-10 | Pratt & Whitney Canada Corp. | Reverse flow ceramic matrix composite combustor |
| US8739546B2 (en) * | 2009-08-31 | 2014-06-03 | United Technologies Corporation | Gas turbine combustor with quench wake control |
| US8443610B2 (en) | 2009-11-25 | 2013-05-21 | United Technologies Corporation | Low emission gas turbine combustor |
| US9068751B2 (en) * | 2010-01-29 | 2015-06-30 | United Technologies Corporation | Gas turbine combustor with staged combustion |
| US8966877B2 (en) | 2010-01-29 | 2015-03-03 | United Technologies Corporation | Gas turbine combustor with variable airflow |
| US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
| US9958162B2 (en) | 2011-01-24 | 2018-05-01 | United Technologies Corporation | Combustor assembly for a turbine engine |
| US9068748B2 (en) | 2011-01-24 | 2015-06-30 | United Technologies Corporation | Axial stage combustor for gas turbine engines |
| US8601820B2 (en) | 2011-06-06 | 2013-12-10 | General Electric Company | Integrated late lean injection on a combustion liner and late lean injection sleeve assembly |
| US9010120B2 (en) | 2011-08-05 | 2015-04-21 | General Electric Company | Assemblies and apparatus related to integrating late lean injection into combustion turbine engines |
| US8919137B2 (en) | 2011-08-05 | 2014-12-30 | General Electric Company | Assemblies and apparatus related to integrating late lean injection into combustion turbine engines |
| US9140455B2 (en) | 2012-01-04 | 2015-09-22 | General Electric Company | Flowsleeve of a turbomachine component |
| US9134028B2 (en) * | 2012-01-18 | 2015-09-15 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
| EP3015770B1 (en) * | 2014-11-03 | 2020-07-01 | Ansaldo Energia Switzerland AG | Can combustion chamber |
| US9810434B2 (en) * | 2016-01-21 | 2017-11-07 | Siemens Energy, Inc. | Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US534313A (en) * | 1895-02-19 | connors | ||
| GB588572A (en) * | 1944-11-28 | 1947-05-28 | William Henry Darlington | Improvements in combustion chambers for internal combustion turbines |
| US2447482A (en) | 1945-04-25 | 1948-08-24 | Westinghouse Electric Corp | Turbine apparatus |
| US2446013A (en) | 1945-05-31 | 1948-07-27 | Gen Electric | Combustion chamber drain arrangement |
| US2885858A (en) * | 1947-12-02 | 1959-05-12 | Power Jets Res & Dev Ltd | Combustion system with mixing chamber |
| US2676460A (en) * | 1950-03-23 | 1954-04-27 | United Aircraft Corp | Burner construction of the can-an-nular type having means for distributing airflow to each can |
| SU151158A1 (en) * | 1961-04-21 | 1961-11-30 | тский З.М. Св | Combustion chamber |
| GB1240009A (en) * | 1968-07-27 | 1971-07-21 | Leyland Gas Turbines Ltd | Flame tube |
| US3938326A (en) | 1974-06-25 | 1976-02-17 | Westinghouse Electric Corporation | Catalytic combustor having a variable temperature profile |
| US3990231A (en) | 1974-10-24 | 1976-11-09 | General Motors Corporation | Interconnections between ceramic rings permitting relative radial movement |
| EP0193029B1 (en) * | 1985-02-26 | 1988-11-17 | BBC Brown Boveri AG | Gas turbine combustor |
| DE3519938A1 (en) * | 1985-06-04 | 1986-12-04 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | COMBUSTION CHAMBER |
| DE3615226A1 (en) * | 1986-05-06 | 1987-11-12 | Mtu Muenchen Gmbh | HOT GAS OVERHEATING PROTECTION DEVICE FOR GAS TURBINE ENGINES |
| US5285632A (en) * | 1993-02-08 | 1994-02-15 | General Electric Company | Low NOx combustor |
-
1994
- 1994-09-14 US US08/306,090 patent/US6182451B1/en not_active Expired - Fee Related
-
1995
- 1995-09-13 EP EP95933085A patent/EP0781392A1/en not_active Withdrawn
- 1995-09-13 WO PCT/US1995/011583 patent/WO1996008679A1/en not_active Application Discontinuation
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