EP2340397A1 - Burner inserts for a gas turbine combustion chamber and gas turbine - Google Patents
Burner inserts for a gas turbine combustion chamber and gas turbineInfo
- Publication number
- EP2340397A1 EP2340397A1 EP09823099A EP09823099A EP2340397A1 EP 2340397 A1 EP2340397 A1 EP 2340397A1 EP 09823099 A EP09823099 A EP 09823099A EP 09823099 A EP09823099 A EP 09823099A EP 2340397 A1 EP2340397 A1 EP 2340397A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- burner
- wall
- gas turbine
- burner insert
- 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
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 92
- 239000012809 cooling fluid Substances 0.000 claims description 6
- 239000007789 gas Substances 0.000 description 42
- 238000001816 cooling Methods 0.000 description 34
- 239000000567 combustion gas Substances 0.000 description 4
- 239000003344 environmental pollutant Substances 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 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
- F23R3/10—Air inlet arrangements for primary air
-
- 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
- F23R2900/03042—Film cooled combustion chamber walls or domes
Definitions
- the present invention relates to a combustor liner for a gas turbine combustor having a burner port for inserting a combustor.
- the invention relates to a gas turbine.
- annular combustion chambers that is to say of combustion chambers which extend annularly around the turbine rotor
- a multiplicity of combustion inserts are generally arranged next to one another in the circumferential direction of the annular combustion chamber.
- the cooling air flowing past the cold side of the burner side then flows into the combustion chamber between the radially outer wall and the radially inner wall of the combustion chamber.
- cooling air can also be introduced into the combustion chamber by gaps between circumferentially adjacent combustion inserts.
- Such an annular combustion chamber is described, for example, in EP 1 557 607 A1.
- a burner insert is shown in Figure 4 in a partially cutaway perspective view. It comprises a burner insert wall 42 with a cold side 43 and a hot side 44, which is to be turned to the combustion chamber interior (the hot side can not be seen in FIG. 4).
- the cold side 43 communicates with the outlet of the compressor in fluid communication so that compressor air can be bypassed for cooling purposes on the cold side 43 to the temperature of the hot side on one for the material of the burner insert 41 acceptable level.
- the hot side is also provided with a heat-insulating coating, for example in the form of a ceramic coating, in order to reduce the need for cooling air.
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)
- Gas Burners (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09823099.8A EP2340397B1 (en) | 2008-10-29 | 2009-09-14 | Burner insert for a gas turbine combustion chamber and gas turbine |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP08018907A EP2182285A1 (en) | 2008-10-29 | 2008-10-29 | Burner insert for a gas turbine combustion chamber and gas turbine |
EP09823099.8A EP2340397B1 (en) | 2008-10-29 | 2009-09-14 | Burner insert for a gas turbine combustion chamber and gas turbine |
PCT/EP2009/061854 WO2010049206A1 (en) | 2008-10-29 | 2009-09-14 | Burner inserts for a gas turbine combustion chamber and gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2340397A1 true EP2340397A1 (en) | 2011-07-06 |
EP2340397B1 EP2340397B1 (en) | 2013-07-31 |
Family
ID=40672584
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08018907A Withdrawn EP2182285A1 (en) | 2008-10-29 | 2008-10-29 | Burner insert for a gas turbine combustion chamber and gas turbine |
EP09823099.8A Active EP2340397B1 (en) | 2008-10-29 | 2009-09-14 | Burner insert for a gas turbine combustion chamber and gas turbine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08018907A Withdrawn EP2182285A1 (en) | 2008-10-29 | 2008-10-29 | Burner insert for a gas turbine combustion chamber and gas turbine |
Country Status (7)
Country | Link |
---|---|
US (1) | US9074771B2 (en) |
EP (2) | EP2182285A1 (en) |
JP (1) | JP5349605B2 (en) |
CN (1) | CN102203509B (en) |
ES (1) | ES2426395T3 (en) |
RU (1) | RU2530684C2 (en) |
WO (1) | WO2010049206A1 (en) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102012204103A1 (en) * | 2012-03-15 | 2013-09-19 | Siemens Aktiengesellschaft | Heat shield element for a compressor air bypass around the combustion chamber |
US9322560B2 (en) * | 2012-09-28 | 2016-04-26 | United Technologies Corporation | Combustor bulkhead assembly |
US20150033746A1 (en) * | 2013-08-02 | 2015-02-05 | Solar Turbines Incorporated | Heat shield with standoffs |
US9534786B2 (en) * | 2014-08-08 | 2017-01-03 | Pratt & Whitney Canada Corp. | Combustor heat shield |
US10267521B2 (en) | 2015-04-13 | 2019-04-23 | Pratt & Whitney Canada Corp. | Combustor heat shield |
DE102016206188A1 (en) * | 2016-04-13 | 2017-10-19 | Rolls-Royce Deutschland Ltd & Co Kg | Combustor shingle of a gas turbine |
DE102016224632A1 (en) * | 2016-12-09 | 2018-06-14 | Rolls-Royce Deutschland Ltd & Co Kg | Plate-shaped component of a gas turbine and method for its production |
US11009230B2 (en) | 2018-02-06 | 2021-05-18 | Raytheon Technologies Corporation | Undercut combustor panel rail |
US11248791B2 (en) | 2018-02-06 | 2022-02-15 | Raytheon Technologies Corporation | Pull-plane effusion combustor panel |
US10830435B2 (en) | 2018-02-06 | 2020-11-10 | Raytheon Technologies Corporation | Diffusing hole for rail effusion |
US11022307B2 (en) | 2018-02-22 | 2021-06-01 | Raytheon Technology Corporation | Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling |
US20190285276A1 (en) * | 2018-03-14 | 2019-09-19 | United Technologies Corporation | Castellated combustor panels |
DE102018212394B4 (en) | 2018-07-25 | 2024-03-28 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber assembly with a wall element having a flow guide device |
US11015807B2 (en) * | 2019-01-30 | 2021-05-25 | Pratt & Whitney Canada Corp. | Combustor heat shield cooling |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2107448B (en) * | 1980-10-21 | 1984-06-06 | Rolls Royce | Gas turbine engine combustion chambers |
US4914918A (en) * | 1988-09-26 | 1990-04-10 | United Technologies Corporation | Combustor segmented deflector |
GB9018014D0 (en) * | 1990-08-16 | 1990-10-03 | Rolls Royce Plc | Gas turbine engine combustor |
GB2287310B (en) * | 1994-03-01 | 1997-12-03 | Rolls Royce Plc | Gas turbine engine combustor heatshield |
US5419115A (en) * | 1994-04-29 | 1995-05-30 | United Technologies Corporation | Bulkhead and fuel nozzle guide assembly for an annular combustion chamber |
DE4427222A1 (en) * | 1994-08-01 | 1996-02-08 | Bmw Rolls Royce Gmbh | Heat shield for a gas turbine combustor |
US6032457A (en) * | 1996-06-27 | 2000-03-07 | United Technologies Corporation | Fuel nozzle guide |
US5974805A (en) * | 1997-10-28 | 1999-11-02 | Rolls-Royce Plc | Heat shielding for a turbine combustor |
US6164074A (en) * | 1997-12-12 | 2000-12-26 | United Technologies Corporation | Combustor bulkhead with improved cooling and air recirculation zone |
US6751961B2 (en) * | 2002-05-14 | 2004-06-22 | United Technologies Corporation | Bulkhead panel for use in a combustion chamber of a gas turbine engine |
US6792757B2 (en) * | 2002-11-05 | 2004-09-21 | Honeywell International Inc. | Gas turbine combustor heat shield impingement cooling baffle |
RU31818U1 (en) * | 2002-11-21 | 2003-08-27 | ОАО Самарский научно-технический комплекс им. Н.Д. Кузнецова | NK-37 gas turbine engine, compressor, combustion chamber, turbine |
US7080515B2 (en) | 2002-12-23 | 2006-07-25 | Siemens Westinghouse Power Corporation | Gas turbine can annular combustor |
DE502004011695D1 (en) | 2004-01-21 | 2010-11-11 | Siemens Ag | Burner with cooled component, gas turbine and method for cooling the component |
RU52982U1 (en) * | 2005-08-03 | 2006-04-27 | ЭКОЛ спол. с.р.о. | BURNER FOR LOW EMISSIONS OF HARMFUL SUBSTANCES AND BURNER SYSTEM |
EP1767855A1 (en) | 2005-09-27 | 2007-03-28 | Siemens Aktiengesellschaft | Combustion Chamber and Gas Turbine Plant |
RU52992U1 (en) | 2005-10-24 | 2006-04-27 | Ираклий Отарович Чиквиладзе | RADIATOR OF THE INTERNAL COMBUSTION ENGINE OF THE RACING CAR |
US7665306B2 (en) * | 2007-06-22 | 2010-02-23 | Honeywell International Inc. | Heat shields for use in combustors |
-
2008
- 2008-10-29 EP EP08018907A patent/EP2182285A1/en not_active Withdrawn
-
2009
- 2009-09-14 RU RU2011121647/06A patent/RU2530684C2/en active
- 2009-09-14 CN CN200980142861.0A patent/CN102203509B/en active Active
- 2009-09-14 WO PCT/EP2009/061854 patent/WO2010049206A1/en active Application Filing
- 2009-09-14 US US13/126,239 patent/US9074771B2/en not_active Expired - Fee Related
- 2009-09-14 ES ES09823099T patent/ES2426395T3/en active Active
- 2009-09-14 JP JP2011533647A patent/JP5349605B2/en not_active Expired - Fee Related
- 2009-09-14 EP EP09823099.8A patent/EP2340397B1/en active Active
Non-Patent Citations (1)
Title |
---|
See references of WO2010049206A1 * |
Also Published As
Publication number | Publication date |
---|---|
US20110197590A1 (en) | 2011-08-18 |
CN102203509A (en) | 2011-09-28 |
EP2340397B1 (en) | 2013-07-31 |
RU2530684C2 (en) | 2014-10-10 |
US9074771B2 (en) | 2015-07-07 |
WO2010049206A1 (en) | 2010-05-06 |
ES2426395T3 (en) | 2013-10-23 |
JP5349605B2 (en) | 2013-11-20 |
RU2011121647A (en) | 2012-12-10 |
CN102203509B (en) | 2014-07-09 |
EP2182285A1 (en) | 2010-05-05 |
JP2012506991A (en) | 2012-03-22 |
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