JP2010526274A5 - - Google Patents
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- Publication number
- JP2010526274A5 JP2010526274A5 JP2010506353A JP2010506353A JP2010526274A5 JP 2010526274 A5 JP2010526274 A5 JP 2010526274A5 JP 2010506353 A JP2010506353 A JP 2010506353A JP 2010506353 A JP2010506353 A JP 2010506353A JP 2010526274 A5 JP2010526274 A5 JP 2010526274A5
- Authority
- JP
- Japan
- Prior art keywords
- diameter
- liner
- combustor
- cooling
- combustor liner
- 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
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/743,126 US20080271457A1 (en) | 2007-05-01 | 2007-05-01 | Cooling Holes For Gas Turbine Combustor Having A Non-Uniform Diameter Therethrough |
| PCT/US2008/055758 WO2008137201A1 (en) | 2007-05-01 | 2008-03-04 | Cooling holes for gas turbine combustor liner having a non-uniform diameter therethrough |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2010526274A JP2010526274A (ja) | 2010-07-29 |
| JP2010526274A5 true JP2010526274A5 (zh) | 2011-04-21 |
Family
ID=39645559
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2010506353A Pending JP2010526274A (ja) | 2007-05-01 | 2008-03-04 | それを貫通した一様でない直径を有するガスタービン燃焼器ライナのための冷却孔 |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20080271457A1 (zh) |
| EP (1) | EP2153133A1 (zh) |
| JP (1) | JP2010526274A (zh) |
| CA (1) | CA2685342A1 (zh) |
| WO (1) | WO2008137201A1 (zh) |
Families Citing this family (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009007164A1 (de) | 2009-02-03 | 2010-08-12 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zum Ausbilden einer Kühlluftöffnung in einer Wand einer Gasturbinenbrennkammer sowie nach dem Verfahren hergestellte Brennkammerwand |
| US8307657B2 (en) * | 2009-03-10 | 2012-11-13 | General Electric Company | Combustor liner cooling system |
| US20100263384A1 (en) * | 2009-04-17 | 2010-10-21 | Ronald James Chila | Combustor cap with shaped effusion cooling holes |
| US8371814B2 (en) * | 2009-06-24 | 2013-02-12 | Honeywell International Inc. | Turbine engine components |
| US8529193B2 (en) * | 2009-11-25 | 2013-09-10 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
| US8628293B2 (en) | 2010-06-17 | 2014-01-14 | Honeywell International Inc. | Gas turbine engine components with cooling hole trenches |
| US9052113B1 (en) | 2011-06-06 | 2015-06-09 | General Electric Company | Combustor nozzle and method for modifying the combustor nozzle |
| US9650900B2 (en) | 2012-05-07 | 2017-05-16 | Honeywell International Inc. | Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations |
| US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
| US9194585B2 (en) | 2012-10-04 | 2015-11-24 | United Technologies Corporation | Cooling for combustor liners with accelerating channels |
| US9309809B2 (en) * | 2013-01-23 | 2016-04-12 | General Electric Company | Effusion plate using additive manufacturing methods |
| WO2014126619A1 (en) * | 2013-02-14 | 2014-08-21 | United Technologies Corporation | Combustor liners with u-shaped cooling channels |
| EP2969525A4 (en) * | 2013-03-15 | 2016-11-16 | Harvard College | PORENARIA AUXETIC FILM |
| EP3039346B1 (en) * | 2013-08-30 | 2022-09-14 | Raytheon Technologies Corporation | Contoured dilution passages for a gas turbine engine combustor |
| EP3066388B1 (en) * | 2013-11-04 | 2024-04-10 | RTX Corporation | Turbine engine combustor heat shield with multi-angled cooling apertures |
| US10190773B2 (en) * | 2013-11-05 | 2019-01-29 | United Technologies Corporation | Attachment stud on a combustor floatwall panel with internal cooling holes |
| US10359194B2 (en) * | 2014-08-26 | 2019-07-23 | Siemens Energy, Inc. | Film cooling hole arrangement for acoustic resonators in gas turbine engines |
| GB201419327D0 (en) | 2014-10-30 | 2014-12-17 | Rolls Royce Plc | A cooled component |
| US20160258623A1 (en) * | 2015-03-05 | 2016-09-08 | United Technologies Corporation | Combustor and heat shield configurations for a gas turbine engine |
| US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
| US20180266687A1 (en) * | 2017-03-16 | 2018-09-20 | General Electric Company | Reducing film scrubbing in a combustor |
| US11149948B2 (en) * | 2017-08-21 | 2021-10-19 | General Electric Company | Fuel nozzle with angled main injection ports and radial main injection ports |
| 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 |
| US11009230B2 (en) | 2018-02-06 | 2021-05-18 | Raytheon Technologies Corporation | Undercut combustor panel rail |
| 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 |
| US11306659B2 (en) | 2019-05-28 | 2022-04-19 | Honeywell International Inc. | Plug resistant effusion holes for gas turbine engine |
| US11371701B1 (en) | 2021-02-03 | 2022-06-28 | General Electric Company | Combustor for a gas turbine engine |
| US11774098B2 (en) | 2021-06-07 | 2023-10-03 | General Electric Company | Combustor for a gas turbine engine |
| US11959643B2 (en) | 2021-06-07 | 2024-04-16 | General Electric Company | Combustor for a gas turbine engine |
| US11885495B2 (en) | 2021-06-07 | 2024-01-30 | General Electric Company | Combustor for a gas turbine engine including a liner having a looped feature |
| CN115493163B (zh) * | 2022-09-06 | 2024-02-20 | 清华大学 | 燃烧室火焰筒及燃烧室火焰筒高效冷却方法 |
Family Cites Families (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2221979B (en) * | 1988-08-17 | 1992-03-25 | Rolls Royce Plc | A combustion chamber for a gas turbine engine |
| US5660525A (en) * | 1992-10-29 | 1997-08-26 | General Electric Company | Film cooled slotted wall |
| US5528904A (en) * | 1994-02-28 | 1996-06-25 | Jones; Charles R. | Coated hot gas duct liner |
| JPH09119322A (ja) * | 1995-10-27 | 1997-05-06 | Ishikawajima Harima Heavy Ind Co Ltd | 航空機エンジンの冷却ライナ |
| US6383602B1 (en) * | 1996-12-23 | 2002-05-07 | General Electric Company | Method for improving the cooling effectiveness of a gaseous coolant stream which flows through a substrate, and related articles of manufacture |
| EP0945593B1 (de) * | 1998-03-23 | 2003-05-07 | ALSTOM (Switzerland) Ltd | Filmkühlungsbohrung |
| CA2288557C (en) * | 1998-11-12 | 2007-02-06 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor cooling structure |
| US6408629B1 (en) * | 2000-10-03 | 2002-06-25 | General Electric Company | Combustor liner having preferentially angled cooling holes |
| US7093439B2 (en) * | 2002-05-16 | 2006-08-22 | United Technologies Corporation | Heat shield panels for use in a combustor for a gas turbine engine |
| US7328580B2 (en) * | 2004-06-23 | 2008-02-12 | General Electric Company | Chevron film cooled wall |
| JP4898253B2 (ja) * | 2005-03-30 | 2012-03-14 | 三菱重工業株式会社 | ガスタービン用高温部材 |
| EP1712739A1 (de) * | 2005-04-12 | 2006-10-18 | Siemens Aktiengesellschaft | Bauteil mit Filmkühlloch |
-
2007
- 2007-05-01 US US11/743,126 patent/US20080271457A1/en not_active Abandoned
-
2008
- 2008-03-04 CA CA002685342A patent/CA2685342A1/en not_active Abandoned
- 2008-03-04 JP JP2010506353A patent/JP2010526274A/ja active Pending
- 2008-03-04 EP EP08731322A patent/EP2153133A1/en not_active Withdrawn
- 2008-03-04 WO PCT/US2008/055758 patent/WO2008137201A1/en active Application Filing
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