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
Claims (15)
(a)前記燃焼器の上流端部に隣接した第1の端部及び該燃焼器の下流端部に隣接した第2の端部を有しかつ高温側面、低温側面及びそれを貫通する中心軸線をさらに有するシェルと、
(b)前記シェル内に形成されかつそれらを通して空気が流れて該シェルの高温側面に沿って冷却フィルムを形成するようになった複数の小径かつ密に間隔を置いて配置されたフィルム冷却孔と、を含み、
前記冷却孔が、前記シェルを貫通する一様でない直径を有する、
燃焼器ライナ。 A liner for a gas turbine combustor,
(A) a first end adjacent to the upstream end of the combustor and a second end adjacent to the downstream end of the combustor, and a hot side, a cold side and a central axis passing therethrough A shell further comprising:
(B) a plurality of small diameter and closely spaced film cooling holes formed in the shell and through which air flows to form a cooling film along the hot side of the shell; Including,
The cooling holes have non-uniform diameters through the shell;
Combustor liner.
(a)前記シェルの低温側面に設置されかつ第1の直径を有する第1の開口と、
(b)前記シェルの高温側面に設置されかつ第2の直径を有する第2の開口と、をさらに含み、
前記第2の開口の第2の直径が、前記第1の開口の第1の直径よりも大きい、
請求項1記載の燃焼器ライナ。 Each of the cooling holes is
(A) a first opening installed on a cold side of the shell and having a first diameter;
(B) a second opening disposed on the hot side of the shell and having a second diameter;
A second diameter of the second opening is greater than a first diameter of the first opening;
The combustor liner of claim 1.
(a)その形状がほぼ円錐形でありかつ前記ライナをほぼ貫通して延びる前記冷却孔の第1の部分を該ライナの高温側面から形成するステップと、
(b)その直径がほぼ一様である前記冷却孔の第2の部分を該冷却孔の第1の部分から前記ライナの低温側面まで形成するステップと、を含む、
方法。 A method of forming a cooling hole having a non-uniform diameter therethrough in a liner of a gas turbine engine combustor, comprising:
(A) forming a first portion of the cooling hole having a generally conical shape and extending substantially through the liner from a hot side surface of the liner;
(B) forming a second portion of the cooling hole having a substantially uniform diameter from the first portion of the cooling hole to a cold side of the liner;
Method.
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 (en) | 2010-07-29 |
JP2010526274A5 true JP2010526274A5 (en) | 2011-04-21 |
Family
ID=39645559
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2010506353A Pending JP2010526274A (en) | 2007-05-01 | 2008-03-04 | Cooling holes for gas turbine combustor liners with non-uniform diameters therethrough |
Country Status (5)
Country | Link |
---|---|
US (1) | US20080271457A1 (en) |
EP (1) | EP2153133A1 (en) |
JP (1) | JP2010526274A (en) |
CA (1) | CA2685342A1 (en) |
WO (1) | WO2008137201A1 (en) |
Families Citing this family (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102009007164A1 (en) | 2009-02-03 | 2010-08-12 | Rolls-Royce Deutschland Ltd & Co Kg | A method of forming a cooling air opening in a wall of a gas turbine combustor and combustor wall made by the method |
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 |
US9194585B2 (en) * | 2012-10-04 | 2015-11-24 | United Technologies Corporation | Cooling for combustor liners with accelerating channels |
US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
US9309809B2 (en) * | 2013-01-23 | 2016-04-12 | General Electric Company | Effusion plate using additive manufacturing methods |
EP2956647B1 (en) * | 2013-02-14 | 2019-05-08 | United Technologies Corporation | Combustor liners with u-shaped cooling channels and method of cooling |
US20160025344A1 (en) | 2013-03-15 | 2016-01-28 | President And Fellows Of Harvard College | Low porosity auxetic sheet |
EP3039346B1 (en) * | 2013-08-30 | 2022-09-14 | Raytheon Technologies Corporation | Contoured dilution passages for a gas turbine engine combustor |
WO2015112221A2 (en) | 2013-11-04 | 2015-07-30 | United Technologies Corporation | Turbine engine combustor heat shield with multi-angled cooling apertures |
WO2015069466A1 (en) * | 2013-11-05 | 2015-05-14 | United Technologies Corporation | Cooled combustor floatwall panel |
JP6456481B2 (en) * | 2014-08-26 | 2019-01-23 | シーメンス エナジー インコーポレイテッド | Film cooling hole array for an acoustic resonator in a gas turbine engine |
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 |
US11009230B2 (en) | 2018-02-06 | 2021-05-18 | Raytheon Technologies Corporation | Undercut combustor panel rail |
US10830435B2 (en) | 2018-02-06 | 2020-11-10 | Raytheon Technologies Corporation | Diffusing hole for rail effusion |
US11248791B2 (en) | 2018-02-06 | 2022-02-15 | Raytheon Technologies Corporation | Pull-plane effusion combustor panel |
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 |
US11885495B2 (en) | 2021-06-07 | 2024-01-30 | General Electric Company | Combustor for a gas turbine engine including a liner having a looped feature |
US11959643B2 (en) | 2021-06-07 | 2024-04-16 | 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 |
CN115493163B (en) * | 2022-09-06 | 2024-02-20 | 清华大学 | Combustion chamber flame tube and high-efficiency cooling method thereof |
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 (en) * | 1995-10-27 | 1997-05-06 | Ishikawajima Harima Heavy Ind Co Ltd | Cooling liner of aircraft engine |
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 (en) * | 1998-03-23 | 2003-05-07 | ALSTOM (Switzerland) Ltd | Film-cooling hole |
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 (en) * | 2005-03-30 | 2012-03-14 | 三菱重工業株式会社 | High temperature components for gas turbines |
EP1712739A1 (en) * | 2005-04-12 | 2006-10-18 | Siemens Aktiengesellschaft | Component with film cooling hole |
-
2007
- 2007-05-01 US US11/743,126 patent/US20080271457A1/en not_active Abandoned
-
2008
- 2008-03-04 JP JP2010506353A patent/JP2010526274A/en active Pending
- 2008-03-04 CA CA002685342A patent/CA2685342A1/en not_active Abandoned
- 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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