KR100711057B1 - 연소터빈의 냉각방법 - Google Patents
연소터빈의 냉각방법 Download PDFInfo
- Publication number
- KR100711057B1 KR100711057B1 KR1020017008498A KR20017008498A KR100711057B1 KR 100711057 B1 KR100711057 B1 KR 100711057B1 KR 1020017008498 A KR1020017008498 A KR 1020017008498A KR 20017008498 A KR20017008498 A KR 20017008498A KR 100711057 B1 KR100711057 B1 KR 100711057B1
- Authority
- KR
- South Korea
- Prior art keywords
- cooling
- passage
- component
- fluid
- cooling passage
- Prior art date
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims (10)
- 고온의 연소가스(12)에 노출되어 있는 가스측 표면(14)을 가진 벽을 구비하고 있는 연소 터빈의 구성요소(10)를 냉각하는 방법으로서, 상기 벽으로부터 열을 제거하기 위하여 냉각유체의 흐름을 상기 벽으로 공급하는 단계를 포함하고 있는 상기 연소 터빈의 구성요소(10)를 냉각하는 방법에 있어서,입구(22)와 출구(24)를 갖추고 있고, 가스측 표면(14) 아래의 구성요소(10)의 상기 벽을 통과하는 제 1 표면아래 냉각 통로(20)를 형성하는 단계;제 1 표면아래 냉각 통로(20)의 입구(22)와 출구(24) 사이의 합류점(32)에서 제 1 표면아래 냉각 통로(20)와 유체연통가능하게 연결된 출구(30)와 입구(28)를 갖추고 있고, 가스측 표면(14) 아래의 구성요소(10)의 상기 벽을 통과하는 제 2 표면아래 냉각 통로(26)를 형성하는 단계;제 1 냉각유체의 제 1 유동을 제 1 표면아래 냉각 통로(20)의 입구(22)로 공급하는 단계;제 1 냉각유체를 합류점(32)에서 합류시키기 위하여 제 2 냉각유체의 제 2 유동을 제 2 표면아래 냉각 통로(26)의 입구(28)로 공급하는 단계; 그리고,제 1 냉각유체 및 제 2 냉각유체를 상기 벽을 통하여 제 1 표면아래 냉각 통로(20)의 출구(24)로 인도하는 단계;를 포함하는 것을 특징으로 하는 연소 터빈의 구성요소(10)를 냉각하는 방법.
- 제 1 항에 있어서, 상기 구성요소(10)는 제 1 부분 및 제 2 부분을 갖고 있고, 상기 제 1 부분은 상기 제 2 부분의 열부하보다 더 큰 열부하를 가지고 있고,제 1 표면아래 냉각 통로(20)와 제 2 표면아래 냉각 통로(26)중 적어도 하나가 제 1 부분을 통과하도록 선택되어 제 1 부분에서의 열제거율이 제 2 부분보다도 크게 되게하는 단계를 더 포함하는 것을 특징으로 하는 연소 터빈의 구성요소(10)를 냉각하는 방법.
- 제 1 항에 있어서, 제 1 냉각유체의 온도가 최대치로 되는 위치에 있는, 합류점(32)의 상류부분의 제 1 표면아래 냉각 통로(20)의 한 부분에 난류 발생 표면(34)을 설치하는 단계를 더 포함하는 것을 특징으로 하는 연소 터빈의 구성요소(10)를 냉각하는 방법.
- 제 1 항에 있어서, 각각의 냉각유체의 유동 통로를 따라 제 1 표면아래 냉각 통로(20)와 제 2 표면아래 냉각 통로(26)중 적어도 하나의 유동 단면적을 변경시킴으로써, 소정의 냉각율이 가스측 표면(14)위의 선택된 지점(16, 18)에서 얻어지게 하는 단계를 더 포함하는 것을 특징으로 하는 연소 터빈의 구성요소(10)를 냉각하는 방법.
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Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/226,732 | 1999-01-07 | ||
US09/226,732 US6224329B1 (en) | 1999-01-07 | 1999-01-07 | Method of cooling a combustion turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
KR20010101372A KR20010101372A (ko) | 2001-11-14 |
KR100711057B1 true KR100711057B1 (ko) | 2007-04-24 |
Family
ID=22850170
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
KR1020017008498A KR100711057B1 (ko) | 1999-01-07 | 2000-01-06 | 연소터빈의 냉각방법 |
Country Status (6)
Country | Link |
---|---|
US (1) | US6224329B1 (ko) |
EP (1) | EP1144808B1 (ko) |
JP (1) | JP4508426B2 (ko) |
KR (1) | KR100711057B1 (ko) |
DE (1) | DE60018706T2 (ko) |
WO (1) | WO2000040838A1 (ko) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR101913122B1 (ko) * | 2017-02-06 | 2018-10-31 | 두산중공업 주식회사 | 직렬로 연결된 냉각홀을 포함하는 가스터빈 링세그먼트 및 이를 포함하는 가스터빈 |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19919654A1 (de) * | 1999-04-29 | 2000-11-02 | Abb Alstom Power Ch Ag | Hitzeschild für eine Gasturbine |
US6331096B1 (en) * | 2000-04-05 | 2001-12-18 | General Electric Company | Apparatus and methods for impingement cooling of an undercut region adjacent a side wall of a turbine nozzle segment |
US6435816B1 (en) * | 2000-11-03 | 2002-08-20 | General Electric Co. | Gas injector system and its fabrication |
EP1256695A1 (de) * | 2001-05-07 | 2002-11-13 | Siemens Aktiengesellschaft | Formstück zur Bildung eines Führungsrings für eine Gasturbine, sowie Gasturbine mit derartigem Führungsring |
US6904747B2 (en) * | 2002-08-30 | 2005-06-14 | General Electric Company | Heat exchanger for power generation equipment |
US7052231B2 (en) * | 2003-04-28 | 2006-05-30 | General Electric Company | Methods and apparatus for injecting fluids in gas turbine engines |
US7191714B2 (en) * | 2003-08-21 | 2007-03-20 | International Enviornmental Solutions Corporation | Shaft seal for a pyrolytic waste treatment system |
US7144220B2 (en) * | 2004-07-30 | 2006-12-05 | United Technologies Corporation | Investment casting |
US7520715B2 (en) * | 2005-07-19 | 2009-04-21 | Pratt & Whitney Canada Corp. | Turbine shroud segment transpiration cooling with individual cast inlet and outlet cavities |
US7571611B2 (en) * | 2006-04-24 | 2009-08-11 | General Electric Company | Methods and system for reducing pressure losses in gas turbine engines |
US20090145132A1 (en) * | 2007-12-07 | 2009-06-11 | General Electric Company | Methods and system for reducing pressure losses in gas turbine engines |
US8128344B2 (en) * | 2008-11-05 | 2012-03-06 | General Electric Company | Methods and apparatus involving shroud cooling |
US8662845B2 (en) | 2011-01-11 | 2014-03-04 | United Technologies Corporation | Multi-function heat shield for a gas turbine engine |
US8840375B2 (en) | 2011-03-21 | 2014-09-23 | United Technologies Corporation | Component lock for a gas turbine engine |
EP2549063A1 (en) * | 2011-07-21 | 2013-01-23 | Siemens Aktiengesellschaft | Heat shield element for a gas turbine |
US10329941B2 (en) * | 2016-05-06 | 2019-06-25 | United Technologies Corporation | Impingement manifold |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4526226A (en) * | 1981-08-31 | 1985-07-02 | General Electric Company | Multiple-impingement cooled structure |
JPH08165904A (ja) * | 1994-06-30 | 1996-06-25 | General Electric Co <Ge> | タービンのスチームによる衝突冷却装置、タービンシュラウドを冷却するシステム及びタービンシュラウドをスチーム衝突により冷却する方法 |
US5581994A (en) * | 1993-08-23 | 1996-12-10 | Abb Management Ag | Method for cooling a component and appliance for carrying out the method |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3689174A (en) | 1971-01-11 | 1972-09-05 | Westinghouse Electric Corp | Axial flow turbine structure |
SE369539B (ko) | 1973-01-05 | 1974-09-02 | Stal Laval Turbin Ab | |
US3864056A (en) | 1973-07-27 | 1975-02-04 | Westinghouse Electric Corp | Cooled turbine blade ring assembly |
US4180373A (en) | 1977-12-28 | 1979-12-25 | United Technologies Corporation | Turbine blade |
US4214851A (en) | 1978-04-20 | 1980-07-29 | General Electric Company | Structural cooling air manifold for a gas turbine engine |
US4230436A (en) * | 1978-07-17 | 1980-10-28 | General Electric Company | Rotor/shroud clearance control system |
US4232527A (en) | 1979-04-13 | 1980-11-11 | General Motors Corporation | Combustor liner joints |
GB2047354B (en) | 1979-04-26 | 1983-03-30 | Rolls Royce | Gas turbine engines |
US4551064A (en) | 1982-03-05 | 1985-11-05 | Rolls-Royce Limited | Turbine shroud and turbine shroud assembly |
US4721433A (en) * | 1985-12-19 | 1988-01-26 | United Technologies Corporation | Coolable stator structure for a gas turbine engine |
JPH0816531B2 (ja) | 1987-04-03 | 1996-02-21 | 株式会社日立製作所 | ガスタ−ビン燃焼器 |
US5720431A (en) * | 1988-08-24 | 1998-02-24 | United Technologies Corporation | Cooled blades for a gas turbine engine |
US5039562A (en) * | 1988-10-20 | 1991-08-13 | The United States Of America As Represented By The Secretary Of The Air Force | Method and apparatus for cooling high temperature ceramic turbine blade portions |
US5100291A (en) | 1990-03-28 | 1992-03-31 | General Electric Company | Impingement manifold |
US5472313A (en) | 1991-10-30 | 1995-12-05 | General Electric Company | Turbine disk cooling system |
US5816777A (en) * | 1991-11-29 | 1998-10-06 | United Technologies Corporation | Turbine blade cooling |
US5273396A (en) | 1992-06-22 | 1993-12-28 | General Electric Company | Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud |
DE4326801A1 (de) | 1993-08-10 | 1995-02-16 | Abb Management Ag | Verfahren und Vorrichtung zur Kühlung von Gasturbinen |
US5472316A (en) | 1994-09-19 | 1995-12-05 | General Electric Company | Enhanced cooling apparatus for gas turbine engine airfoils |
-
1999
- 1999-01-07 US US09/226,732 patent/US6224329B1/en not_active Expired - Lifetime
-
2000
- 2000-01-06 KR KR1020017008498A patent/KR100711057B1/ko not_active IP Right Cessation
- 2000-01-06 EP EP00904232A patent/EP1144808B1/en not_active Expired - Lifetime
- 2000-01-06 WO PCT/US2000/000297 patent/WO2000040838A1/en active IP Right Grant
- 2000-01-06 JP JP2000592521A patent/JP4508426B2/ja not_active Expired - Fee Related
- 2000-01-06 DE DE60018706T patent/DE60018706T2/de not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4526226A (en) * | 1981-08-31 | 1985-07-02 | General Electric Company | Multiple-impingement cooled structure |
US5581994A (en) * | 1993-08-23 | 1996-12-10 | Abb Management Ag | Method for cooling a component and appliance for carrying out the method |
JPH08165904A (ja) * | 1994-06-30 | 1996-06-25 | General Electric Co <Ge> | タービンのスチームによる衝突冷却装置、タービンシュラウドを冷却するシステム及びタービンシュラウドをスチーム衝突により冷却する方法 |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR101913122B1 (ko) * | 2017-02-06 | 2018-10-31 | 두산중공업 주식회사 | 직렬로 연결된 냉각홀을 포함하는 가스터빈 링세그먼트 및 이를 포함하는 가스터빈 |
Also Published As
Publication number | Publication date |
---|---|
KR20010101372A (ko) | 2001-11-14 |
WO2000040838A1 (en) | 2000-07-13 |
EP1144808B1 (en) | 2005-03-16 |
US6224329B1 (en) | 2001-05-01 |
DE60018706T2 (de) | 2006-03-16 |
JP4508426B2 (ja) | 2010-07-21 |
EP1144808A1 (en) | 2001-10-17 |
JP2002534628A (ja) | 2002-10-15 |
DE60018706D1 (de) | 2005-04-21 |
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