WO1998057044B1 - Combustion turbine cooling panel - Google Patents
Combustion turbine cooling panelInfo
- Publication number
- WO1998057044B1 WO1998057044B1 PCT/US1998/010919 US9810919W WO9857044B1 WO 1998057044 B1 WO1998057044 B1 WO 1998057044B1 US 9810919 W US9810919 W US 9810919W WO 9857044 B1 WO9857044 B1 WO 9857044B1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- cooling
- panel
- flow channel
- liner
- cooling panel
- Prior art date
Links
- 238000001816 cooling Methods 0.000 title claims abstract 59
- 238000002485 combustion reaction Methods 0.000 title 1
- 239000012530 fluid Substances 0.000 claims abstract 15
- 230000000875 corresponding Effects 0.000 claims 2
- 238000005352 clarification Methods 0.000 claims 1
- 239000002826 coolant Substances 0.000 claims 1
- 230000002708 enhancing Effects 0.000 claims 1
- 238000003754 machining Methods 0.000 claims 1
- 238000002156 mixing Methods 0.000 claims 1
- 239000000203 mixture Substances 0.000 claims 1
- 230000004048 modification Effects 0.000 claims 1
- 238000006011 modification reaction Methods 0.000 claims 1
Abstract
A cooling panel for cooling a turbine member is provided. The cooling panel comprises a first panel having a relative width, relative length, upper surface and lower surface. The upper surface defines at least one corrugated portion traversing along a portion of the relative width of the upper surface. The corrugated portion defines a cooling flow channel through which a cooling fluid can travel to cool the turbine member. The cooling flow channel has at least one inlet opening for enabling the cooling fluid to enter into the cooling flow channel. The lower portion surface of the first panel is adapted to be coupled in fluid communication witth the turbine member.
Claims
1. A cooling panel (64) for a gas turbine for enhancing_cooling of a finite segment of a turbine member (58), said cooling panel (64) comprising: a first panel (65) having a relative finite width (W) and Length (L)Λ which are substantially less than the width and length of the turbine member, an outer surface (74) and an inner surface (76), said outer surface (74) defining at least one channeled portion (80) traversing along a portion of the relative width of said outer surface, said channeled portion (80) defining a cooling flow channel (82) through which a cooling fluid can travel to cool the finite segment of the turbine member (58), said cooling flow channel (82) having at least one inlet opening (84) for enabling the cooling fluid to enter into the cooling flow channel, said inner surface (76) having a portion thereof_adapted to be removably attached to an outer surface (70) of the turbine member (58), and a closed end (86), spaced along said cooling flow channel (82) from said inlet opening (84), to direct the cooling fluid to an outlet opening.
2. The cooling panel (64) in claim 1, wherein said first panel (65) is adapted to be attached to the turbine member in a manner that enables he cooling panel (65) to be removed and replaced with another cooling panel (65).
3. The cooling panel (64) in claim 2, further comprising a plurality of channels (80).
4. The cooling panel (64) in claim 3, wherein said plurality of channels (80) are formed from a corrugation (80).
5. The cooling panel (64) in claim 3, wherein the positioning of the inlet opening (84) and closed end (86) of one channel (80) is located at opposite ends relative to adjacent channels (80).
6. The cooling panel (64) in claim 2, wherein each channel (80) comprises a relative peak radius (Rp) and two leg radii (RL), said peak radius (R.) blending substantially smoothly with each one of said leg radii (RL).
7. The cooling panel (64) in claim 6, wherein each channel (80) is spaced equidistant apart from each neighboring channel (80).
8. The cooling panel (64) in claim 6, wherein each leg radii (RJ extends into and blends generally smoothly with corresponding generally flat surface, said generally flat surface having an upper portion and bottom portion (77), said bottom portion (77) of each generally flat surface adapted to be removably attached to the turbine member.
9. An improved gas turbine having a combustor transition member (100) comprising: a side wall (102) having an exterior surface (106) and interior surface
(104), said interior surface (104) defining a working gas flow channel (108) having an inlet end (110) and outlet end (112); and at least one cooling panel (126) having a finite dimension along the surface of the side wall (102) which is substantially less than the corresponding dimension of the side wall (102), said cooling panel (126) comprising at least one channel (136) which protrudes in a outwardly direction relative to said exterior surface (106)_of said side wall (102) and defines a cooling flow channel (114)_having an open end (116) which forms a cooling fluid inlet (116) and a closed end (118) at the opposite end of the cooling flow channel (114) spaced from the open end (116), said cooling panel (126) mechanically coupled to said exterior surface (106) of said side wall (102) such that said cooling flow channel is in fluid communication with said working gas flow channel through an inlet port (120) in the side wall (102) positioned proximate said closed end (118).
10. A method of enhancing the cooling properties of a portion of a cooling fluid flow path (82) within a gas turbine transition member (58) enclosed within a shell (48) that surrounds a transition member liner (66) that funnels a working gas to a turbine section (56) to produce mechanical work, wherein the area between the shell (48) and the liner (66) defines the cooling fluid flow path (82) comprising the steps of: machining a predetermined sized liner port (90) through the surface (70) of the liner (66), that provides a cooling fluid flow path between the shell (48) and the interior of the liner (66); positioning a discrete cooling panel (64) on the outer surface (70) of the liner (66), the cooling panel having a channeled portion (80) that defines an elongated coolant flow channel (82) with a cooling fluid inlet port (84) at one end and a closed end (86) spaced from the inlet port (84); aligning a portion of the cooling flow channel (82) proximate the closed end (86) with the liner port (90) and the rest of the cooling flow channel (82) with a portion of the surface of the liner (66) to be cooled to form a heat transfer path between the surface (70) of the liner (66) and the cooling fluid; and fastening the cooling panel (64) to the surface of the liner (66).
11. The method of claim 10 wherein the length of the cooling flow channel (82) is a relatively small increment of the length of the transition member (58).
12. The method of claim 10 wherein the cooling panel (64) defines a plurality of distinct parallel cooling flow channels (82).
13. The method of claim 12 wherein adj acent parallel cooling flow channels (82) direct the cooling fluid in opposite directions.
14. The method of claim 10 including the step of attaching a plurality of the cooling panels (64) to the turbine transition member (58).
15. The method of claim 14 including the step of removing one cooling panel (64) from the surface of the liner (66) and replacing the one cooling panel (64) with a second cooling panel (64).
STATEMENT UNDER ARTICLE 19
Claim 1 has been amended to further define that the panel of this invention is intended to cool only a finite length of a much larger turbine member and incorporates the limitations previously provided in claim 4 with regard to the cooling fluid inlet and closed end of each cooling channel. Originally filed claims 2, 3, 5, 6, 7 and 8 have been amended to provide further clarification of the subject matter originally presented. Claim 4 has been modified to identify that the channels now called for in claim 1 are formed from a corrugation. Claim 9 now calls for a gas turbine having the transition member originally claimed with a cooling panel that now conforms to the modifications provided to claim 1. Original claims 10, 11 and 12 have been cancelled and newly added method claims 10-15 recite the method for installing one or more of the cooling panels called for in claim 1.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE69803069T DE69803069T2 (en) | 1997-06-13 | 1998-05-28 | COOLED COMBUSTION CHAMBER WALL FOR A GAS TURBINE |
JP50258299A JP2002511126A (en) | 1997-06-13 | 1998-05-28 | Gas turbine cooling panel |
EP98939068A EP0988441B1 (en) | 1997-06-13 | 1998-05-28 | Combustion turbine cooling panel |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US08/874,703 US6018950A (en) | 1997-06-13 | 1997-06-13 | Combustion turbine modular cooling panel |
US08/874,703 | 1997-06-13 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO1998057044A1 WO1998057044A1 (en) | 1998-12-17 |
WO1998057044B1 true WO1998057044B1 (en) | 1999-02-18 |
Family
ID=25364375
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US1998/010919 WO1998057044A1 (en) | 1997-06-13 | 1998-05-28 | Combustion turbine cooling panel |
Country Status (7)
Country | Link |
---|---|
US (1) | US6018950A (en) |
EP (1) | EP0988441B1 (en) |
JP (1) | JP2002511126A (en) |
AR (1) | AR012961A1 (en) |
DE (1) | DE69803069T2 (en) |
TW (1) | TW394823B (en) |
WO (1) | WO1998057044A1 (en) |
Families Citing this family (64)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001289062A (en) * | 2000-04-07 | 2001-10-19 | Mitsubishi Heavy Ind Ltd | Wall surface cooling structure for gas turbine combustor |
EP1146289B1 (en) * | 2000-04-13 | 2008-12-24 | Mitsubishi Heavy Industries, Ltd. | Cooling structure of combustor tail tube |
GB2361302A (en) * | 2000-04-13 | 2001-10-17 | Rolls Royce Plc | Discharge nozzle for a gas turbine engine combustion chamber |
JP3846169B2 (en) * | 2000-09-14 | 2006-11-15 | 株式会社日立製作所 | Gas turbine repair method |
JP2002243154A (en) * | 2001-02-16 | 2002-08-28 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor and tail cylinder outlet structure thereof |
JP4008212B2 (en) * | 2001-06-29 | 2007-11-14 | 三菱重工業株式会社 | Hollow structure with flange |
US6602053B2 (en) | 2001-08-02 | 2003-08-05 | Siemens Westinghouse Power Corporation | Cooling structure and method of manufacturing the same |
JP2003201863A (en) * | 2001-10-29 | 2003-07-18 | Mitsubishi Heavy Ind Ltd | Combustor and gas turbine with it |
US6568187B1 (en) * | 2001-12-10 | 2003-05-27 | Power Systems Mfg, Llc | Effusion cooled transition duct |
US6619915B1 (en) * | 2002-08-06 | 2003-09-16 | Power Systems Mfg, Llc | Thermally free aft frame for a transition duct |
DE10239534A1 (en) * | 2002-08-23 | 2004-04-22 | Man Turbomaschinen Ag | Hot gas leading gas manifold |
EP1398462A1 (en) * | 2002-09-13 | 2004-03-17 | Siemens Aktiengesellschaft | Gas turbine and transition piece |
US6860108B2 (en) * | 2003-01-22 | 2005-03-01 | Mitsubishi Heavy Industries, Ltd. | Gas turbine tail tube seal and gas turbine using the same |
JP4191552B2 (en) * | 2003-07-14 | 2008-12-03 | 三菱重工業株式会社 | Cooling structure of gas turbine tail tube |
US7080514B2 (en) * | 2003-08-15 | 2006-07-25 | Siemens Power Generation,Inc. | High frequency dynamics resonator assembly |
EP1566531A1 (en) | 2004-02-19 | 2005-08-24 | Siemens Aktiengesellschaft | Gas turbine with compressor casing protected against cooling and Method to operate a gas turbine |
US7373772B2 (en) * | 2004-03-17 | 2008-05-20 | General Electric Company | Turbine combustor transition piece having dilution holes |
US7373778B2 (en) * | 2004-08-26 | 2008-05-20 | General Electric Company | Combustor cooling with angled segmented surfaces |
US7310938B2 (en) * | 2004-12-16 | 2007-12-25 | Siemens Power Generation, Inc. | Cooled gas turbine transition duct |
US7827801B2 (en) * | 2006-02-09 | 2010-11-09 | Siemens Energy, Inc. | Gas turbine engine transitions comprising closed cooled transition cooling channels |
US8146364B2 (en) * | 2007-09-14 | 2012-04-03 | Siemens Energy, Inc. | Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber |
MY154620A (en) * | 2008-02-20 | 2015-07-15 | Alstom Technology Ltd | Gas turbine having an improved cooling architecture |
US8186167B2 (en) * | 2008-07-07 | 2012-05-29 | General Electric Company | Combustor transition piece aft end cooling and related method |
US8033119B2 (en) * | 2008-09-25 | 2011-10-11 | Siemens Energy, Inc. | Gas turbine transition duct |
US8549861B2 (en) * | 2009-01-07 | 2013-10-08 | General Electric Company | Method and apparatus to enhance transition duct cooling in a gas turbine engine |
US20100224353A1 (en) * | 2009-03-05 | 2010-09-09 | General Electric Company | Methods and apparatus involving cooling fins |
US8015817B2 (en) * | 2009-06-10 | 2011-09-13 | Siemens Energy, Inc. | Cooling structure for gas turbine transition duct |
DE102009032277A1 (en) * | 2009-07-08 | 2011-01-20 | Rolls-Royce Deutschland Ltd & Co Kg | Combustion chamber head of a gas turbine |
US8307654B1 (en) * | 2009-09-21 | 2012-11-13 | Florida Turbine Technologies, Inc. | Transition duct with spiral finned cooling passage |
US20110110772A1 (en) * | 2009-11-11 | 2011-05-12 | Arrell Douglas J | Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same |
US8413443B2 (en) * | 2009-12-15 | 2013-04-09 | Siemens Energy, Inc. | Flow control through a resonator system of gas turbine combustor |
KR101123243B1 (en) * | 2009-12-31 | 2012-03-21 | 연세대학교 산학협력단 | AFT ring for gas turbine combustor and AFT assembly having the same |
RU2530685C2 (en) * | 2010-03-25 | 2014-10-10 | Дженерал Электрик Компани | Impact action structures for cooling systems |
US8647053B2 (en) | 2010-08-09 | 2014-02-11 | Siemens Energy, Inc. | Cooling arrangement for a turbine component |
US8667801B2 (en) | 2010-09-08 | 2014-03-11 | Siemens Energy, Inc. | Combustor liner assembly with enhanced cooling system |
US8720204B2 (en) | 2011-02-09 | 2014-05-13 | Siemens Energy, Inc. | Resonator system with enhanced combustor liner cooling |
ES2427440T3 (en) * | 2011-03-15 | 2013-10-30 | Siemens Aktiengesellschaft | Gas turbine combustion chamber |
US9127551B2 (en) | 2011-03-29 | 2015-09-08 | Siemens Energy, Inc. | Turbine combustion system cooling scoop |
CN103649468A (en) * | 2011-03-31 | 2014-03-19 | 通用电气公司 | Power augmentation system with dynamics damping |
US8966910B2 (en) * | 2011-06-21 | 2015-03-03 | General Electric Company | Methods and systems for cooling a transition nozzle |
JP5804872B2 (en) * | 2011-09-27 | 2015-11-04 | 三菱日立パワーシステムズ株式会社 | Combustor transition piece, gas turbine equipped with the same, and transition piece manufacturing method |
US9085981B2 (en) | 2012-10-19 | 2015-07-21 | Siemens Energy, Inc. | Ducting arrangement for cooling a gas turbine structure |
US20160348911A1 (en) * | 2013-12-12 | 2016-12-01 | Siemens Energy, Inc. | W501 d5/d5a df42 combustion system |
KR101579122B1 (en) * | 2014-01-15 | 2015-12-21 | 두산중공업 주식회사 | Combuster of gas turbine, gasturbineincluding the same, and cooling method thereof |
US20150198050A1 (en) * | 2014-01-15 | 2015-07-16 | Siemens Energy, Inc. | Internal cooling system with corrugated insert forming nearwall cooling channels for airfoil usable in a gas turbine engine |
KR101556532B1 (en) * | 2014-01-16 | 2015-10-01 | 두산중공업 주식회사 | liner, flow sleeve and gas turbine combustor including cooling sleeve |
EP2960436B1 (en) * | 2014-06-27 | 2017-08-09 | Ansaldo Energia Switzerland AG | Cooling structure for a transition piece of a gas turbine |
US10520193B2 (en) * | 2015-10-28 | 2019-12-31 | General Electric Company | Cooling patch for hot gas path components |
US10801341B2 (en) * | 2015-12-15 | 2020-10-13 | Siemens Aktiengesellschaft | Cooling features for a gas turbine engine transition duct |
JP6843513B2 (en) * | 2016-03-29 | 2021-03-17 | 三菱パワー株式会社 | Combustor, how to improve the performance of the combustor |
KR102099307B1 (en) * | 2017-10-11 | 2020-04-09 | 두산중공업 주식회사 | Turbulence generating structure for enhancing cooling performance of liner and a gas turbine combustor using the same |
CN109882314B (en) * | 2019-03-08 | 2021-09-10 | 西北工业大学 | Double-walled cooling structure with transverse corrugated impingement orifice plate for a vectoring nozzle |
US11371702B2 (en) | 2020-08-31 | 2022-06-28 | General Electric Company | Impingement panel for a turbomachine |
US11994293B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus support structure and method of manufacture |
US11614233B2 (en) | 2020-08-31 | 2023-03-28 | General Electric Company | Impingement panel support structure and method of manufacture |
US11460191B2 (en) | 2020-08-31 | 2022-10-04 | General Electric Company | Cooling insert for a turbomachine |
US11994292B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus for turbomachine |
US11255545B1 (en) | 2020-10-26 | 2022-02-22 | General Electric Company | Integrated combustion nozzle having a unified head end |
CN112490579A (en) * | 2020-12-16 | 2021-03-12 | 广东和胜新能源汽车配件有限公司 | Battery box |
EP4047187A1 (en) * | 2021-02-18 | 2022-08-24 | Siemens Energy Global GmbH & Co. KG | Transition with uneven surface |
DE112022001110T5 (en) * | 2021-02-18 | 2024-01-18 | Siemens Energy Global GmbH & Co. KG | Transition with uneven surface |
CN113739201B (en) * | 2021-09-13 | 2023-02-17 | 中国联合重型燃气轮机技术有限公司 | Cap with drainage device |
US11767766B1 (en) | 2022-07-29 | 2023-09-26 | General Electric Company | Turbomachine airfoil having impingement cooling passages |
US20240191630A1 (en) * | 2022-12-09 | 2024-06-13 | General Electric Company | Fluid ducts including a rib |
Family Cites Families (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2610467A (en) * | 1946-04-03 | 1952-09-16 | Westinghouse Electric Corp | Combustion chamber having telescoping walls and corrugated spacers |
US2958194A (en) * | 1951-09-24 | 1960-11-01 | Power Jets Res & Dev Ltd | Cooled flame tube |
NL248467A (en) * | 1957-02-18 | |||
US2938333A (en) * | 1957-03-18 | 1960-05-31 | Gen Motors Corp | Combustion chamber liner construction |
GB1010338A (en) * | 1962-09-11 | 1965-11-17 | Lucas Industries Ltd | Means for supporting the downstream end of a combustion chamber in a gas turbine engine |
GB1074785A (en) * | 1965-04-08 | 1967-07-05 | Rolls Royce | Combustion apparatus e.g. for a gas turbine engine |
US3485043A (en) * | 1968-02-01 | 1969-12-23 | Gen Electric | Shingled combustion liner |
US3572031A (en) * | 1969-07-11 | 1971-03-23 | United Aircraft Corp | Variable area cooling passages for gas turbine burners |
US4392355A (en) * | 1969-11-13 | 1983-07-12 | General Motors Corporation | Combustion liner |
US3589128A (en) * | 1970-02-02 | 1971-06-29 | Avco Corp | Cooling arrangement for a reverse flow gas turbine combustor |
US3652181A (en) * | 1970-11-23 | 1972-03-28 | Carl F Wilhelm Jr | Cooling sleeve for gas turbine combustor transition member |
US3702058A (en) * | 1971-01-13 | 1972-11-07 | Westinghouse Electric Corp | Double wall combustion chamber |
US3800864A (en) * | 1972-09-05 | 1974-04-02 | Gen Electric | Pin-fin cooling system |
GB1438379A (en) * | 1973-08-16 | 1976-06-03 | Rolls Royce | Cooling arrangement for duct walls |
GB2087066B (en) * | 1980-11-06 | 1984-09-19 | Westinghouse Electric Corp | Transition duct for combustion turbine |
US4719748A (en) * | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
JPH0752014B2 (en) * | 1986-03-20 | 1995-06-05 | 株式会社日立製作所 | Gas turbine combustor |
DE3803086C2 (en) * | 1987-02-06 | 1997-06-26 | Gen Electric | Combustion chamber for a gas turbine engine |
US4821522A (en) * | 1987-07-02 | 1989-04-18 | United Technologies Corporation | Sealing and cooling arrangement for combustor vane interface |
US5144793A (en) * | 1990-12-24 | 1992-09-08 | United Technologies Corporation | Integrated connector/airtube for a turbomachine's combustion chamber walls |
US5687572A (en) * | 1992-11-02 | 1997-11-18 | Alliedsignal Inc. | Thin wall combustor with backside impingement cooling |
US5375973A (en) * | 1992-12-23 | 1994-12-27 | United Technologies Corporation | Turbine blade outer air seal with optimized cooling |
US5596870A (en) * | 1994-09-09 | 1997-01-28 | United Technologies Corporation | Gas turbine exhaust liner with milled air chambers |
DE4443864A1 (en) * | 1994-12-09 | 1996-06-13 | Abb Management Ag | Cooled wall part |
US5737922A (en) * | 1995-01-30 | 1998-04-14 | Aerojet General Corporation | Convectively cooled liner for a combustor |
-
1997
- 1997-06-13 US US08/874,703 patent/US6018950A/en not_active Expired - Lifetime
-
1998
- 1998-05-28 JP JP50258299A patent/JP2002511126A/en not_active Ceased
- 1998-05-28 WO PCT/US1998/010919 patent/WO1998057044A1/en active IP Right Grant
- 1998-05-28 EP EP98939068A patent/EP0988441B1/en not_active Expired - Lifetime
- 1998-05-28 DE DE69803069T patent/DE69803069T2/en not_active Expired - Lifetime
- 1998-06-04 TW TW087108865A patent/TW394823B/en active
- 1998-06-10 AR ARP980102751A patent/AR012961A1/en unknown
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