WO1998057044B1 - Combustion turbine cooling panel - Google Patents

Combustion turbine cooling panel

Info

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
Application number
PCT/US1998/010919
Other languages
French (fr)
Other versions
WO1998057044A1 (en
Filing date
Publication date
Priority claimed from US08/874,703 external-priority patent/US6018950A/en
Application filed filed Critical
Priority to DE69803069T priority Critical patent/DE69803069T2/en
Priority to JP50258299A priority patent/JP2002511126A/en
Priority to EP98939068A priority patent/EP0988441B1/en
Publication of WO1998057044A1 publication Critical patent/WO1998057044A1/en
Publication of WO1998057044B1 publication Critical patent/WO1998057044B1/en

Links

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

AMENDED CLAIMS[received by the International Bureau on 29 December 1998 (29.12.98); original claims 1-12 replaced by new claims 1-15 (3 pages)]
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.
PCT/US1998/010919 1997-06-13 1998-05-28 Combustion turbine cooling panel WO1998057044A1 (en)

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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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

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