WO2007050205A3 - Serpentine cooling circuit and method for cooling a gas turbine part - Google Patents

Serpentine cooling circuit and method for cooling a gas turbine part Download PDF

Info

Publication number
WO2007050205A3
WO2007050205A3 PCT/US2006/036523 US2006036523W WO2007050205A3 WO 2007050205 A3 WO2007050205 A3 WO 2007050205A3 US 2006036523 W US2006036523 W US 2006036523W WO 2007050205 A3 WO2007050205 A3 WO 2007050205A3
Authority
WO
WIPO (PCT)
Prior art keywords
circuit channel
heat exchanger
cooling
gas turbine
compact heat
Prior art date
Application number
PCT/US2006/036523
Other languages
French (fr)
Other versions
WO2007050205A2 (en
Inventor
Paul M Lutjen
Gary L Grogg
Original Assignee
United Technologies Corp
Paul M Lutjen
Gary L Grogg
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by United Technologies Corp, Paul M Lutjen, Gary L Grogg filed Critical United Technologies Corp
Publication of WO2007050205A2 publication Critical patent/WO2007050205A2/en
Publication of WO2007050205A3 publication Critical patent/WO2007050205A3/en

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
    • F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D21/00—Heat-exchange apparatus not covered by any of the groups F28D1/00 - F28D20/00
    • F28D2021/0019—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for
    • F28D2021/0077—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for tempering, e.g. with cooling or heating circuits for temperature control of elements
    • F28D2021/0078—Other heat exchangers for particular applications; Heat exchange systems not otherwise provided for for tempering, e.g. with cooling or heating circuits for temperature control of elements in the form of cooling walls

Abstract

A compact heat exchanger for providing coolant gas flow through a gas turbine component is provided. The compact heat exchanger reduces internal pressure losses through the compact heat exchanger. The compact heat exchanger has at least one inlet through which a coolant gas may enter, a circuit channel in fluid communication with the at least one inlet, and at least one outlet in fluid communication with the circuit channel through which the coolant gas may- exit the circuit channel. The circuit channel is formed from superimposition of a plurality of alternating serpentine circuits, where at least one crossover of the circuit channel has a flow stabilizer that is formed in the channel and reduces internal pressure losses in the circuit channel.
PCT/US2006/036523 2005-09-19 2006-09-19 Serpentine cooling circuit and method for cooling a gas turbine part WO2007050205A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/229,783 US20070227706A1 (en) 2005-09-19 2005-09-19 Compact heat exchanger
US11/229,783 2005-09-19

Publications (2)

Publication Number Publication Date
WO2007050205A2 WO2007050205A2 (en) 2007-05-03
WO2007050205A3 true WO2007050205A3 (en) 2007-09-20

Family

ID=37968291

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2006/036523 WO2007050205A2 (en) 2005-09-19 2006-09-19 Serpentine cooling circuit and method for cooling a gas turbine part

Country Status (2)

Country Link
US (1) US20070227706A1 (en)
WO (1) WO2007050205A2 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8157527B2 (en) 2008-07-03 2012-04-17 United Technologies Corporation Airfoil with tapered radial cooling passage
US8572844B2 (en) 2008-08-29 2013-11-05 United Technologies Corporation Airfoil with leading edge cooling passage
US8303252B2 (en) 2008-10-16 2012-11-06 United Technologies Corporation Airfoil with cooling passage providing variable heat transfer rate
US8109725B2 (en) 2008-12-15 2012-02-07 United Technologies Corporation Airfoil with wrapped leading edge cooling passage
GB201016335D0 (en) * 2010-09-29 2010-11-10 Rolls Royce Plc Endwall component for a turbine stage of a gas turbine engine
US8449246B1 (en) * 2010-12-01 2013-05-28 Florida Turbine Technologies, Inc. BOAS with micro serpentine cooling
US10221708B2 (en) * 2014-12-03 2019-03-05 United Technologies Corporation Tangential on-board injection vanes

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1257041A (en) * 1968-03-27 1971-12-15
US4203706A (en) * 1977-12-28 1980-05-20 United Technologies Corporation Radial wafer airfoil construction
US4407632A (en) * 1981-06-26 1983-10-04 United Technologies Corporation Airfoil pedestaled trailing edge region cooling configuration
US4542867A (en) * 1983-01-31 1985-09-24 United Technologies Corporation Internally cooled hollow airfoil
US4752186A (en) * 1981-06-26 1988-06-21 United Technologies Corporation Coolable wall configuration
US5243759A (en) * 1991-10-07 1993-09-14 United Technologies Corporation Method of casting to control the cooling air flow rate of the airfoil trailing edge
US5772397A (en) * 1996-05-08 1998-06-30 Alliedsignal Inc. Gas turbine airfoil with aft internal cooling
EP1091091A2 (en) * 1999-10-05 2001-04-11 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
EP1091092A2 (en) * 1999-10-05 2001-04-11 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
EP1223308A2 (en) * 2000-12-16 2002-07-17 ALSTOM (Switzerland) Ltd Cooling of a turbo machine component
US20030235494A1 (en) * 2002-06-19 2003-12-25 Draper Samuel David Linked, manufacturable, non-plugging microcircuits
EP1505257A2 (en) * 2003-08-08 2005-02-09 United Technologies Corporation Gas turbine blade circuit cooling
WO2005083235A1 (en) * 2004-02-27 2005-09-09 Siemens Aktiengesellschaft Blade or vane for a turbomachine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2389119A1 (en) * 2002-06-04 2003-12-04 Christopher R. Shore Lateral plate finned heat exchanger
DE10236380A1 (en) * 2002-08-08 2004-03-04 Mtu Aero Engines Gmbh Recuperative exhaust gas heat exchanger for gas turbine drive has collection tube with closed end fastened radially and axially to turbine housing

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1257041A (en) * 1968-03-27 1971-12-15
US4203706A (en) * 1977-12-28 1980-05-20 United Technologies Corporation Radial wafer airfoil construction
US4407632A (en) * 1981-06-26 1983-10-04 United Technologies Corporation Airfoil pedestaled trailing edge region cooling configuration
US4752186A (en) * 1981-06-26 1988-06-21 United Technologies Corporation Coolable wall configuration
US4542867A (en) * 1983-01-31 1985-09-24 United Technologies Corporation Internally cooled hollow airfoil
US5243759A (en) * 1991-10-07 1993-09-14 United Technologies Corporation Method of casting to control the cooling air flow rate of the airfoil trailing edge
US5772397A (en) * 1996-05-08 1998-06-30 Alliedsignal Inc. Gas turbine airfoil with aft internal cooling
EP1091091A2 (en) * 1999-10-05 2001-04-11 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
EP1091092A2 (en) * 1999-10-05 2001-04-11 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
EP1223308A2 (en) * 2000-12-16 2002-07-17 ALSTOM (Switzerland) Ltd Cooling of a turbo machine component
US20030235494A1 (en) * 2002-06-19 2003-12-25 Draper Samuel David Linked, manufacturable, non-plugging microcircuits
EP1505257A2 (en) * 2003-08-08 2005-02-09 United Technologies Corporation Gas turbine blade circuit cooling
WO2005083235A1 (en) * 2004-02-27 2005-09-09 Siemens Aktiengesellschaft Blade or vane for a turbomachine

Also Published As

Publication number Publication date
WO2007050205A2 (en) 2007-05-03
US20070227706A1 (en) 2007-10-04

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