WO2001020133A8 - Film cooling hole construction in gas turbine moving-vanes - Google Patents

Film cooling hole construction in gas turbine moving-vanes

Info

Publication number
WO2001020133A8
WO2001020133A8 PCT/JP1999/005047 JP9905047W WO0120133A8 WO 2001020133 A8 WO2001020133 A8 WO 2001020133A8 JP 9905047 W JP9905047 W JP 9905047W WO 0120133 A8 WO0120133 A8 WO 0120133A8
Authority
WO
WIPO (PCT)
Prior art keywords
cooling
cooling hole
gas turbine
vane
flow
Prior art date
Application number
PCT/JP1999/005047
Other languages
French (fr)
Japanese (ja)
Other versions
WO2001020133A1 (en
Inventor
Masanori Yuri
Original Assignee
Mitsubishi Heavy Ind Ltd
Masanori Yuri
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 Mitsubishi Heavy Ind Ltd, Masanori Yuri filed Critical Mitsubishi Heavy Ind Ltd
Priority to CA002347888A priority Critical patent/CA2347888A1/en
Priority to EP99943365A priority patent/EP1132575A4/en
Priority to PCT/JP1999/005047 priority patent/WO2001020133A1/en
Priority to US09/807,748 priority patent/US6474947B1/en
Publication of WO2001020133A1 publication Critical patent/WO2001020133A1/en
Publication of WO2001020133A8 publication Critical patent/WO2001020133A8/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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A moving vane (20) is formed with cooling passages (22, 23) partitioned by a rib (51), wherein cooling air (41) flows in through the cooling passage (22) and into the cooling passage (23) as indicated by an arrow (41e). A stagnant region (53) is formed in the corner at the front end of the cooling passage (22) where there is no cooling hole (50); however, a flow (41i) goes out of the vane through a cooling hole (2), so that a flow of cooling air is formed in this region. Further, at the front end of a rib (51) there is formed a peel region (52) due to the peeling of the flow, but the cooling air (41h) flows out of the vane through a cooling hole (1) and a flow of cooling air is produced in this region. Further, a film cooling hole construction is also disclosed wherein in a gas turbine moving-vane having multi-stage turbulators (28) formed on the inner wall surface (60) of the cooling passage, the peeling of the cooling air taking place between the turbulators (28) is eliminated.
PCT/JP1999/005047 1998-03-13 1999-09-16 Film cooling hole construction in gas turbine moving-vanes WO2001020133A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
CA002347888A CA2347888A1 (en) 1999-09-16 1999-09-16 Film cooling hole structure of gas turbine moving blade
EP99943365A EP1132575A4 (en) 1999-09-16 1999-09-16 Film cooling hole construction in gas turbine moving-vanes
PCT/JP1999/005047 WO2001020133A1 (en) 1999-09-16 1999-09-16 Film cooling hole construction in gas turbine moving-vanes
US09/807,748 US6474947B1 (en) 1998-03-13 1999-09-16 Film cooling hole construction in gas turbine moving-vanes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP1999/005047 WO2001020133A1 (en) 1999-09-16 1999-09-16 Film cooling hole construction in gas turbine moving-vanes

Publications (2)

Publication Number Publication Date
WO2001020133A1 WO2001020133A1 (en) 2001-03-22
WO2001020133A8 true WO2001020133A8 (en) 2001-07-26

Family

ID=14236721

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP1999/005047 WO2001020133A1 (en) 1998-03-13 1999-09-16 Film cooling hole construction in gas turbine moving-vanes

Country Status (3)

Country Link
EP (1) EP1132575A4 (en)
CA (1) CA2347888A1 (en)
WO (1) WO2001020133A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1362982B1 (en) 2002-05-09 2010-08-18 General Electric Company Turbine airfoil with single aft flowing three pass serpentine cooling circuit
US7235122B2 (en) 2004-11-08 2007-06-26 E. I. Du Pont De Nemours And Company Filtration media for filtering particulate material from gas streams
CN104791020B (en) * 2015-04-23 2016-06-15 华能国际电力股份有限公司 Gas turbine blade with longitudinal crossed rib cooling structure

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1350424A (en) * 1971-07-02 1974-04-18 Rolls Royce Cooled blade for a gas turbine engine
GB1564608A (en) * 1975-12-20 1980-04-10 Rolls Royce Means for cooling a surface by the impingement of a cooling fluid
GB2165315B (en) * 1984-10-04 1987-12-31 Rolls Royce Improvements in or relating to hollow fluid cooled turbine blades
JPS62228603A (en) * 1986-03-31 1987-10-07 Toshiba Corp Gas turbine blade
US4930980A (en) * 1989-02-15 1990-06-05 Westinghouse Electric Corp. Cooled turbine vane
JPH11257005A (en) * 1998-03-16 1999-09-21 Mitsubishi Heavy Ind Ltd Film cooling hole structure of gas turbine moving blade

Also Published As

Publication number Publication date
WO2001020133A1 (en) 2001-03-22
CA2347888A1 (en) 2001-03-22
EP1132575A4 (en) 2002-04-10
EP1132575A1 (en) 2001-09-12

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