EP1008727A3 - Cooling in gas turbines - Google Patents

Cooling in gas turbines Download PDF

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Publication number
EP1008727A3
EP1008727A3 EP99811112A EP99811112A EP1008727A3 EP 1008727 A3 EP1008727 A3 EP 1008727A3 EP 99811112 A EP99811112 A EP 99811112A EP 99811112 A EP99811112 A EP 99811112A EP 1008727 A3 EP1008727 A3 EP 1008727A3
Authority
EP
European Patent Office
Prior art keywords
cooling
gas turbines
another
static pressure
cooling bores
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
EP99811112A
Other languages
German (de)
French (fr)
Other versions
EP1008727A2 (en
Inventor
Fathi Dr. Tarada
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Technology GmbH
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1008727A2 publication Critical patent/EP1008727A2/en
Publication of EP1008727A3 publication Critical patent/EP1008727A3/en
Ceased legal-status Critical Current

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
    • F01D5/186—Film 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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

Abstract

Um eine ausreichende Kühlung der Bauteile (210) zu gewährleisten, ist erfindungsgemäß der Abstand der Kühlbohrungen (240) untereinander jeweils so gewählt, daß die Kühlbohrungen (240) in dem Bereich erhöhten statischen Druckes (234) des heissen Fluides einen kleineren Abstand zueinander aufweisen als in den Bereichen niedrigeren statischen Druckes. Eine typische Ausführung der Erfindung ist in Figur 3 dargestellt.

Figure 00000001
In order to ensure adequate cooling of the components (210), the spacing of the cooling bores (240) among one another is selected in accordance with the invention such that the cooling bores (240) are at a smaller distance from one another in the area of increased static pressure (234) of the hot fluid in the areas of lower static pressure. A typical embodiment of the invention is shown in FIG. 3.
Figure 00000001
EP99811112A 1998-12-05 1999-12-02 Cooling in gas turbines Ceased EP1008727A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19856199 1998-12-05
DE19856199A DE19856199A1 (en) 1998-12-05 1998-12-05 Cooling in gas turbines

Publications (2)

Publication Number Publication Date
EP1008727A2 EP1008727A2 (en) 2000-06-14
EP1008727A3 true EP1008727A3 (en) 2003-11-19

Family

ID=7890118

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99811112A Ceased EP1008727A3 (en) 1998-12-05 1999-12-02 Cooling in gas turbines

Country Status (3)

Country Link
US (1) US6276897B1 (en)
EP (1) EP1008727A3 (en)
DE (1) DE19856199A1 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6672832B2 (en) * 2002-01-07 2004-01-06 General Electric Company Step-down turbine platform
US20050070983A1 (en) * 2003-09-25 2005-03-31 Rugnetta Jaime L. Lead system having lead body with minimized cross-section
US8651799B2 (en) * 2011-06-02 2014-02-18 General Electric Company Turbine nozzle slashface cooling holes
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
EP2885506B8 (en) 2012-08-17 2021-03-31 Raytheon Technologies Corporation Contoured flowpath surface
EP2949871B1 (en) * 2014-05-07 2017-03-01 United Technologies Corporation Variable vane segment
US20210079799A1 (en) * 2019-09-12 2021-03-18 General Electric Company Nozzle assembly for turbine engine
CN111779548B (en) * 2020-06-29 2021-05-28 西安交通大学 End wall air film hole arrangement structure
US11927111B2 (en) * 2022-06-09 2024-03-12 General Electric Company Turbine engine with a blade

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB980363A (en) * 1961-12-04 1965-01-13 Jan Jerie Improvements in or relating to gas turbines
US4137619A (en) * 1977-10-03 1979-02-06 General Electric Company Method of fabricating composite structures for water cooled gas turbine components
US4353679A (en) * 1976-07-29 1982-10-12 General Electric Company Fluid-cooled element
US4616976A (en) * 1981-07-07 1986-10-14 Rolls-Royce Plc Cooled vane or blade for a gas turbine engine
US4767261A (en) * 1986-04-25 1988-08-30 Rolls-Royce Plc Cooled vane
EP0615055B1 (en) * 1993-03-11 1996-02-07 ROLLS-ROYCE plc A stator blade cooling
DE19601819A1 (en) * 1995-02-23 1996-08-29 Bmw Rolls Royce Gmbh Turbine blade arrangement with a cooled shroud
US5820336A (en) * 1994-11-11 1998-10-13 Mitsubishi Heavy Industries, Ltd. Gas turbine stationary blade unit

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4283822A (en) * 1979-12-26 1981-08-18 General Electric Company Method of fabricating composite nozzles for water cooled gas turbines
JPS59122705A (en) * 1982-12-28 1984-07-16 Toshiba Corp Turbine blade
US4739621A (en) 1984-10-11 1988-04-26 United Technologies Corporation Cooling scheme for combustor vane interface

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB980363A (en) * 1961-12-04 1965-01-13 Jan Jerie Improvements in or relating to gas turbines
US4353679A (en) * 1976-07-29 1982-10-12 General Electric Company Fluid-cooled element
US4137619A (en) * 1977-10-03 1979-02-06 General Electric Company Method of fabricating composite structures for water cooled gas turbine components
US4616976A (en) * 1981-07-07 1986-10-14 Rolls-Royce Plc Cooled vane or blade for a gas turbine engine
US4767261A (en) * 1986-04-25 1988-08-30 Rolls-Royce Plc Cooled vane
EP0615055B1 (en) * 1993-03-11 1996-02-07 ROLLS-ROYCE plc A stator blade cooling
US5820336A (en) * 1994-11-11 1998-10-13 Mitsubishi Heavy Industries, Ltd. Gas turbine stationary blade unit
DE19601819A1 (en) * 1995-02-23 1996-08-29 Bmw Rolls Royce Gmbh Turbine blade arrangement with a cooled shroud

Also Published As

Publication number Publication date
DE19856199A1 (en) 2000-06-08
US6276897B1 (en) 2001-08-21
EP1008727A2 (en) 2000-06-14

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