GB1322802A - Gas turbine engines and engine subassemblies including a temperautre control arrangement for a row of turbine blades therein - Google Patents

Gas turbine engines and engine subassemblies including a temperautre control arrangement for a row of turbine blades therein

Info

Publication number
GB1322802A
GB1322802A GB945870A GB945870A GB1322802A GB 1322802 A GB1322802 A GB 1322802A GB 945870 A GB945870 A GB 945870A GB 945870 A GB945870 A GB 945870A GB 1322802 A GB1322802 A GB 1322802A
Authority
GB
United Kingdom
Prior art keywords
temperautre
row
gas turbine
control arrangement
turbine blades
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.)
Expired
Application number
GB945870A
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 Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority claimed from GB4156370A external-priority patent/GB1322801A/en
Publication of GB1322802A publication Critical patent/GB1322802A/en
Expired 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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Abstract

1322802 Gas turbine blades GENERAL ELECTRIC CO 28 Aug 1970 [1 Dec 1969] 9458/73 Divided out of 1322801 Heading FIT The subject matter of the Specification is the same as that of the parent, Specification 1322801, but the claims are concerned with other features of the cooled stator vane assembly.
GB945870A 1969-12-01 1970-08-28 Gas turbine engines and engine subassemblies including a temperautre control arrangement for a row of turbine blades therein Expired GB1322802A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US88125469A 1969-12-01 1969-12-01
GB4156370A GB1322801A (en) 1969-12-01 1970-08-28 Vane assembly

Publications (1)

Publication Number Publication Date
GB1322802A true GB1322802A (en) 1973-07-11

Family

ID=26264705

Family Applications (1)

Application Number Title Priority Date Filing Date
GB945870A Expired GB1322802A (en) 1969-12-01 1970-08-28 Gas turbine engines and engine subassemblies including a temperautre control arrangement for a row of turbine blades therein

Country Status (1)

Country Link
GB (1) GB1322802A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2132703A (en) * 1982-12-15 1984-07-11 Onera (Off Nat Aerospatiale) Cooling ceramic blades of turbomachines
GB2210415A (en) * 1987-09-25 1989-06-07 Toshiba Kk Turbine vane with cooling features
GB2223276A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Cooling turbine blade shrouds
GB2244520A (en) * 1990-05-31 1991-12-04 Gen Electric Nozzle assembly for a gas turbine engine
US20190195086A1 (en) * 2017-12-22 2019-06-27 United Technologies Corporation Platform flow turning elements for gas turbine engine components
US10683760B2 (en) 2012-10-17 2020-06-16 United Technologies Corporation Gas turbine engine component platform cooling

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2132703A (en) * 1982-12-15 1984-07-11 Onera (Off Nat Aerospatiale) Cooling ceramic blades of turbomachines
GB2210415A (en) * 1987-09-25 1989-06-07 Toshiba Kk Turbine vane with cooling features
GB2210415B (en) * 1987-09-25 1992-04-22 Toshiba Kk Gas turbine vane
GB2223276A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Cooling turbine blade shrouds
GB2223276B (en) * 1988-09-30 1992-09-02 Rolls Royce Plc Turbine aerofoil blade
GB2244520A (en) * 1990-05-31 1991-12-04 Gen Electric Nozzle assembly for a gas turbine engine
FR2662742A1 (en) * 1990-05-31 1991-12-06 Gen Electric COOLING DEVICE FOR OVERFLOWING NOZZLE.
US5197852A (en) * 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
US10683760B2 (en) 2012-10-17 2020-06-16 United Technologies Corporation Gas turbine engine component platform cooling
US20190195086A1 (en) * 2017-12-22 2019-06-27 United Technologies Corporation Platform flow turning elements for gas turbine engine components
US10655496B2 (en) * 2017-12-22 2020-05-19 United Technologies Corporation Platform flow turning elements for gas turbine engine components

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Legal Events

Date Code Title Description
PS Patent sealed
PE20 Patent expired after termination of 20 years