GB853328A - Method of and device for cooling the component elements of machines - Google Patents

Method of and device for cooling the component elements of machines

Info

Publication number
GB853328A
GB853328A GB15684/58A GB1568458A GB853328A GB 853328 A GB853328 A GB 853328A GB 15684/58 A GB15684/58 A GB 15684/58A GB 1568458 A GB1568458 A GB 1568458A GB 853328 A GB853328 A GB 853328A
Authority
GB
United Kingdom
Prior art keywords
blade
shell
cooling air
discharges
gas
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
GB15684/58A
Inventor
Otto Arthur David
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB853328A publication Critical patent/GB853328A/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
    • 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
    • F01D5/182—Transpiration 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

853,328. Gas-turbine blades. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. May 15, 1958 [May 28, 1957], No. 15684/58. Class 110 (3). In a method of cooling component elements of machines, particularly hollow gas-turbine blades, jets of cooling air or other gaseous fluid under, pressure are directed perpendicularly to the surface to be cooled from an inner chamber formed within the element and having small orifices through which the gaseous fluid discharges so as to impinge against the surface. The embodiment shown is a gas-turbine blade 1 formed of sheet metal and welded along its trailing edge to a rib 2 formed with apertures 3 through which cooling air can escape. A shell 4 is disposed within the blade 1 being closed at its end 5 adjacent the blade tip and formed with small projections by which it is spaced from the inner surface of the blade 1. The shell is formed with small orifices 8 through which cooling air under pressure supplied to the interior of the shell discharges to impinge perpendicularly on the inner surface of the blade wall adjacent its leading and trailing edges. The cooling air then flows through the passage 9 between the shell 4 and the blade 1 and discharges through the outlets 3.
GB15684/58A 1957-05-28 1958-05-15 Method of and device for cooling the component elements of machines Expired GB853328A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1092255X 1957-05-28

Publications (1)

Publication Number Publication Date
GB853328A true GB853328A (en) 1960-11-02

Family

ID=9615865

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15684/58A Expired GB853328A (en) 1957-05-28 1958-05-15 Method of and device for cooling the component elements of machines

Country Status (4)

Country Link
US (1) US3032314A (en)
DE (1) DE1092255B (en)
FR (1) FR1177035A (en)
GB (1) GB853328A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3301527A (en) * 1965-05-03 1967-01-31 Gen Electric Turbine diaphragm structure
DE1280618B (en) * 1964-12-02 1968-10-17 Rolls Royce Double-walled guide vane for gas turbine engines
EP0182588A1 (en) * 1984-11-15 1986-05-28 Westinghouse Electric Corporation Multi-chamber airfoil cooling insert for turbine vane
GB2439330A (en) * 2006-06-22 2007-12-27 Rolls Royce Plc Sheet metal aerofoil eg for turbomachinery

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1204021B (en) * 1959-04-27 1965-10-28 Rolls Royce Blade for axial flow machines, especially gas turbines
US3191908A (en) * 1961-05-02 1965-06-29 Rolls Royce Blades for fluid flow machines
US3171631A (en) * 1962-12-05 1965-03-02 Gen Motors Corp Turbine blade
US3319593A (en) * 1962-12-24 1967-05-16 Papst Hermann Boundary layer control
US3316714A (en) * 1963-06-20 1967-05-02 Rolls Royce Gas turbine engine combustion equipment
US3346235A (en) * 1963-12-23 1967-10-10 Papst Hermann Boundary layer control
US3240468A (en) * 1964-12-28 1966-03-15 Curtiss Wright Corp Transpiration cooled blades for turbines, compressors, and the like
FR1503348A (en) * 1965-12-11 1967-11-24 Daimler Benz Ag Blade for gas turbines, in particular for aircraft engines
GB1070480A (en) * 1966-02-01 1967-06-01 Rolls Royce Aerofoil shaped blade for a fluid flow machine such as a gas turbine engine
US3540810A (en) * 1966-03-17 1970-11-17 Gen Electric Slanted partition for hollow airfoil vane insert
US3574481A (en) * 1968-05-09 1971-04-13 James A Pyne Jr Variable area cooled airfoil construction for gas turbines
US3700348A (en) * 1968-08-13 1972-10-24 Gen Electric Turbomachinery blade structure
US3715170A (en) * 1970-12-11 1973-02-06 Gen Electric Cooled turbine blade
US3767322A (en) * 1971-07-30 1973-10-23 Westinghouse Electric Corp Internal cooling for turbine vanes
US3806275A (en) * 1972-08-30 1974-04-23 Gen Motors Corp Cooled airfoil
US3806276A (en) * 1972-08-30 1974-04-23 Gen Motors Corp Cooled turbine blade
CH584347A5 (en) * 1974-11-08 1977-01-31 Bbc Sulzer Turbomaschinen
GB1564608A (en) * 1975-12-20 1980-04-10 Rolls Royce Means for cooling a surface by the impingement of a cooling fluid
DE3003347A1 (en) * 1979-12-20 1981-06-25 BBC AG Brown, Boveri & Cie., Baden, Aargau COOLED WALL
US6237344B1 (en) 1998-07-20 2001-05-29 General Electric Company Dimpled impingement baffle
US6183192B1 (en) * 1999-03-22 2001-02-06 General Electric Company Durable turbine nozzle
US9719362B2 (en) * 2013-04-24 2017-08-01 Honeywell International Inc. Turbine nozzles and methods of manufacturing the same
EP2949871B1 (en) * 2014-05-07 2017-03-01 United Technologies Corporation Variable vane segment

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE432599A (en) * 1938-02-08
CH237475A (en) * 1942-06-09 1945-04-30 Vorkauf Heinrich Method and device for cooling gas turbine blades.
DE906636C (en) * 1944-01-23 1954-03-15 Herwig Kress Dr Ing Gas or exhaust gas turbines with hollow blade cooling
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means
BE498667A (en) * 1949-08-27
US2746671A (en) * 1950-04-14 1956-05-22 United Aircraft Corp Compressor deicing and thrust balancing arrangement
DE949954C (en) * 1952-02-09 1956-09-27 Helmut Reining Device on cooling frames for Siemens-Martin ovens or other industrial ovens
US2787049A (en) * 1952-05-23 1957-04-02 Stalkcr Dev Company Process of fabricating blades for turbines, compressors and the like
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
GB740597A (en) * 1953-11-07 1955-11-16 Gen Motors Corp Improvements relating to gas turbine or compressor blades
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
GB753224A (en) * 1953-04-13 1956-07-18 Rolls Royce Improvements in or relating to blading for turbines or compressors
US2859011A (en) * 1953-07-27 1958-11-04 Gen Motors Corp Turbine bucket and liner
US2851216A (en) * 1954-01-13 1958-09-09 Schwarzkopf Dev Co Device adapted for respiration cooling and process of making same

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1280618B (en) * 1964-12-02 1968-10-17 Rolls Royce Double-walled guide vane for gas turbine engines
US3301527A (en) * 1965-05-03 1967-01-31 Gen Electric Turbine diaphragm structure
EP0182588A1 (en) * 1984-11-15 1986-05-28 Westinghouse Electric Corporation Multi-chamber airfoil cooling insert for turbine vane
GB2439330A (en) * 2006-06-22 2007-12-27 Rolls Royce Plc Sheet metal aerofoil eg for turbomachinery
GB2439330B (en) * 2006-06-22 2008-09-17 Rolls Royce Plc Aerofoil
US7819627B2 (en) 2006-06-22 2010-10-26 Rolls-Royce Plc Aerofoil

Also Published As

Publication number Publication date
DE1092255B (en) 1960-11-03
FR1177035A (en) 1959-04-20
US3032314A (en) 1962-05-01

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