IT997587B - IMPACT-COOLED TURBINE BLADES AND METHOD FOR PRODUCING - Google Patents

IMPACT-COOLED TURBINE BLADES AND METHOD FOR PRODUCING

Info

Publication number
IT997587B
IT997587B IT53459/73A IT5345973A IT997587B IT 997587 B IT997587 B IT 997587B IT 53459/73 A IT53459/73 A IT 53459/73A IT 5345973 A IT5345973 A IT 5345973A IT 997587 B IT997587 B IT 997587B
Authority
IT
Italy
Prior art keywords
impact
producing
turbine blades
cooled turbine
cooled
Prior art date
Application number
IT53459/73A
Other languages
Italian (it)
Original Assignee
Avco Corp
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 Avco Corp filed Critical Avco Corp
Application granted granted Critical
Publication of IT997587B publication Critical patent/IT997587B/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • 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
IT53459/73A 1972-10-31 1973-10-31 IMPACT-COOLED TURBINE BLADES AND METHOD FOR PRODUCING IT997587B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00302421A US3846041A (en) 1972-10-31 1972-10-31 Impingement cooled turbine blades and method of making same

Publications (1)

Publication Number Publication Date
IT997587B true IT997587B (en) 1975-12-30

Family

ID=23167669

Family Applications (1)

Application Number Title Priority Date Filing Date
IT53459/73A IT997587B (en) 1972-10-31 1973-10-31 IMPACT-COOLED TURBINE BLADES AND METHOD FOR PRODUCING

Country Status (6)

Country Link
US (1) US3846041A (en)
JP (1) JPS5249085B2 (en)
FR (1) FR2205097A5 (en)
GB (1) GB1441969A (en)
IT (1) IT997587B (en)
SE (1) SE389162B (en)

Families Citing this family (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH582305A5 (en) * 1974-09-05 1976-11-30 Bbc Sulzer Turbomaschinen
JPS5234111A (en) * 1975-09-10 1977-03-15 Toshiba Corp Turbine moving blade
US3994622A (en) * 1975-11-24 1976-11-30 United Technologies Corporation Coolable turbine blade
GB1564608A (en) * 1975-12-20 1980-04-10 Rolls Royce Means for cooling a surface by the impingement of a cooling fluid
GB1551678A (en) * 1978-03-20 1979-08-30 Rolls Royce Cooled rotor blade for a gas turbine engine
GB1552536A (en) * 1977-05-05 1979-09-12 Rolls Royce Rotor blade for a gas turbine engine
US4297077A (en) * 1979-07-09 1981-10-27 Westinghouse Electric Corp. Cooled turbine vane
US4314794A (en) * 1979-10-25 1982-02-09 Westinghouse Electric Corp. Transpiration cooled blade for a gas turbine engine
US4400137A (en) * 1980-12-29 1983-08-23 Elliott Turbomachinery Co., Inc. Rotor assembly and methods for securing a rotor blade therewithin and removing a rotor blade therefrom
US4451959A (en) * 1980-12-29 1984-06-05 Elliott Turbomachinery Company, Inc. Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom
US4407632A (en) * 1981-06-26 1983-10-04 United Technologies Corporation Airfoil pedestaled trailing edge region cooling configuration
US5352091A (en) * 1994-01-05 1994-10-04 United Technologies Corporation Gas turbine airfoil
DE4430302A1 (en) * 1994-08-26 1996-02-29 Abb Management Ag Impact-cooled wall part
US5741117A (en) * 1996-10-22 1998-04-21 United Technologies Corporation Method for cooling a gas turbine stator vane
US6193465B1 (en) * 1998-09-28 2001-02-27 General Electric Company Trapped insert turbine airfoil
US6453557B1 (en) * 2000-04-11 2002-09-24 General Electric Company Method of joining a vane cavity insert to a nozzle segment of a gas turbine
US6811378B2 (en) * 2002-07-31 2004-11-02 Power Systems Mfg, Llc Insulated cooling passageway for cooling a shroud of a turbine blade
US6769877B2 (en) 2002-10-18 2004-08-03 General Electric Company Undercut leading edge for compressor blades and related method
US6824352B1 (en) * 2003-09-29 2004-11-30 Power Systems Mfg, Llc Vane enhanced trailing edge cooling design
US7118326B2 (en) * 2004-06-17 2006-10-10 Siemens Power Generation, Inc. Cooled gas turbine vane
FR2899271B1 (en) 2006-03-29 2008-05-30 Snecma Sa DUSTBOARD AND COOLING SHIELD ASSEMBLY, TURBOMACHINE DISPENSER COMPRISING THE ASSEMBLY, TURBOMACHINE, METHOD OF ASSEMBLING AND REPAIRING THE ASSEMBLY
DE102007012320A1 (en) * 2007-03-09 2008-09-11 Rolls-Royce Deutschland Ltd & Co Kg Turbine blade with blade-formed microturbine nozzle
US7713029B1 (en) 2007-03-28 2010-05-11 Florida Turbine Technologies, Inc. Turbine blade with spar and shell construction
US7972113B1 (en) * 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
US8070421B2 (en) * 2008-03-26 2011-12-06 Siemens Energy, Inc. Mechanically affixed turbine shroud plug
US8033790B2 (en) * 2008-09-26 2011-10-11 Siemens Energy, Inc. Multiple piece turbine engine airfoil with a structural spar
US7967565B1 (en) * 2009-03-20 2011-06-28 Florida Turbine Technologies, Inc. Low cooling flow turbine blade
US8449249B2 (en) 2010-04-09 2013-05-28 Williams International Co., L.L.C. Turbine nozzle apparatus and associated method of manufacture
US8888455B2 (en) * 2010-11-10 2014-11-18 Rolls-Royce Corporation Gas turbine engine and blade for gas turbine engine
US9759072B2 (en) * 2012-08-30 2017-09-12 United Technologies Corporation Gas turbine engine airfoil cooling circuit arrangement
US9670797B2 (en) 2012-09-28 2017-06-06 United Technologies Corporation Modulated turbine vane cooling
US20150198050A1 (en) * 2014-01-15 2015-07-16 Siemens Energy, Inc. Internal cooling system with corrugated insert forming nearwall cooling channels for airfoil usable in a gas turbine engine
EP3189213A1 (en) * 2014-09-04 2017-07-12 Siemens Aktiengesellschaft Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of a gas turbine airfoil
US9840930B2 (en) 2014-09-04 2017-12-12 Siemens Aktiengesellschaft Internal cooling system with insert forming nearwall cooling channels in midchord cooling cavities of a gas turbine airfoil
US10443407B2 (en) * 2016-02-15 2019-10-15 General Electric Company Accelerator insert for a gas turbine engine airfoil
DE102016216858A1 (en) 2016-09-06 2018-03-08 Rolls-Royce Deutschland Ltd & Co Kg Blade for a turbomachine and method for assembling a blade for a turbomachine
US10626740B2 (en) 2016-12-08 2020-04-21 General Electric Company Airfoil trailing edge segment
FR3067389B1 (en) * 2017-04-10 2021-10-29 Safran TURBINE BLADE WITH AN IMPROVED STRUCTURE
US10851663B2 (en) * 2017-06-12 2020-12-01 General Electric Company Turbomachine rotor blade
FR3114762B1 (en) * 2020-10-06 2022-08-19 Safran Aircraft Engines Method of manufacturing a turbomachine compressor blade by compacting

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2779565A (en) * 1948-01-05 1957-01-29 Bruno W Bruckmann Air cooling of turbine blades
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
DE926397C (en) * 1952-09-25 1955-04-18 Ernst Heinkel Dr Dr Hollow blade, preferably for axially flowed turbines
US3446480A (en) * 1966-12-19 1969-05-27 Gen Motors Corp Turbine rotor
US3700348A (en) * 1968-08-13 1972-10-24 Gen Electric Turbomachinery blade structure
US3635587A (en) * 1970-06-02 1972-01-18 Gen Motors Corp Blade cooling liner

Also Published As

Publication number Publication date
DE2354693A1 (en) 1974-05-09
JPS4995011A (en) 1974-09-10
US3846041A (en) 1974-11-05
JPS5249085B2 (en) 1977-12-14
FR2205097A5 (en) 1974-05-24
GB1441969A (en) 1976-07-07
DE2354693B2 (en) 1975-07-03
SE389162B (en) 1976-10-25

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