GB1404757A - Gas turbine engine blades - Google Patents

Gas turbine engine blades

Info

Publication number
GB1404757A
GB1404757A GB3977771A GB3977771A GB1404757A GB 1404757 A GB1404757 A GB 1404757A GB 3977771 A GB3977771 A GB 3977771A GB 3977771 A GB3977771 A GB 3977771A GB 1404757 A GB1404757 A GB 1404757A
Authority
GB
United Kingdom
Prior art keywords
blade
insert
coolant
gas turbine
aug
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
GB3977771A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3977771A priority Critical patent/GB1404757A/en
Priority to DE19722241191 priority patent/DE2241191B2/en
Priority to AU45873/72A priority patent/AU466679B2/en
Priority to IT5233672A priority patent/IT962211B/en
Priority to FR7230137A priority patent/FR2150475B1/fr
Priority to SE1098772A priority patent/SE380065B/xx
Priority to JP8465872A priority patent/JPS5345447B2/ja
Publication of GB1404757A publication Critical patent/GB1404757A/en
Expired legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J5/00—Manufacture of articles or shaped materials containing macromolecular substances
    • C08J5/04—Reinforcing macromolecular compounds with loose or coherent fibrous material
    • C08J5/06—Reinforcing macromolecular compounds with loose or coherent fibrous material using pretreated fibrous materials
    • C08J5/08—Reinforcing macromolecular compounds with loose or coherent fibrous material using pretreated fibrous materials glass fibres
    • 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
    • C—CHEMISTRY; METALLURGY
    • C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
    • C08J—WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H
    • C08J2321/00—Characterised by the use of unspecified rubbers

Abstract

1404757 Gas turbine blades ROLLS-ROYCE (1971) Ltd 25 Aug 1972 [25 Aug 1971] 39777/71 Heading F1T A hollow gas turbine blade contains a sheet-like solid insert 14 spaced from the blade walls by inclined fins 16 defining passages forming a spirallike coolant fluid flow-path around and along the insert. The fins 16 and insert locating pimples (15), indicated by crosses, may be integral with the blade walls. Insert 14 is brazed at one end to the blade but is otherwise unattached to permit differential expansion. Some of the coolant leaves the spiral path through holes (20), 21 in the leading and trailing edges 10, 11 respectively, the path decreasing in flow area towards blade tip 12 to compensate for the reduced flow. The remaining coolant escapes through holes (22) adjacent tip 12 and flows along channels (24) in the underside of shroud (23). The coolant may be liquid, air or other gas. The blade may be for a rotor or stator.
GB3977771A 1971-08-25 1971-08-25 Gas turbine engine blades Expired GB1404757A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
GB3977771A GB1404757A (en) 1971-08-25 1971-08-25 Gas turbine engine blades
DE19722241191 DE2241191B2 (en) 1971-08-25 1972-08-22 Internally cooled gas turbine blade
AU45873/72A AU466679B2 (en) 1971-08-25 1972-08-23 Gas turbine engine blades
IT5233672A IT962211B (en) 1971-08-25 1972-08-24 ROTOR FOR GAS TURBINES
FR7230137A FR2150475B1 (en) 1971-08-25 1972-08-24
SE1098772A SE380065B (en) 1971-08-25 1972-08-24
JP8465872A JPS5345447B2 (en) 1971-08-25 1972-08-25

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3977771A GB1404757A (en) 1971-08-25 1971-08-25 Gas turbine engine blades

Publications (1)

Publication Number Publication Date
GB1404757A true GB1404757A (en) 1975-09-03

Family

ID=10411441

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3977771A Expired GB1404757A (en) 1971-08-25 1971-08-25 Gas turbine engine blades

Country Status (7)

Country Link
JP (1) JPS5345447B2 (en)
AU (1) AU466679B2 (en)
DE (1) DE2241191B2 (en)
FR (1) FR2150475B1 (en)
GB (1) GB1404757A (en)
IT (1) IT962211B (en)
SE (1) SE380065B (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215431A (en) * 1991-06-25 1993-06-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Cooled turbine guide vane
GB2272731A (en) * 1992-11-18 1994-05-25 Snecma Hollow blade for the fan or compressor of a turbomachine
WO2005083235A1 (en) * 2004-02-27 2005-09-09 Siemens Aktiengesellschaft Blade or vane for a turbomachine
US9206695B2 (en) 2012-09-28 2015-12-08 Solar Turbines Incorporated Cooled turbine blade with trailing edge flow metering
US9228439B2 (en) 2012-09-28 2016-01-05 Solar Turbines Incorporated Cooled turbine blade with leading edge flow redirection and diffusion
US9314838B2 (en) 2012-09-28 2016-04-19 Solar Turbines Incorporated Method of manufacturing a cooled turbine blade with dense cooling fin array
US11098602B2 (en) * 2018-04-17 2021-08-24 Doosan Heavy Industries & Construction Co., Ltd. Turbine vane equipped with insert support

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4515523A (en) * 1983-10-28 1985-05-07 Westinghouse Electric Corp. Cooling arrangement for airfoil stator vane trailing edge
JPH06102963B2 (en) * 1983-12-22 1994-12-14 株式会社東芝 Gas turbine air cooling blade
FR2672338B1 (en) * 1991-02-06 1993-04-16 Snecma TURBINE BLADE PROVIDED WITH A COOLING SYSTEM.
FR2743391B1 (en) * 1996-01-04 1998-02-06 Snecma REFRIGERATED BLADE OF TURBINE DISTRIBUTOR
EP1925780A1 (en) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Blade for an axial-flow turbine
RU2014125561A (en) * 2011-11-25 2015-12-27 Сименс Акциенгезелльшафт AERODYNAMIC PROFILE WITH COOLING CHANNELS
WO2016133511A1 (en) * 2015-02-19 2016-08-25 Siemens Energy, Inc. Turbine airfoil with an internal cooling system formed from an interrupted internal wall forming inactive cavities
US9995221B2 (en) * 2015-12-22 2018-06-12 General Electric Company Staged fuel and air injection in combustion systems of gas turbines
JP2021050688A (en) * 2019-09-26 2021-04-01 川崎重工業株式会社 Turbine blade

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3314650A (en) * 1965-07-20 1967-04-18 Gen Motors Corp Cooled blade

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215431A (en) * 1991-06-25 1993-06-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Cooled turbine guide vane
GB2272731A (en) * 1992-11-18 1994-05-25 Snecma Hollow blade for the fan or compressor of a turbomachine
WO2005083235A1 (en) * 2004-02-27 2005-09-09 Siemens Aktiengesellschaft Blade or vane for a turbomachine
US7674092B2 (en) 2004-02-27 2010-03-09 Siemens Aktiengesellschaft Blade or vane for a turbomachine
US9206695B2 (en) 2012-09-28 2015-12-08 Solar Turbines Incorporated Cooled turbine blade with trailing edge flow metering
US9228439B2 (en) 2012-09-28 2016-01-05 Solar Turbines Incorporated Cooled turbine blade with leading edge flow redirection and diffusion
US9314838B2 (en) 2012-09-28 2016-04-19 Solar Turbines Incorporated Method of manufacturing a cooled turbine blade with dense cooling fin array
US11098602B2 (en) * 2018-04-17 2021-08-24 Doosan Heavy Industries & Construction Co., Ltd. Turbine vane equipped with insert support

Also Published As

Publication number Publication date
DE2241191A1 (en) 1973-03-08
SE380065B (en) 1975-10-27
JPS5345447B2 (en) 1978-12-06
DE2241191B2 (en) 1980-11-06
AU466679B2 (en) 1975-11-06
AU4587372A (en) 1974-03-07
IT962211B (en) 1973-12-20
FR2150475A1 (en) 1973-04-06
FR2150475B1 (en) 1976-05-21
JPS4829917A (en) 1973-04-20

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee