GB1068280A - Aerofoil-shaped blade for use in a fluid flow machine such as a turbine - Google Patents

Aerofoil-shaped blade for use in a fluid flow machine such as a turbine

Info

Publication number
GB1068280A
GB1068280A GB52633/65A GB5263365A GB1068280A GB 1068280 A GB1068280 A GB 1068280A GB 52633/65 A GB52633/65 A GB 52633/65A GB 5263365 A GB5263365 A GB 5263365A GB 1068280 A GB1068280 A GB 1068280A
Authority
GB
United Kingdom
Prior art keywords
blade
sleeve
air
turbine
interior
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
GB52633/65A
Inventor
Glyn Twiston Davies
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 US597078A priority Critical patent/US3412979A/en
Publication of GB1068280A publication Critical patent/GB1068280A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Abstract

1,068,280. Turbine blades. ROLLSROYCE Ltd. Dec. 10, 1965, No. 52633/65. Addition to 1, 034, 260. Heading F1T. In a modification of the blade for a gas turbine engine described in Specification 1,034,260, a baffle plate 40 is welded to the sleeve 23 mounted within the blade so as to reduce the flow of cooling air in the space 31 between the sleeve and the blade wall 32 to a low pressure region at the radially inner portion of the blade. The air in space 31 exhausts through a radially extending aperture 33 at the blade trailing edge. Air is directed to the interior of sleeve 23 from an annular dilution air duct (19), Fig. 1 (not shown) by scoops (27, 28), the blade forming a turbine nozzle guide blade in an annular combustion chamber (12). Part of this air flows through apertures (30) Fig. 2 (not shown), in sleeve 23 to enter space 31 and the remainder flows through radially spaced stub pipes (35) from the interior of the sleeve to the exterior of the blade wall 32 to act as dilution air for the combustion products. A partition 24 divides the interior of the sleeve. The blade may also be used in a steam turbine.
GB52633/65A 1964-12-02 1965-12-10 Aerofoil-shaped blade for use in a fluid flow machine such as a turbine Expired GB1068280A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US597078A US3412979A (en) 1965-12-10 1966-11-25 Aerofoil-shaped blade for use in a fluid flow machine such as a turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB49101/64A GB1034260A (en) 1964-12-02 1964-12-02 Aerofoil-shaped blade for use in a fluid flow machine

Publications (1)

Publication Number Publication Date
GB1068280A true GB1068280A (en) 1967-05-10

Family

ID=10451151

Family Applications (2)

Application Number Title Priority Date Filing Date
GB49101/64A Expired GB1034260A (en) 1964-12-02 1964-12-02 Aerofoil-shaped blade for use in a fluid flow machine
GB52633/65A Expired GB1068280A (en) 1964-12-02 1965-12-10 Aerofoil-shaped blade for use in a fluid flow machine such as a turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB49101/64A Expired GB1034260A (en) 1964-12-02 1964-12-02 Aerofoil-shaped blade for use in a fluid flow machine

Country Status (5)

Country Link
US (1) US3353351A (en)
DE (2) DE1280618B (en)
FR (1) FR1454951A (en)
GB (2) GB1034260A (en)
MY (1) MY6800109A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11603766B1 (en) 2022-05-04 2023-03-14 Pratt & Whitney Canada Corp. Turbine stator vanes having inserts and splitter plates

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3412979A (en) * 1965-12-10 1968-11-26 Rolls Royce Aerofoil-shaped blade for use in a fluid flow machine such as a turbine
US3726604A (en) * 1971-10-13 1973-04-10 Gen Motors Corp Cooled jet flap vane
US4967562A (en) * 1988-12-12 1990-11-06 Sundstrand Corporation Turbine engine with high efficiency fuel atomization
US4989404A (en) * 1988-12-12 1991-02-05 Sundstrand Corporation Turbine engine with high efficiency fuel atomization
US4967563A (en) * 1988-12-12 1990-11-06 Sundstrand Corporation Turbine engine with high efficiency fuel atomization
US5220794A (en) * 1988-12-12 1993-06-22 Sundstrand Corporation Improved fuel injector for a gas turbine engine
US5027603A (en) * 1988-12-28 1991-07-02 Sundstrand Corporation Turbine engine with start injector
US5241818A (en) * 1989-07-13 1993-09-07 Sundstrand Corporation Fuel injector for a gas turbine engine
US5239818A (en) * 1992-03-30 1993-08-31 General Electric Company Dilution pole combustor and method
DE4309131A1 (en) * 1993-03-22 1994-09-29 Abb Management Ag Method and appliance for influencing the wake in furnace fittings
DE4336143C2 (en) * 1993-10-22 1995-11-16 Erich Wuerzinger Cooling process for turbomachinery
DE19651881A1 (en) * 1996-12-13 1998-06-18 Asea Brown Boveri Combustion chamber with integrated guide vanes
DE50107283D1 (en) * 2001-06-18 2005-10-06 Siemens Ag Gas turbine with a compressor for air
US7070386B2 (en) 2004-06-25 2006-07-04 United Technologies Corporation Airfoil insert with castellated end
WO2006053825A1 (en) * 2004-11-16 2006-05-26 Alstom Technology Ltd Gas turbine system and associated combustion chamber
US8713909B2 (en) * 2009-03-04 2014-05-06 United Technologies Corporation Elimination of unfavorable outflow margin
US10711702B2 (en) * 2015-08-18 2020-07-14 General Electric Company Mixed flow turbocore
US10578028B2 (en) 2015-08-18 2020-03-03 General Electric Company Compressor bleed auxiliary turbine
US10822963B2 (en) 2018-12-05 2020-11-03 Raytheon Technologies Corporation Axial flow cooling scheme with castable structural rib for a gas turbine engine
US20200182068A1 (en) * 2018-12-05 2020-06-11 United Technologies Corporation Axial flow cooling scheme with structural rib for a gas turbine engine

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2641040A (en) * 1948-01-02 1953-06-09 Esther C Goddard Means for cooling turbine blades by air
US2858100A (en) * 1952-02-01 1958-10-28 Stalker Dev Company Blade structure for turbines and the like
GB753224A (en) * 1953-04-13 1956-07-18 Rolls Royce Improvements in or relating to blading for turbines or compressors
DE1055884B (en) * 1954-03-02 1959-04-23 Bristol Aero Engines Ltd Flame tube for a combustion chamber of a gas turbine engine
US2920866A (en) * 1954-12-20 1960-01-12 A V Roe Canada Ltd Hollow air cooled sheet metal turbine blade
FR1177035A (en) * 1957-05-28 1959-04-20 Snecma Method and device for cooling machine parts
GB854135A (en) * 1958-03-05 1960-11-16 Rolls Royce Improvements in or relating to combustion equipment
DE1204021B (en) * 1959-04-27 1965-10-28 Rolls Royce Blade for axial flow machines, especially gas turbines
GB898368A (en) * 1959-06-23 1962-06-06 Rolls Royce Improved combustion chamber
US3242674A (en) * 1961-05-05 1966-03-29 Lucas Industries Ltd Liquid fuel combustion apparatus
GB938247A (en) * 1962-03-26 1963-10-02 Rolls Royce Gas turbine engine having cooled turbine blading

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11603766B1 (en) 2022-05-04 2023-03-14 Pratt & Whitney Canada Corp. Turbine stator vanes having inserts and splitter plates

Also Published As

Publication number Publication date
US3353351A (en) 1967-11-21
DE1280618B (en) 1968-10-17
DE1476892B2 (en) 1970-11-12
FR1454951A (en) 1966-02-11
MY6800109A (en) 1968-12-31
GB1034260A (en) 1966-06-29
DE1476892A1 (en) 1970-07-16

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