GB1034260A - Aerofoil-shaped blade for use in a fluid flow machine - Google Patents

Aerofoil-shaped blade for use in a fluid flow machine

Info

Publication number
GB1034260A
GB1034260A GB49101/64A GB4910164A GB1034260A GB 1034260 A GB1034260 A GB 1034260A GB 49101/64 A GB49101/64 A GB 49101/64A GB 4910164 A GB4910164 A GB 4910164A GB 1034260 A GB1034260 A GB 1034260A
Authority
GB
United Kingdom
Prior art keywords
blade
fluid
wall
air
leading edge
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
GB49101/64A
Inventor
Arthur Bill
Thomas Steel
Michael Poucher
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 GB49101/64A priority Critical patent/GB1034260A/en
Priority to US508683A priority patent/US3353351A/en
Priority to FR40128A priority patent/FR1454951A/en
Priority to DER42097A priority patent/DE1280618B/en
Priority to GB52633/65A priority patent/GB1068280A/en
Publication of GB1034260A publication Critical patent/GB1034260A/en
Priority to DE19661476892 priority patent/DE1476892B2/en
Priority to FR86823A priority patent/FR91287E/en
Priority to MY1968109A priority patent/MY6800109A/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

1,034,260. Turbine blades; gas turbine combustion chambers. ROLLS-ROYCE Ltd. Dec. 2, 1964, No. 49101/64. Headings F1L and F1T. A gas or steam turbine blade has an external wall, means surrounded by and spaced from the external wall for receiving fluid and directing some of the fluid over the interior of the wall to effect cooling, the wall having at least one aperture enabling the cooling fluid to escape from the space between the fluid receiving means and the wall, and passage defining means wherein a portion of the fluid entering the fluid receiving means passes across the space directly to the exterior of the blade without mixing with the fluid in the space. A gas turbine engine annular combustion chamber 12, Fig. 2, is supplied with primary and secondary air through spaced inlets 17, 18 respectively. The secondary air flows to the outer ends of hollow nozzle guide blades 20 mounted within the combustion chamber. Each blade 20, Fig. 3 (not shown), has a hollow internal sleeve 27 spaced from its outer wall 20a and a partition having an air scoop 21 dividing the interior of sleeve 27 into chambers 28, 29. Some of the secondary airflow is directed by scoop 21 into chamber 28 to flow through apertures 32 onto the blade leading edge to effect cooling, this air finally leaving through apertures 25 adjacent the trailing edge. A further portion of the secondary air is directed by a second scoop 22 into chamber 29 from which this air enters the combustion chamber through tubes 31 and holes 23 in the blade wall 20a to dilute the combustion products. Strips 26 are attached to blade 20 adjacent its leading edge so as to deflect the incoming primary air radially inwards to promote mixing with the fuel supplied. In a modification, cooling air apertures are also provided in the blade leading edge, in which case the strips 26 are connected by a web and disposed slightly upstream of the leading edge.
GB49101/64A 1964-12-02 1964-12-02 Aerofoil-shaped blade for use in a fluid flow machine Expired GB1034260A (en)

Priority Applications (8)

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
US508683A US3353351A (en) 1964-12-02 1965-11-19 Aerofoil-shaped fluid-cooled blade for a fluid flow machine
FR40128A FR1454951A (en) 1964-12-02 1965-11-29 New type of blade for gas or steam turbines
DER42097A DE1280618B (en) 1964-12-02 1965-11-30 Double-walled guide vane for gas turbine engines
GB52633/65A GB1068280A (en) 1964-12-02 1965-12-10 Aerofoil-shaped blade for use in a fluid flow machine such as a turbine
DE19661476892 DE1476892B2 (en) 1964-12-02 1966-11-25 Double-walled guide vane for gas turbine engines
FR86823A FR91287E (en) 1964-12-02 1966-12-09 New type of blade for gas or steam turbines
MY1968109A MY6800109A (en) 1964-12-02 1968-12-31 Method of repairing a metallic hull for buoyant vessel

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
GB1034260A true GB1034260A (en) 1966-06-29

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 After (1)

Application Number Title Priority Date Filing Date
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

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
US3726604A (en) * 1971-10-13 1973-04-10 Gen Motors Corp Cooled jet flap vane

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
US5220794A (en) * 1988-12-12 1993-06-22 Sundstrand Corporation Improved fuel injector for a gas turbine engine
US4967563A (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
US4967562A (en) * 1988-12-12 1990-11-06 Sundstrand Corporation Turbine engine with high efficiency fuel atomization
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
EP1270874B1 (en) * 2001-06-18 2005-08-31 Siemens Aktiengesellschaft Gas turbine with an air compressor
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
US11603766B1 (en) 2022-05-04 2023-03-14 Pratt & Whitney Canada Corp. Turbine stator vanes having inserts and splitter plates

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
US3726604A (en) * 1971-10-13 1973-04-10 Gen Motors Corp Cooled jet flap vane

Also Published As

Publication number Publication date
DE1476892A1 (en) 1970-07-16
MY6800109A (en) 1968-12-31
GB1068280A (en) 1967-05-10
DE1476892B2 (en) 1970-11-12
DE1280618B (en) 1968-10-17
US3353351A (en) 1967-11-21
FR1454951A (en) 1966-02-11

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