GB1235545A - Improvements in or relating to blades or vanes for fluid flow machines - Google Patents

Improvements in or relating to blades or vanes for fluid flow machines

Info

Publication number
GB1235545A
GB1235545A GB43367/68A GB4336768A GB1235545A GB 1235545 A GB1235545 A GB 1235545A GB 43367/68 A GB43367/68 A GB 43367/68A GB 4336768 A GB4336768 A GB 4336768A GB 1235545 A GB1235545 A GB 1235545A
Authority
GB
United Kingdom
Prior art keywords
bellows
blade
camber
ties
sept
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
GB43367/68A
Inventor
John Henry Ellinger
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 GB43367/68A priority Critical patent/GB1235545A/en
Priority to US855668A priority patent/US3614260A/en
Priority to FR6930565A priority patent/FR2017885A1/fr
Priority to DE1946086A priority patent/DE1946086C3/en
Publication of GB1235545A publication Critical patent/GB1235545A/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
    • 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
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • 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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • 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
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/05—Variable camber or chord length

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Devices (AREA)

Abstract

1,235,545. Axial-flow fans; jet propulsion plant. ROLLS-ROYCE Ltd. Sept. 15, 1969 [Sept.12, 1968J, No.43367/68. Headings F1C; F1J. A variable camber blade, e.g. for the outlet stator assembly of a ducted fan in a gas turbine engine, comprises a rigid metal spine portion 16 and a thin sheet metal member 17 of hairpin shaped cross-section surrounding the nose of portion 16 to define the forward surfaces of the blade. The member 17 is rigidly attached to the convex flank of portion 16 at 18 but on the concave flank is attached at 19 to actuation means for varying the camber of the member 17. The actuation means comprise radially spaced oil filled bellows 22 embedded in the portion 16 and each connected to member 17 by a spring link 24. To reduce the blade camber, e.g. in an emergency, pressure oil is supplied through line 23 to the bellows 22 so that the latter expand to move the member 17 from the position 26B into the position 26A. The bellows 22 are arranged to operate as compression springs so that should the oil supply fail they automatically return the member 17 to the position 26B. The bellows 22 are assisted by further actuating bellows 25 interposed in the space between the forward flanks of the portion 16 and the internal surface of the member 17 and connected to a supply of compressed air and plastic foam, the latter helping to reduce vibrations within the bellows 25. To stiffen the member 17 the opposite flanks thereof are interconnected by ties 20, 21 passing freely through slots in the portion 16. The ties 20, 21 are nicked at their points of attachment to member 17 so that they tend to hinge at these points rather than bending over their complete length and distorting the surface of member 17. The variable camber arrangement can also be applied to the trailing edge of the blade. In the ducted fan engine, Fig. 1 (not shown), the variable camber blades (15) support a gas generator section (11) within a fan cowling (14).
GB43367/68A 1968-09-12 1968-09-12 Improvements in or relating to blades or vanes for fluid flow machines Expired GB1235545A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB43367/68A GB1235545A (en) 1968-09-12 1968-09-12 Improvements in or relating to blades or vanes for fluid flow machines
US855668A US3614260A (en) 1968-09-12 1969-09-05 Blades or vanes for fluid flow machines
FR6930565A FR2017885A1 (en) 1968-09-12 1969-09-09
DE1946086A DE1946086C3 (en) 1968-09-12 1969-09-11 Blade for gas turbine jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB43367/68A GB1235545A (en) 1968-09-12 1968-09-12 Improvements in or relating to blades or vanes for fluid flow machines

Publications (1)

Publication Number Publication Date
GB1235545A true GB1235545A (en) 1971-06-16

Family

ID=10428464

Family Applications (1)

Application Number Title Priority Date Filing Date
GB43367/68A Expired GB1235545A (en) 1968-09-12 1968-09-12 Improvements in or relating to blades or vanes for fluid flow machines

Country Status (4)

Country Link
US (1) US3614260A (en)
DE (1) DE1946086C3 (en)
FR (1) FR2017885A1 (en)
GB (1) GB1235545A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7753654B2 (en) 2006-01-21 2010-07-13 Rolls-Royce Plc Aerofoils for gas turbine engines
EP2522809A2 (en) 2011-05-13 2012-11-14 Rolls-Royce plc A method of reducing asymmetric fluid flow effects in a passage

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3844677A (en) * 1971-11-01 1974-10-29 Gen Electric Blunted leading edge fan blade for noise reduction
US4571157A (en) * 1981-10-02 1986-02-18 Karl Eickmann Propeller with an interior arrangement to variate the pitch
US4619585A (en) * 1983-07-28 1986-10-28 Joe Storm Wind turbine apparatus
DE3540401A1 (en) * 1985-11-14 1987-05-21 Mtu Muenchen Gmbh Vane ring for turbo machines, especially for gas turbines
DE3710321C1 (en) * 1987-03-28 1988-06-01 Mtu Muenchen Gmbh Fan blade, especially for prop fan engines
US4802823A (en) * 1988-05-09 1989-02-07 Avco Corporation Stress relief support structures and assemblies
US5207558A (en) * 1991-10-30 1993-05-04 The United States Of America As Represented By The Secretary Of The Air Force Thermally actuated vane flow control
NZ511661A (en) * 2001-05-11 2003-09-26 Graham Bond Grove An improved aerofoil
DE10256008B3 (en) * 2002-11-30 2004-08-12 Universität Kassel Turbomachine e.g. compressor or water turbine, with relative movement of blade rear edges of guide grid blades upon alignment of blade front edges with flow direction
US6763899B1 (en) * 2003-02-21 2004-07-20 Schlumberger Technology Corporation Deformable blades for downhole applications in a wellbore
GB0519502D0 (en) 2005-09-24 2005-11-02 Rolls Royce Plc Vane assembly
US8162603B2 (en) * 2009-01-30 2012-04-24 General Electric Company Vane frame for a turbomachine and method of minimizing weight thereof
US9650903B2 (en) * 2009-08-28 2017-05-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
US20110232291A1 (en) * 2010-03-26 2011-09-29 General Electric Company System and method for an exhaust diffuser
US9789636B2 (en) 2013-06-03 2017-10-17 United Technologies Corporation Rigid and rotatable vanes molded within variably shaped flexible airfoils
US9267427B2 (en) * 2013-06-11 2016-02-23 Ford Global Technologies, Llc Variable geometry turbine vane
DE102014216266A1 (en) 2014-07-23 2016-01-28 Ebm-Papst Mulfingen Gmbh & Co. Kg Shovel for a wheel
US10502086B2 (en) * 2016-03-16 2019-12-10 General Electric Company System and method for actuating gas turbine engine components using integrated jamming devices
ES2825025T3 (en) * 2018-01-29 2021-05-14 Siemens Gamesa Renewable Energy As Trailing edge assembly
US11465735B2 (en) 2019-06-11 2022-10-11 David Thomas BIRKENSTOCK Aircraft wing with bellows assembly for optimizing a boundary layer control system
US11971004B2 (en) * 2021-10-21 2024-04-30 Schlumberger Technology Corporation Adjustable fins on a turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT100913B (en) * 1924-09-25 1925-09-10 Istvan Eder Bucket for centrifugal pumps.
US2616509A (en) * 1946-11-29 1952-11-04 Thomas Wilfred Pneumatic airfoil
DE961742C (en) * 1952-05-25 1957-04-11 Kloeckner Humboldt Deutz Ag Device for adjusting the blading of flow machines
US2967573A (en) * 1954-10-14 1961-01-10 Goodyear Aircraft Corp Pneumatic airfoil
US3042371A (en) * 1958-09-04 1962-07-03 United Aircraft Corp Variable camber balding
US3158338A (en) * 1963-02-18 1964-11-24 Walton W Cushman Sustaining airfoils having variable configurations to vary lift characteristics

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7753654B2 (en) 2006-01-21 2010-07-13 Rolls-Royce Plc Aerofoils for gas turbine engines
EP2522809A2 (en) 2011-05-13 2012-11-14 Rolls-Royce plc A method of reducing asymmetric fluid flow effects in a passage
US9091174B2 (en) 2011-05-13 2015-07-28 Rolls-Royce Plc Method of reducing asymmetric fluid flow effects in a passage

Also Published As

Publication number Publication date
DE1946086A1 (en) 1970-07-30
US3614260A (en) 1971-10-19
DE1946086B2 (en) 1973-09-20
DE1946086C3 (en) 1974-04-25
FR2017885A1 (en) 1970-05-22

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee