GB1023766A - Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber - Google Patents

Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber

Info

Publication number
GB1023766A
GB1023766A GB621764A GB621764A GB1023766A GB 1023766 A GB1023766 A GB 1023766A GB 621764 A GB621764 A GB 621764A GB 621764 A GB621764 A GB 621764A GB 1023766 A GB1023766 A GB 1023766A
Authority
GB
United Kingdom
Prior art keywords
links
vane
camber
gear teeth
hinge pin
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
GB621764A
Inventor
William Henry Lindsey
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.)
Bristol Siddeley Engines Ltd
Original Assignee
Bristol Siddeley Engines Ltd
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 Bristol Siddeley Engines Ltd filed Critical Bristol Siddeley Engines Ltd
Priority to GB621764A priority Critical patent/GB1023766A/en
Publication of GB1023766A publication Critical patent/GB1023766A/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/44—Varying camber
    • B64C3/48—Varying camber by relatively-movable parts of wing structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B64C3/44—Varying camber
    • B64C3/50—Varying camber by leading or trailing edge flaps
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,023,766. Adjustable - camber aerofoils. BRISTOL SIDDELEY ENGINES Ltd. Feb. 15, 1965 [Feb. 14, 1964], No. 6217/64. Heading B7G. [Also in Division F1] The invention relates to a member of aerodynamic cross-sectional shape having a variable camber such as a guide vane, a blade for a compressor or turbine, or an aerofoil, the invention being described with reference to a guide vane which supports a discharge cone 11 within an exhaust duct 12 leading from a reversible centripetal turbine. The guide vane comprises an adjustable leading portion 1 and a fixed trailing portion 2 the adjacent longitudinally-extending edges of the two portions being formed of convex shape on which are formed interengaging longitudinally-extending gear teeth 5, (Fig. 2, not shown). Aligned pairs of notches are also formed along the adjacent edges of the two portions 1 and 2 and elliptical section link members 3 and 4 are disposed in the notches, hinge pins 6 and 8 extending through the vane portion 2 and 1 and also through the links 3 and 4, the hinge pin 6 being secured to the links 3 and 4 and carrying at its outer end an actuating lever 7. The hinge pin 8 is located against endwise movement by screwed stops 9. Thus as the lever 7 is moved the links 3 and 4 move the leading portion 1 and the gear teeth 5 cause the leading portion to pivot about the hinge pin 8 so as to vary the camber of the vane. The links 3 are formed with longitudinal extensions which cover the interengaging gear teeth and act to form a smooth surface at the convex or concave surface of the vane.
GB621764A 1964-02-14 1964-02-14 Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber Expired GB1023766A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB621764A GB1023766A (en) 1964-02-14 1964-02-14 Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB621764A GB1023766A (en) 1964-02-14 1964-02-14 Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber

Publications (1)

Publication Number Publication Date
GB1023766A true GB1023766A (en) 1966-03-23

Family

ID=9810543

Family Applications (1)

Application Number Title Priority Date Filing Date
GB621764A Expired GB1023766A (en) 1964-02-14 1964-02-14 Improvements in or relating to a member of aerodynamic cross-sectional shape having a variable camber

Country Status (1)

Country Link
GB (1) GB1023766A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1985000573A1 (en) * 1983-07-15 1985-02-14 Wildensteiner Otto M Reversible camber airfoil
EP0223194A1 (en) * 1985-11-14 1987-05-27 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Variable guide vane for a turbo machine
FR2607188A1 (en) * 1986-11-26 1988-05-27 Snecma TURBOMACHINE INPUT CASING WITH RADIANT ARMS
JP2017155748A (en) * 2016-03-04 2017-09-07 ゼネラル・エレクトリック・カンパニイ Modulated hybrid variable area turbine nozzle for gas turbine engine
WO2023099117A1 (en) * 2021-12-01 2023-06-08 Friedrich Grimm Device comprising an asymmetrical adjustable wing profile

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1985000573A1 (en) * 1983-07-15 1985-02-14 Wildensteiner Otto M Reversible camber airfoil
EP0223194A1 (en) * 1985-11-14 1987-05-27 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Variable guide vane for a turbo machine
US4741665A (en) * 1985-11-14 1988-05-03 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Guide vane ring for turbo-engines, especially gas turbines
FR2607188A1 (en) * 1986-11-26 1988-05-27 Snecma TURBOMACHINE INPUT CASING WITH RADIANT ARMS
EP0274293A1 (en) * 1986-11-26 1988-07-13 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Air intake housing for a turbo machine with radial struts
US4821758A (en) * 1986-11-26 1989-04-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M A." Turbine plant intake housing
JP2017155748A (en) * 2016-03-04 2017-09-07 ゼネラル・エレクトリック・カンパニイ Modulated hybrid variable area turbine nozzle for gas turbine engine
WO2023099117A1 (en) * 2021-12-01 2023-06-08 Friedrich Grimm Device comprising an asymmetrical adjustable wing profile

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