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 camberInfo
- 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
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.
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)
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 MàNchen 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 |
-
1964
- 1964-02-14 GB GB621764A patent/GB1023766A/en not_active Expired
Cited By (8)
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 MàNchen 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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