GB946995A - Fluid flow machine such as a gas turbine engine - Google Patents

Fluid flow machine such as a gas turbine engine

Info

Publication number
GB946995A
GB946995A GB1865461A GB1865461A GB946995A GB 946995 A GB946995 A GB 946995A GB 1865461 A GB1865461 A GB 1865461A GB 1865461 A GB1865461 A GB 1865461A GB 946995 A GB946995 A GB 946995A
Authority
GB
United Kingdom
Prior art keywords
vanes
pivoted
platforms
casing
blades
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
GB1865461A
Inventor
Kenneth Edward George Bracey
Geoffrey Light Wilde
Edward Reginald Brealey
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 GB1865461A priority Critical patent/GB946995A/en
Priority to DER32764A priority patent/DE1224990B/en
Priority to FR898386A priority patent/FR1325261A/en
Publication of GB946995A publication Critical patent/GB946995A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

946,995. Turbines. ROLLS-ROYCE Ltd. May 16, 1962 [May 23, 1961], No. 18654/61. Heading F1T. A fluid flow machine has a ring of blades each of which, at its root and at its tip, has a platform which is mounted in a casing for pivotal movement between two extreme angular positions, each platform being of a shape such that in each of the extreme angular positions the platforms of adjacent blades contact each other to prevent fluid from passing between adjacent platforms and thus around the blades, means being provided for effecting pivotal movement of the blades. A gas turbine engine has nozzle guide vanes 15 having platforms 17, 18 with flats 20, 21 of which the flat 20 is of greater length than the flat 21 and is disposed alongside a flat 21 of an adjacent nozzle guide vane 15. The platforms 17, 18 are pivoted in casings 26, 27, sealing of the curved portions 22, 23 being effected by labyrinths 24, 25. Leakage across the vanes 15 is prevented by contact between either the upstream or downstream ends of adjacent flats 20, 21. The casing 27 is spaced from the engine casing 10 by an annular space 30 supplied with compressed air. Pivotal movement of the vanes 15 is effected by a fixed piston 32, forming part of the casing 27, and an axially movable cylinder 33 having an axial annular extension 34. Movement of cylinder 33 is controlled by a two-way valve 40 connected to compartments 35, 36 in cylinder 33, to compressed air in space 30 and to atmosphere. Annular extension 34 has fingers each of which is pivoted to an arm attached to a hollow quill shaft 43 welded to platform 18 of vane 15. In a modification movement of the vanes 15 is effected by pneumatic rams 50, Fig. 6, each having a piston 51 pivoted to an axially extending lever 53 whose downstream end is pivoted to a fixed structure at 54. A ring 55, rotatable circumferentially of the engine has parts 56 through which the levers 53 pass. Blocks 57 on ring 55 are connected by arms 60 to vanes 15. Thus movement of pistons 51 and levers 53 causes rotation of vanes 15. In both embodiments the vanes 15 are cooled by air fed from space 30 through the quill shafts.
GB1865461A 1961-05-23 1961-05-23 Fluid flow machine such as a gas turbine engine Expired GB946995A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB1865461A GB946995A (en) 1961-05-23 1961-05-23 Fluid flow machine such as a gas turbine engine
DER32764A DE1224990B (en) 1961-05-23 1962-05-21 Guide device for flow machines, especially gas turbines
FR898386A FR1325261A (en) 1961-05-23 1962-05-22 Fluid flow machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1865461A GB946995A (en) 1961-05-23 1961-05-23 Fluid flow machine such as a gas turbine engine

Publications (1)

Publication Number Publication Date
GB946995A true GB946995A (en) 1964-01-15

Family

ID=10116170

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1865461A Expired GB946995A (en) 1961-05-23 1961-05-23 Fluid flow machine such as a gas turbine engine

Country Status (2)

Country Link
DE (1) DE1224990B (en)
GB (1) GB946995A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
EP1918529A2 (en) * 2006-11-03 2008-05-07 Rolls-Royce Deutschland Ltd & Co KG Turbomachine with adjustable stator vanes
FR3081028A1 (en) * 2018-05-14 2019-11-15 Safran Aircraft Engines DEVICE FOR CHANGING THE SETTING OF A RECTIFIER BLADE
FR3081029A1 (en) * 2018-05-14 2019-11-15 Safran Aircraft Engines DEVICE FOR CONTROLLING VARIATION IN THE SETTING OF A RECTIFIER BLADE

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2835349C2 (en) * 1978-08-11 1979-12-20 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Adjustable grille for highly loaded compressors, especially of gas turbine engines

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE850681C (en) * 1945-02-13 1952-09-25 Maschf Augsburg Nuernberg Ag Adjustable diffuser for flow machines, especially gas turbines
BE555908A (en) * 1956-03-20
FR1268985A (en) * 1960-10-05 1961-08-04 Meccaniche Riva S P A Costruzi Low-loss mobile vane distributor for turbine machines

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
EP1918529A2 (en) * 2006-11-03 2008-05-07 Rolls-Royce Deutschland Ltd & Co KG Turbomachine with adjustable stator vanes
EP1918529A3 (en) * 2006-11-03 2010-05-12 Rolls-Royce Deutschland Ltd & Co KG Turbomachine with adjustable stator vanes
FR3081028A1 (en) * 2018-05-14 2019-11-15 Safran Aircraft Engines DEVICE FOR CHANGING THE SETTING OF A RECTIFIER BLADE
FR3081029A1 (en) * 2018-05-14 2019-11-15 Safran Aircraft Engines DEVICE FOR CONTROLLING VARIATION IN THE SETTING OF A RECTIFIER BLADE

Also Published As

Publication number Publication date
DE1224990B (en) 1966-09-15

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