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GB774501A - A stator guide vane construction for elastic fluid turbines - Google Patents

A stator guide vane construction for elastic fluid turbines

Info

Publication number
GB774501A
GB774501A GB28463/53A GB2846353A GB774501A GB 774501 A GB774501 A GB 774501A GB 28463/53 A GB28463/53 A GB 28463/53A GB 2846353 A GB2846353 A GB 2846353A GB 774501 A GB774501 A GB 774501A
Authority
GB
United Kingdom
Prior art keywords
blade
vane
fixed
air
spindle
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
GB28463/53A
Inventor
David Geoffrey Ainley
Sydney William Henry Perry
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB28463/53A priority Critical patent/GB774501A/en
Publication of GB774501A publication Critical patent/GB774501A/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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical

Landscapes

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

Abstract

774,501. Elastic-fluid turbines. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Jan. 7, 1955 [Oct. 15, 1953], No. 28463/53. Class 110 (3). In an inlet nozzle guide vane assembly or an interstage stator blade assembly of an elasticfluid turbine, each inlet nozzle vane or stator blade comprises a fixed forward portion 1 incorporating the leading edge of the vane or blade and a rearward portion 2 incorporating the trailing edge of the vane or blade, the rearward portion is rotatable about an axis extending along its forward edge and means are provided for cooling the fixed part of the vane or blade. The fixed portion 1 of the gas turbine stator blade shown in Fig. 1 has integral outer and inner shrouds 3 and 4 which abut rings 5 and 29 respectively, the abutting surfaces being formed with apertures through which extend the spindles 2a, 2b of the rotatable portion 2 of the blade. The shroud 4 is connected to a ring 20 which carries a footstep bearing 6 in which engages a hardened conical pivot 7 on the spindle 2b. The shroud 3 is connected to an annular structure 8 while the ring 5 is formed integrally with an annular structure 9, the structures 8 and 9 abutting on a transverse plane and being formed with semi-cylindrica portions 8a, 9a which surround the spindles 2a. The outer end of the spindle 2a bears against a spring-loaded pivot 11 carried in fixed structure 13. An operating lever 15 is connected to each spindle 2a. One of the semi cylindrical portions 9a is provided with an inlet 16 through which cooling air, which may be tapped from the engine compressor, is fed to the space 27. The air then passes into the fixed blade portions 1 which comprises an outer shell 1a and an inner core 1b and issues through outlets 1c at the downstream edge and flows over the surface of the rotatable blade portior 2. In the case of an inlet nozzle guide vane cooling air may pass into the fixed portions of the vanes from both the inner and outer ends, the air being tapped from the space between the outer air casing and the flame tube or tubes of the combustion equipment. The air space within the two semi-cylindrical portions is closed by means of a flexible conical seal 17 connected to the spindle 2a. The invention may be applied in the case of assemblies of combustion equipment and turbine inlet nozzle guide vanes as described and claimed in Specifications 723,015 and 774,500. Specification 755,527 also is referred to.
GB28463/53A 1953-10-15 1953-10-15 A stator guide vane construction for elastic fluid turbines Expired GB774501A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB28463/53A GB774501A (en) 1953-10-15 1953-10-15 A stator guide vane construction for elastic fluid turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB28463/53A GB774501A (en) 1953-10-15 1953-10-15 A stator guide vane construction for elastic fluid turbines

Publications (1)

Publication Number Publication Date
GB774501A true GB774501A (en) 1957-05-08

Family

ID=10276023

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28463/53A Expired GB774501A (en) 1953-10-15 1953-10-15 A stator guide vane construction for elastic fluid turbines

Country Status (1)

Country Link
GB (1) GB774501A (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3211423A (en) * 1964-05-13 1965-10-12 Gen Electric High temperature gas turbine nozzle partition
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
US4221114A (en) * 1967-01-18 1980-09-09 Rolls-Royce Limited Gas turbine jet propulsion engine
FR2586268A1 (en) * 1985-08-14 1987-02-20 Snecma DEVICE FOR VARIATION OF THE PASSAGE SECTION OF A TURBINE DISPENSER
FR2607188A1 (en) * 1986-11-26 1988-05-27 Snecma TURBOMACHINE INPUT CASING WITH RADIANT ARMS
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
US5375972A (en) * 1993-09-16 1994-12-27 The United States Of America As Represented By The Secretary Of The Air Force Turbine stator vane structure
FR2857699A1 (en) * 2003-07-17 2005-01-21 Snecma Moteurs Turbine intake guide wheel blade de-icer has at least one emission slot in a fore and aft direction along trailing edge of blade's fixed section
DE102010021145A1 (en) * 2010-05-21 2011-11-24 Mtu Aero Engines Gmbh Adjustable guide vane and turbomachine
EP3093442A1 (en) * 2015-05-15 2016-11-16 United Technologies Corporation Vane strut positioning and securing systems
BE1023397B1 (en) * 2015-09-04 2017-03-06 Safran Aero Boosters S.A. DRAWER WITH VARIABLE ADJUSTMENT OF AXIAL TURBOMACHINE COMPRESSOR
US9803559B2 (en) 2014-02-06 2017-10-31 United Technologies Corporation Variable vane and seal arrangement
FR3079553A1 (en) * 2018-03-30 2019-10-04 Safran Aircraft Engines ASSEMBLY FOR TURBOMACHINE
GB2588956A (en) * 2019-11-15 2021-05-19 Rolls Royce Plc A variable vane assembly

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3211423A (en) * 1964-05-13 1965-10-12 Gen Electric High temperature gas turbine nozzle partition
US4221114A (en) * 1967-01-18 1980-09-09 Rolls-Royce Limited Gas turbine jet propulsion engine
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
FR2586268A1 (en) * 1985-08-14 1987-02-20 Snecma DEVICE FOR VARIATION OF THE PASSAGE SECTION OF A TURBINE DISPENSER
EP0214038A1 (en) * 1985-08-14 1987-03-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Device for varying the inlet section of a turbine
US4705452A (en) * 1985-08-14 1987-11-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Stator vane having a movable trailing edge flap
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
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
US5375972A (en) * 1993-09-16 1994-12-27 The United States Of America As Represented By The Secretary Of The Air Force Turbine stator vane structure
EP1500787A1 (en) * 2003-07-17 2005-01-26 Snecma Moteurs De-icing device for inlet vanes of a turbo engine, the vane using the same de-icing device and the aeronautical engine using such vanes.
FR2857699A1 (en) * 2003-07-17 2005-01-21 Snecma Moteurs Turbine intake guide wheel blade de-icer has at least one emission slot in a fore and aft direction along trailing edge of blade's fixed section
US7055304B2 (en) 2003-07-17 2006-06-06 Snecma Moteurs De-icing device for turbojet inlet guide wheel vane, vane provided with such a de-icing device, and aircraft engine equipped with such vanes
DE102010021145A1 (en) * 2010-05-21 2011-11-24 Mtu Aero Engines Gmbh Adjustable guide vane and turbomachine
US9803559B2 (en) 2014-02-06 2017-10-31 United Technologies Corporation Variable vane and seal arrangement
EP3093442A1 (en) * 2015-05-15 2016-11-16 United Technologies Corporation Vane strut positioning and securing systems
US9879560B2 (en) 2015-05-15 2018-01-30 United Technologies Corporation Vane strut positioning and securing systems
BE1023397B1 (en) * 2015-09-04 2017-03-06 Safran Aero Boosters S.A. DRAWER WITH VARIABLE ADJUSTMENT OF AXIAL TURBOMACHINE COMPRESSOR
FR3079553A1 (en) * 2018-03-30 2019-10-04 Safran Aircraft Engines ASSEMBLY FOR TURBOMACHINE
GB2574107A (en) * 2018-03-30 2019-11-27 Safran Aircraft Engines Assembly for a turbine engine
US10934884B2 (en) 2018-03-30 2021-03-02 Safran Aircraft Engines Assembly for a turbine engine
GB2574107B (en) * 2018-03-30 2022-09-21 Safran Aircraft Engines Assembly for a turbine engine
GB2588956A (en) * 2019-11-15 2021-05-19 Rolls Royce Plc A variable vane assembly

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