GB805015A - Improvements in and relating to turbines - Google Patents

Improvements in and relating to turbines

Info

Publication number
GB805015A
GB805015A GB18082/56A GB1808256A GB805015A GB 805015 A GB805015 A GB 805015A GB 18082/56 A GB18082/56 A GB 18082/56A GB 1808256 A GB1808256 A GB 1808256A GB 805015 A GB805015 A GB 805015A
Authority
GB
United Kingdom
Prior art keywords
blade
cavity
fixed
parts
movable
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
GB18082/56A
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.)
Schweizerische Lokomotiv und Maschinenfabrik AG (SLM)
Original Assignee
Schweizerische Lokomotiv und Maschinenfabrik AG (SLM)
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 Schweizerische Lokomotiv und Maschinenfabrik AG (SLM) filed Critical Schweizerische Lokomotiv und Maschinenfabrik AG (SLM)
Publication of GB805015A publication Critical patent/GB805015A/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
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • 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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Abstract

805,015. Turbines. SCHWEIZERISCHE LOKOMOTIVUND MASCHINENFABRIK. June 12, 1956 [June 17, 1955], No. 18082/56. Class 110 (3). In an axial flow turbine guide blade ring comprising blades consisting on the inlet side of a fixed part and on the outlet side of a part pivotally movable relative to the fixed part each blade has the separation between the fixed and movable parts located in the region of greatest blade thickness and the sector angle of the circular arc profile bounding the gap of the pivoted part is of such magnitude that even in the most extreme positions of this part a tangential continuation of the profile of the fixed part is ensured. Each guide blade of the interstage guide blade ring 2 comprises a fixed blade part 8 which forms a rigid connection between the outer and inner blade supporting rings 9, 10 and a pivoted part 11. The separation between the stationary and movable blade parts is located at the region of greatest blade thickness. The sector angle γ of the circular arc profile 14 is of such magnitude that even in the most extreme positions 11<SP>1</SP>, 11<SP>11</SP> of the movable blade parts, a tangential continuation of the profile of the fixed blade parts is ensured. The ratio of the length L of the movable blade part to the blade pitch T is preferably greater than 1: 0 and the angle y greater than 180 degrees so as to obtain a favourable channel shape at partial load. The pivoted blade parts are moved in unison by a ring 21. The inner supporting ring is made in two halves 10, 10a so that the inner ends of the blade parts 11 may be provided with pivot pins 17. Cooling air may be supplied to a cavity 23 formed in the fixed blade part 8 and discharged therefrom through gaps 12, 13. A cavity 26 formed in the movable blade part 11 may be supplied with cooling air from the cavity 23 through the duct 27. Cooling air is discharged from the cavity 26 through the ducts 28, 29, 30. The cavity 23 may be supplied with cooling air from the cavity 26 which receives the initial air supply. Specifications 736,796 and 774,501 are referred to.
GB18082/56A 1955-06-17 1956-06-12 Improvements in and relating to turbines Expired GB805015A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
NL333663X 1955-06-17

Publications (1)

Publication Number Publication Date
GB805015A true GB805015A (en) 1958-11-26

Family

ID=19784465

Family Applications (1)

Application Number Title Priority Date Filing Date
GB18082/56A Expired GB805015A (en) 1955-06-17 1956-06-12 Improvements in and relating to turbines

Country Status (5)

Country Link
AT (1) AT195186B (en)
CH (1) CH333663A (en)
FR (1) FR1151368A (en)
GB (1) GB805015A (en)
NL (2) NL198161A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3089679A (en) * 1960-06-06 1963-05-14 Chrysler Corp Gas turbine nozzle suspension and adjustment
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
US4097187A (en) * 1975-10-14 1978-06-27 Westinghouse Canada Limited Adjustable vane assembly for a gas 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
GB2210935A (en) * 1987-10-10 1989-06-21 Rolls Royce Plc Variable stator vane assembly
US4856962A (en) * 1988-02-24 1989-08-15 United Technologies Corporation Variable inlet guide vane
US4950129A (en) * 1989-02-21 1990-08-21 General Electric Company Variable inlet guide vanes for an axial flow compressor
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
GB2328723A (en) * 1997-08-28 1999-03-03 Gen Electric Variable area gas turbine nozzle
EP1256698A2 (en) * 2001-05-11 2002-11-13 FIATAVIO S.p.A. Axial turbine with a variable-geometry stator
GB2395235A (en) * 2002-11-13 2004-05-19 Ishikawajima Harima Heavy Ind A lightweight cooled turbine blade
JP2015506439A (en) * 2012-02-02 2015-03-02 シーメンス アクティエンゲゼルシャフト A blade ring for an axial-flow turbomachine and a method for adjusting the maximum flow rate of the blade ring
EP3018291A1 (en) * 2014-11-10 2016-05-11 Rolls-Royce plc A guide vane
WO2019243484A1 (en) * 2018-06-21 2019-12-26 Safran Aero Boosters Sa Turbine engine outer shroud

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1113787B (en) * 1958-09-12 1961-09-14 Bbc Brown Boveri & Cie Axial compressor with rotatable guide vanes for dusty gas
DE1204021B (en) * 1959-04-27 1965-10-28 Rolls Royce Blade for axial flow machines, especially gas turbines
DE1173292B (en) * 1960-08-02 1964-07-02 M A N I Turbomotoren G M B H Hubjet engine for vertical take-off aircraft
DE1245218B (en) * 1963-05-15 1967-07-20 Hitachi Ltd Gas turbine rotor
US3316714A (en) * 1963-06-20 1967-05-02 Rolls Royce Gas turbine engine combustion equipment
US3224194A (en) * 1963-06-26 1965-12-21 Curtiss Wright Corp Gas turbine engine
GB1048968A (en) * 1964-05-08 1966-11-23 Rolls Royce Combustion chamber for a gas turbine engine
GB1313841A (en) * 1967-01-18 1973-04-18 Secr Defence Gas turbine jet propulsion engine
US3423069A (en) * 1967-09-29 1969-01-21 Trw Inc Airfoil
US4169692A (en) * 1974-12-13 1979-10-02 General Electric Company Variable area turbine nozzle and means for sealing same
US4026659A (en) * 1975-10-16 1977-05-31 Avco Corporation Cooled composite vanes for turbine nozzles
US4384823A (en) * 1980-10-27 1983-05-24 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Curved film cooling admission tube
EP0196450B1 (en) * 1985-03-15 1989-05-03 Siemens Aktiengesellschaft Drag adjuster
GB2218746B (en) * 1988-05-17 1992-06-17 Rolls Royce Plc A nozzle guide vane for a gas turbine engine
CN112727955B (en) * 2021-01-18 2023-04-18 一汽解放汽车有限公司 Hydraulic retarder rotor

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3089679A (en) * 1960-06-06 1963-05-14 Chrysler Corp Gas turbine nozzle suspension and adjustment
US4097187A (en) * 1975-10-14 1978-06-27 Westinghouse Canada Limited Adjustable vane assembly for a gas turbine
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
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
GB2210935A (en) * 1987-10-10 1989-06-21 Rolls Royce Plc Variable stator vane assembly
US4861228A (en) * 1987-10-10 1989-08-29 Rolls-Royce Plc Variable stator vane assembly
GB2210935B (en) * 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly
US4856962A (en) * 1988-02-24 1989-08-15 United Technologies Corporation Variable inlet guide vane
US4950129A (en) * 1989-02-21 1990-08-21 General Electric Company Variable inlet guide vanes for an axial flow compressor
US5314301A (en) * 1992-02-13 1994-05-24 Rolls-Royce Plc Variable camber stator vane
GB2266562A (en) * 1992-04-23 1993-11-03 Turbo Propulsores Ind Gas turbine engine variable stator vane assembly.
GB2266562B (en) * 1992-04-23 1995-10-11 Turbo Propulsores Ind Gas turbine stator vane assembly
GB2328723A (en) * 1997-08-28 1999-03-03 Gen Electric Variable area gas turbine nozzle
GB2328723B (en) * 1997-08-28 2001-12-19 Gen Electric Variable area turbine nozzle
FR2767865A1 (en) * 1997-08-28 1999-03-05 Gen Electric VARIABLE SECTION TURBINE DISPENSER
US6860717B2 (en) 2001-05-11 2005-03-01 Avio S.P.A. Axial turbine for aeronautical applications
EP1256698A2 (en) * 2001-05-11 2002-11-13 FIATAVIO S.p.A. Axial turbine with a variable-geometry stator
EP1256698A3 (en) * 2001-05-11 2004-03-10 AVIO S.p.A. Axial turbine with a variable-geometry stator
US6926499B2 (en) 2002-11-13 2005-08-09 Ishikawajima-Harima Heavy Industries Co., Ltd. Thin-walled, lightweight cooled turbine blade
GB2395235A (en) * 2002-11-13 2004-05-19 Ishikawajima Harima Heavy Ind A lightweight cooled turbine blade
GB2395235B (en) * 2002-11-13 2006-03-29 Ishikawajima Harima Heavy Ind Thin-walled,lightweight cooled turbine blade
JP2015506439A (en) * 2012-02-02 2015-03-02 シーメンス アクティエンゲゼルシャフト A blade ring for an axial-flow turbomachine and a method for adjusting the maximum flow rate of the blade ring
EP3018291A1 (en) * 2014-11-10 2016-05-11 Rolls-Royce plc A guide vane
US10012103B2 (en) 2014-11-10 2018-07-03 Rolls-Royce Plc Guide vane
WO2019243484A1 (en) * 2018-06-21 2019-12-26 Safran Aero Boosters Sa Turbine engine outer shroud
BE1026411B1 (en) * 2018-06-21 2020-01-30 Safran Aero Boosters Sa EXTERIOR TURBOMACHINE OIL
US11236634B2 (en) 2018-06-21 2022-02-01 Safran Aero Boosters Sa Turbine engine outer shroud

Also Published As

Publication number Publication date
NL198161A (en)
NL86599C (en)
FR1151368A (en) 1958-01-29
CH333663A (en) 1958-10-31
AT195186B (en) 1958-01-25

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