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GB737473A - Turbines and like machines having adjustable guide blades - Google Patents

Turbines and like machines having adjustable guide blades

Info

Publication number
GB737473A
GB737473A GB24895/52A GB2489552A GB737473A GB 737473 A GB737473 A GB 737473A GB 24895/52 A GB24895/52 A GB 24895/52A GB 2489552 A GB2489552 A GB 2489552A GB 737473 A GB737473 A GB 737473A
Authority
GB
United Kingdom
Prior art keywords
blades
annular
adjustable guide
pivoted
compressor
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
GB24895/52A
Inventor
Sidney Henry Albert Magin
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son 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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB24895/52A priority Critical patent/GB737473A/en
Priority to FR1084494D priority patent/FR1084494A/en
Priority to DEN7815A priority patent/DE929667C/en
Priority to US383812A priority patent/US2917275A/en
Publication of GB737473A publication Critical patent/GB737473A/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
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • F05D2250/131—Two-dimensional trapezoidal polygonal
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Abstract

737,473. Turbines ; axial-flow compressors. NAPIER & SON, Ltd., D. Sept. 28, 1953 [Oct. 3, 1952], No. 24895/52. Classes 110 (1) and 110 (3). A turbine or axial flow compressor having a guide blade ring assembly comprising inner and outer annular members with angularly adjustable guide blades pivoted therein about radial axes, has non-adjustable guide blades dispersed at intervals between the adjustable guide blades and connected to both the annular members. The hot gases from' an annular combustion chamber or several individual combustion chambers 11 pass through a ring of adjustable guide blades 12 to the turbine rotor. The combustion chambers having a sliding fit in an annular member 16. The blades 12 are adjusted by an annular adjusting member 31 as described in Specification 737,472. To maintain the annular members 16 and 30 in which the blades are pivoted in a given position relative to one another so as to prevent binding of the pivots, fixed blades 26 are provided. The fixed blades are attached to the flange 19 of the annular member 16 by studs 27 at least one of which is threaded to receive a nut 28 and to the outer annular member 30 by links 34 pivoted to spigots 33 on the blades and the member 30. The links 34 are disposed in a plane normal to the axis of the turbine or compressor, so that the blades 26 can expand and contract radially but' are not free to move axially relative to the casing 30. A shroud ring 30, which may be made up of separate arcuate portions, surrounds the fixed and adjustable blades and is mounted on and located by the spigots 32. The rear edge of this shroud ring abuts against a shoulder of the casing 30 to form a gas seal. To avoid all of the axial thrust on the blades 12 being taken through the outer ends of the blades, compressed air from the compressor is led through the shaft 15 and ports 22, 23 to the rear of the annular member 16. The blade platforms 35, Fig. 4, are provided with stops 36, 37 which in the end positions of the blades abut against corresponding stops 38, 39 on adjacent blade platforms.
GB24895/52A 1952-10-03 1952-10-03 Turbines and like machines having adjustable guide blades Expired GB737473A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB24895/52A GB737473A (en) 1952-10-03 1952-10-03 Turbines and like machines having adjustable guide blades
FR1084494D FR1084494A (en) 1952-10-03 1953-09-30 Turbo-machine with adjustable guide fins
DEN7815A DE929667C (en) 1952-10-03 1953-10-02 Turbomachine with adjustable guide vanes
US383812A US2917275A (en) 1952-10-03 1953-10-02 Turbo machines having adjustable guide blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB24895/52A GB737473A (en) 1952-10-03 1952-10-03 Turbines and like machines having adjustable guide blades

Publications (1)

Publication Number Publication Date
GB737473A true GB737473A (en) 1955-09-28

Family

ID=10218950

Family Applications (1)

Application Number Title Priority Date Filing Date
GB24895/52A Expired GB737473A (en) 1952-10-03 1952-10-03 Turbines and like machines having adjustable guide blades

Country Status (4)

Country Link
US (1) US2917275A (en)
DE (1) DE929667C (en)
FR (1) FR1084494A (en)
GB (1) GB737473A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2433118A1 (en) * 1978-08-11 1980-03-07 Mtu Muenchen Gmbh COMPRESSOR, ESPECIALLY A GAS TURBINE ENGINE

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1058315B (en) * 1955-09-30 1959-05-27 Power Jets Res & Dev Ltd Jet engine with air inlet connected to a combustion chamber via a connecting duct and device arranged within this connecting duct for increasing the pressure of the air flowing from the air inlet to the combustion chamber
DE1047538B (en) * 1956-10-29 1958-12-24 Siemens Ag Rotatable guide vane with limited range of rotation, especially for turbines, e.g. B. gas turbines
US3263906A (en) * 1963-07-22 1966-08-02 Task Corp Stator vane check valve
FR2583820B1 (en) * 1985-06-20 1989-04-28 Snecma DEVICE FOR VARIATION OF THE PASSAGE SECTION OF A TURBINE DISTRIBUTOR
EP1571298A1 (en) * 2004-03-02 2005-09-07 Siemens Aktiengesellschaft Blade for a turbomachine and turbomachine
US7588415B2 (en) * 2005-07-20 2009-09-15 United Technologies Corporation Synch ring variable vane synchronizing mechanism for inner diameter vane shroud
US7690889B2 (en) * 2005-07-20 2010-04-06 United Technologies Corporation Inner diameter variable vane actuation mechanism
US7753647B2 (en) * 2005-07-20 2010-07-13 United Technologies Corporation Lightweight cast inner diameter vane shroud for variable stator vanes
US7628579B2 (en) * 2005-07-20 2009-12-08 United Technologies Corporation Gear train variable vane synchronizing mechanism for inner diameter vane shroud
DE102006052003A1 (en) * 2006-11-03 2008-05-08 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with adjustable stator blades
US20240229828A1 (en) * 2023-01-11 2024-07-11 Saudi Arabian Oil Company Balance drum for a rotating machine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1067356A (en) * 1913-03-26 1913-07-15 Ljungstroems Angturbin Ab Steam-turbine.
US1694481A (en) * 1926-07-12 1928-12-11 Moody Lewis Ferry Propeller-type turbine or pump
US1978809A (en) * 1931-05-26 1934-10-30 Moody Lewis Ferry Hydraulic apparatus
NL131105B (en) * 1946-03-20
US2616662A (en) * 1949-01-05 1952-11-04 Westinghouse Electric Corp Turbine bearing support structure
BE496713A (en) * 1949-07-01

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2433118A1 (en) * 1978-08-11 1980-03-07 Mtu Muenchen Gmbh COMPRESSOR, ESPECIALLY A GAS TURBINE ENGINE

Also Published As

Publication number Publication date
DE929667C (en) 1955-06-30
US2917275A (en) 1959-12-15
FR1084494A (en) 1955-01-19

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