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GB1276720A - Drives to adjustable stator blades for turbomachinery - Google Patents

Drives to adjustable stator blades for turbomachinery

Info

Publication number
GB1276720A
GB1276720A GB6193569A GB6193569A GB1276720A GB 1276720 A GB1276720 A GB 1276720A GB 6193569 A GB6193569 A GB 6193569A GB 6193569 A GB6193569 A GB 6193569A GB 1276720 A GB1276720 A GB 1276720A
Authority
GB
United Kingdom
Prior art keywords
blades
arms
axial
ring
axis
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
GB6193569A
Inventor
Alan Stuart Lee
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.)
English Electric Co Ltd
Original Assignee
English Electric Co 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 English Electric Co Ltd filed Critical English Electric Co Ltd
Priority to GB6193569A priority Critical patent/GB1276720A/en
Priority to DE19702062328 priority patent/DE2062328A1/en
Publication of GB1276720A publication Critical patent/GB1276720A/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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1276720 Turbomachines; axial-flow blowers ENGLISH ELECTRIC CO Ltd 18 Dec 1970 [19 Dec 1969] 61935/69 Headings F1C and F1T] A turbomachine, such as an axial-flow helium blower, has angularly adjustable stator blades 29 connected by arms 36 to a common actuating ring 42 concentric with the machine axis 21A, the axes 30A of blades 29 lying on a cone whose vertex is at a point 39 on axis 21A. To reduce friction, the vertex angle is so related to the lengths of arms 36 that the outer ends of the latter during blade adjustment follow paths which when projected on to a plane normal to axis 21A approximate to circular arcs of radius equal to that of actuating ring 42. Each blade 29 has a shaft 30 rotatably supported by a cylindrical bearing surface 31 in a housing 32 bolted to the intake casing 25 of the machine. A plate 34 is splined to the end of shaft 30 and is bolted to a boss 35 integral with arm 36 and mounted by cylindrical bearings 37, 38 upon the outside of housing 32. The ends of arms 36 are connected to ring 42 by spherical bearings 40 and pins 41. Axial and circumferential movement of ring 42, and thus adjustment of blades 29, may be effected by an axially movable rod 47 pivotally connected to an additional arm (46), Fig. 5 (not shown) on one of the bosses 35. In an extreme position adjacent blades 29 abut to shut off the flow of gas to rotor blades 23. The inner surface of outer casing 25 and the outer surface of wall 26 are spherical adjacent blades 29 so that clearances 44, 45 do not vary as the blades are adjusted.
GB6193569A 1969-12-19 1969-12-19 Drives to adjustable stator blades for turbomachinery Expired GB1276720A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB6193569A GB1276720A (en) 1969-12-19 1969-12-19 Drives to adjustable stator blades for turbomachinery
DE19702062328 DE2062328A1 (en) 1969-12-19 1970-12-17 Turbo engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB6193569A GB1276720A (en) 1969-12-19 1969-12-19 Drives to adjustable stator blades for turbomachinery

Publications (1)

Publication Number Publication Date
GB1276720A true GB1276720A (en) 1972-06-07

Family

ID=10487654

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6193569A Expired GB1276720A (en) 1969-12-19 1969-12-19 Drives to adjustable stator blades for turbomachinery

Country Status (2)

Country Link
DE (1) DE2062328A1 (en)
GB (1) GB1276720A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1188903A1 (en) * 2000-09-18 2002-03-20 Snecma Moteurs Machined turbomachine shroud
EP1256696A2 (en) * 2001-05-11 2002-11-13 FIATAVIO S.p.A. Axial turbine with a variable-geometry stator
WO2012013909A1 (en) * 2010-07-30 2012-02-02 Turbomeca Device for controlling pivoting blades of a turbine engine
WO2014163681A1 (en) * 2013-03-10 2014-10-09 Fulayter Roy D Gas turbine engines and corresponding method

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4050844A (en) * 1976-06-01 1977-09-27 United Technologies Corporation Connection between vane arm and unison ring in variable area stator ring
DE2740192C2 (en) * 1977-09-07 1981-11-12 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Gap seal for an axially flow-around guide vane of a turbomachine that is adjustable about its longitudinal axis
US4278398A (en) * 1978-12-04 1981-07-14 General Electric Company Apparatus for maintaining variable vane clearance
FR2599785B1 (en) * 1986-06-04 1990-10-12 Snecma VARIABLE SETTING AIR INTAKE DIRECTOR FOR TURBOJET
IT1217437B (en) * 1988-04-21 1990-03-22 Nuovo Pignone Spa IMPROVED SYSTEM OF ADJUSTMENT OF THE ADJUSTABLE NOZZLES OF A GAS TURBINE IN POSITION
DE4213716A1 (en) * 1992-04-25 1993-10-28 Asea Brown Boveri Turbine with direct axial flow - has guide blades, which are axially movable in adjusting axis
DE102005040574A1 (en) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Gap control device for a gas turbine

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1188903A1 (en) * 2000-09-18 2002-03-20 Snecma Moteurs Machined turbomachine shroud
FR2814205A1 (en) * 2000-09-18 2002-03-22 Snecma Moteurs IMPROVED FLOW VEIN TURBOMACHINE
US6602049B2 (en) 2000-09-18 2003-08-05 Snecma Moteurs Compressor stator having a constant clearance
EP1256696A2 (en) * 2001-05-11 2002-11-13 FIATAVIO S.p.A. Axial turbine with a variable-geometry stator
EP1256696A3 (en) * 2001-05-11 2004-03-10 AVIO S.p.A. Axial turbine with a variable-geometry stator
JP2013535610A (en) * 2010-07-30 2013-09-12 ターボメカ Device for controlling the pivot blades of a turbomachine
FR2963384A1 (en) * 2010-07-30 2012-02-03 Turbomeca DEVICE FOR CONTROLLING TURBOMACHINE SWIVELING BLADES
CN103189602A (en) * 2010-07-30 2013-07-03 涡轮梅坎公司 Device for controlling pivoting blades of a turbine engine
WO2012013909A1 (en) * 2010-07-30 2012-02-02 Turbomeca Device for controlling pivoting blades of a turbine engine
CN103189602B (en) * 2010-07-30 2015-12-09 涡轮梅坎公司 A kind of device controlling turbo machine pivotable vanes
RU2600199C2 (en) * 2010-07-30 2016-10-20 Турбомека Device for control of rotating blades of turbomachine and turbomachine comprising such device
US9551234B2 (en) 2010-07-30 2017-01-24 Turnomeca Device for controlling pivotable vanes of a turbo-machine
WO2014163681A1 (en) * 2013-03-10 2014-10-09 Fulayter Roy D Gas turbine engines and corresponding method
US9708914B2 (en) 2013-03-10 2017-07-18 Rolls-Royce Corporation Gas turbine engine airflow member having spherical end
EP3505727A1 (en) * 2013-03-10 2019-07-03 Rolls-Royce Corporation Gas turbine engines and corresponding method
US10539024B2 (en) 2013-03-10 2020-01-21 Rolls-Royce Corporation Variable pitch fan for a gas turbine engine

Also Published As

Publication number Publication date
DE2062328A1 (en) 1971-06-24

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed