US3574479A - Turbine having variable-angle nozzle guide vanes - Google Patents

Turbine having variable-angle nozzle guide vanes Download PDF

Info

Publication number
US3574479A
US3574479A US851703A US3574479DA US3574479A US 3574479 A US3574479 A US 3574479A US 851703 A US851703 A US 851703A US 3574479D A US3574479D A US 3574479DA US 3574479 A US3574479 A US 3574479A
Authority
US
United States
Prior art keywords
turbine
rack
leaf spring
nozzle guide
guide vanes
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 - Lifetime
Application number
US851703A
Inventor
Mark Cary Sedgwick Barnard
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.)
Leyland Gas Turbines Ltd
Original Assignee
Leyland Gas Turbines 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 Leyland Gas Turbines Ltd filed Critical Leyland Gas Turbines Ltd
Application granted granted Critical
Publication of US3574479A publication Critical patent/US3574479A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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

Definitions

  • the invention relates to a turbine having a ring of variableangle nozzle guide vanes.
  • each nozzle guide vane is arranged to be turned about an axis extending longitudinally thereof by a pinion engaging an annular rack coaxial with the turbine and arrangement to be reciprocated by bellcrank lever means actuated by a fluid-operated plunger,
  • a connecting link pivotally attached at one end thereof to a bellcrank lever and at the other end thereof to the rack.
  • a turbine having a ring of variable-angle nozzle guide vanes, each arranged to be turned simultaneously about an axis extending longitudinally thereof by one of a plurality of pinions engaging an annular rack coaxial with the turbine includes a substantially tangentially extending leaf spring secured at one end thereof to the annular rack end at the other end thereof to a lever by which the annular rack is to be angularly turned to effect simultaneous turning of the pinions and hence of the nozzle guide vanes, the leaf spring being flexible in a direction toward and away from the circumference of the annular rack.
  • the leaf spring may either be mounted directly on the lever or be attached to a link pivotally connected at the end thereof remote from the leaf spring to the lever.
  • the lever may be one arm of a bellcrank lever having another arm arranged to be moved by operating means, for example a fluid-operated plunger.
  • leaf spring By employing a leaf spring to transmit actuating movement to the rack relatively sliding surfaces on the spring or a mounting therefor and on the annulus are avoided and therefore there is no possibility of seizure or wear problems at high temperature, as there would be by employing a conventional pivot joint. Furthermore, the leaf spring can flex as a result of angular movement of the lever or the connecting link, where the latter is provided, and the lever or the link is always aligned with the adjacent portion of the leaf spring.
  • reference 1 denotes the axis of rotation of the turbine.
  • An annular rack for turning the nozzle guide vanes through individual pinions is indicated by reference 2.
  • One pinion and the associated nozzle guide vane are shown and are indicated by references 10 and 11 respectively.
  • the pinion 10 is carried by a shaft 12 extending longitudinally from the vane 11 and rotation of the pinion 10 by the rack 2 effects rotation of the guide vane. Circumferential movement of the rack 2 effects similar movement of all the vanes 11 simultaneously.
  • the annular rack has secured to its outer periphery a mounting block 3 in which is secured one end of a leaf spring 4.
  • the leaf spring 4 extends substantially tangentially of the annular rack, but can flex towards or away from the peripheral surface of the annular rack.
  • the end of the leaf spring 4 remote from the mounting block 3 is secured to a link 5, which is pivotally attached to the radially outer end of an arm 6 of a bellcrank lever.
  • the bellcrank lever has a second arm 7 to which a fluidoperated plunger 8 is pivotally attached. Reciprocation of the plunger 8 effects angular oscillation of the bellcrank lever between the position shown in full lines and the position indicated by chain line. This in turn moves the link 5 which pulls or pushes the leaf spring 4 and hence turns the annular rack 2 which turns the pinions 10 and hence the nozzle uide vanes i1.
  • the leaf spring 4 flexes as necessary so as to fo ow a smooth curve between the link 5 and the mounting block 3.
  • a turbine having a ring of variable-angle nozzle guide vanes, each arranged to be turned simultaneously about an axis extending longitudinally thereof, a driving pinion coaxial with each vane and an annular rack coaxial with the turbine and engaging said driving pinions, wherein the improvement comprises a substantially tangentially extending leaf spring secured at one thereof to said annular rack and a lever secured to the other end of said leaf spring and by which the annular rack is to be angularly turned to effect simultaneous turning of said pinions and hence of the nozzle guide vanes, said leaf spring being flexible in a direction toward and away from the circumference of said annular rack.
  • a turbine as claimed in claim 1 including a link secured at one end thereof to the end of said leaf spring remote from said annular rack and pivotally connected at the end thereof remote from said leaf spring to the lever.
  • a turbine as claimed in claim 2 including a bellcrank having one arm forming said lever and another arm to which an operating force is to be applied, the turbine also including an operating device connected to said other arm of the bellcrank.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Abstract

A turbine being a ring of variable-angle nozzle guide vanes each having a driving pinion engaging an annular rack movable circumferentially to effect simultaneous turning of the vanes, the rack being connected to an actuating member by a leaf spring flexible in a direction toward and away from the circumference of the annular rack, thereby to avoid a pivotal joint between the actuating member and the rack in a very hot region of the turbine.

Description

United States Patet [56] References Cited UNITED STATES PATENTS 3/1938 Seelig....
[72] lnventor Mark Cary Sedgwick Barnard Solihull, England [21] Appl. No. 851,703
[22] Filed Aug. 20, 1969 [45] Patented Apr. 13, 1971 [73] Assignee Leyland Gas Turbines Limited Solihull, England [32] Priority Sept. 17,1968
FOREIGN PATENTS 544,440 4/1942 GreatBritain................
Great Britain 44120/68 415/160 813,343 5/1959 Great Britain................ 415/160 Primary Examiner-Henry F. Raduazo Att0rneyMawhinney & Mawhinney ABSTRACT: A turbine being a ring of variable-angle nozzle [54] TURBINE HAVING VARIABLE-ANGLE NOZZLE guide vanes each having a driving pinion engaging an annular GUIDE VANES rack movable circumferentially to effect simultaneous turning of the vanes, the rack being connected to an actuating member by a leaf spring flexible in a direction toward and 4 Claims, 1 Drawing Fig.
415/160 F0ld 17/00 away from the circumference of the annular rack, thereby to [50] Field 415/160, avoid a pivotal joint between the actuating member and the 161, 162, 163 rack in a very hot region of the turbine.
51 im. c|...........
PATENTEUAPR] 3:97: 35,74,473
INv ram MARK CAaY enema: BARNARD A-r-ro 2 N EY TURBINE HAVING VARIABLE-ANGLE NOZZLE GUIDE VANES The invention relates to a turbine having a ring of variableangle nozzle guide vanes.
In one arrangement proposed hitherto, each nozzle guide vane is arranged to be turned about an axis extending longitudinally thereof by a pinion engaging an annular rack coaxial with the turbine and arrangement to be reciprocated by bellcrank lever means actuated by a fluid-operated plunger, One such arrangement proposed hitherto includes a connecting link pivotally attached at one end thereof to a bellcrank lever and at the other end thereof to the rack. This suffers from the disadvantage that as the link is pivotally attached at each end thereof, there could be wear at each pivot, resulting in angular movement of the bellcrank lever being incorrectly transmitted to the rack and hence to the vanes and also from the disadvantage that there are relatively sliding surfaces at the pivots, particularly at the pivot adjacent the rack, which is in a very hot region of the turbine.
According to the invention, a turbine having a ring of variable-angle nozzle guide vanes, each arranged to be turned simultaneously about an axis extending longitudinally thereof by one of a plurality of pinions engaging an annular rack coaxial with the turbine, includes a substantially tangentially extending leaf spring secured at one end thereof to the annular rack end at the other end thereof to a lever by which the annular rack is to be angularly turned to effect simultaneous turning of the pinions and hence of the nozzle guide vanes, the leaf spring being flexible in a direction toward and away from the circumference of the annular rack.
The leaf spring may either be mounted directly on the lever or be attached to a link pivotally connected at the end thereof remote from the leaf spring to the lever.
The lever may be one arm of a bellcrank lever having another arm arranged to be moved by operating means, for example a fluid-operated plunger.
By employing a leaf spring to transmit actuating movement to the rack relatively sliding surfaces on the spring or a mounting therefor and on the annulus are avoided and therefore there is no possibility of seizure or wear problems at high temperature, as there would be by employing a conventional pivot joint. Furthermore, the leaf spring can flex as a result of angular movement of the lever or the connecting link, where the latter is provided, and the lever or the link is always aligned with the adjacent portion of the leaf spring.
By way of example, an arrangement for turning variableangle nozzle guide vanes of a turbine is now described with reference to the accompanying drawing which is a view in the direction of the axis of rotation of the turbine.
In the drawing, reference 1 denotes the axis of rotation of the turbine. An annular rack for turning the nozzle guide vanes through individual pinions is indicated by reference 2. One pinion and the associated nozzle guide vane are shown and are indicated by references 10 and 11 respectively. The pinion 10 is carried by a shaft 12 extending longitudinally from the vane 11 and rotation of the pinion 10 by the rack 2 effects rotation of the guide vane. Circumferential movement of the rack 2 effects similar movement of all the vanes 11 simultaneously. In accordance with the invention, the annular rack has secured to its outer periphery a mounting block 3 in which is secured one end of a leaf spring 4. The leaf spring 4 extends substantially tangentially of the annular rack, but can flex towards or away from the peripheral surface of the annular rack. The end of the leaf spring 4 remote from the mounting block 3 is secured to a link 5, which is pivotally attached to the radially outer end of an arm 6 of a bellcrank lever. The bellcrank lever has a second arm 7 to which a fluidoperated plunger 8 is pivotally attached. Reciprocation of the plunger 8 effects angular oscillation of the bellcrank lever between the position shown in full lines and the position indicated by chain line. This in turn moves the link 5 which pulls or pushes the leaf spring 4 and hence turns the annular rack 2 which turns the pinions 10 and hence the nozzle uide vanes i1. The leaf spring 4 flexes as necessary so as to fo ow a smooth curve between the link 5 and the mounting block 3.
I claim:
1. A turbine having a ring of variable-angle nozzle guide vanes, each arranged to be turned simultaneously about an axis extending longitudinally thereof, a driving pinion coaxial with each vane and an annular rack coaxial with the turbine and engaging said driving pinions, wherein the improvement comprises a substantially tangentially extending leaf spring secured at one thereof to said annular rack and a lever secured to the other end of said leaf spring and by which the annular rack is to be angularly turned to effect simultaneous turning of said pinions and hence of the nozzle guide vanes, said leaf spring being flexible in a direction toward and away from the circumference of said annular rack.
2. A turbine as claimed in claim 1 including a link secured at one end thereof to the end of said leaf spring remote from said annular rack and pivotally connected at the end thereof remote from said leaf spring to the lever.
3. A turbine as claimed in claim 2 including a bellcrank having one arm forming said lever and another arm to which an operating force is to be applied, the turbine also including an operating device connected to said other arm of the bellcrank.
4. A turbine as claimed in claim 3 in which said operating device is a fluid-operated plunger.

Claims (3)

  1. 2. A turbine as claimed in claim 1 including a link secured at one end thereof to the end of said leaf spring remote from said annular rack and pivotally connected at the end thereof remote from said leaf spring to the lever.
  2. 3. A turbine as claimed in claim 2 including a bellcrank having one arm forming said lever and another arm to which an operating force is to be applied, the turbine also including an operating device connected to said other arm of the bellcrank.
  3. 4. A turbine as claimed in claim 3 in which said operating device is a fluid-operated plunger.
US851703A 1968-09-17 1969-08-20 Turbine having variable-angle nozzle guide vanes Expired - Lifetime US3574479A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB44120/68A GB1211447A (en) 1968-09-17 1968-09-17 Turbine having variable angle nozzle guide vanes

Publications (1)

Publication Number Publication Date
US3574479A true US3574479A (en) 1971-04-13

Family

ID=10431877

Family Applications (1)

Application Number Title Priority Date Filing Date
US851703A Expired - Lifetime US3574479A (en) 1968-09-17 1969-08-20 Turbine having variable-angle nozzle guide vanes

Country Status (2)

Country Link
US (1) US3574479A (en)
GB (1) GB1211447A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3685921A (en) * 1969-08-14 1972-08-22 Bennes Marrcl Gas turbine with variable blade distributor
US3801216A (en) * 1970-08-19 1974-04-02 Mtu Muenchen Gmbh Installation for adjusting power turbine guide blades in twin-shaft gas turbine engines, especially for the drive of motor vehicles
US3893784A (en) * 1972-11-08 1975-07-08 Bbc Sulzer Turbomaschinen Apparatus for adjusting stator blades
US3904309A (en) * 1974-08-12 1975-09-09 Caterpillar Tractor Co Variable angle turbine nozzle actuating mechanism
US4003675A (en) * 1975-09-02 1977-01-18 Caterpillar Tractor Co. Actuating mechanism for gas turbine engine nozzles
US4720237A (en) * 1986-02-24 1988-01-19 United Technologies Corporation Unison ring actuator assembly
US4890977A (en) * 1988-12-23 1990-01-02 Pratt & Whitney Canada, Inc. Variable inlet guide vane mechanism
US20140127003A1 (en) * 2012-11-07 2014-05-08 Rolls-Royce Deutschland Ltd & Co Kg Stator vane adjusting device of a gas turbine
CN110159364A (en) * 2019-05-28 2019-08-23 哈尔滨电气股份有限公司 A kind of adjustable guide vane executing agency applied to gas turbine
US10774662B2 (en) 2018-07-17 2020-09-15 Rolls-Royce Corporation Separable turbine vane stage

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4652208A (en) * 1985-06-03 1987-03-24 General Electric Company Actuating lever for variable stator vanes

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE20668E (en) * 1938-03-08 Multistage fan
GB544440A (en) * 1939-07-05 1942-04-14 Alessandro Baj Improvements in centrifugal compressors for supercharging internal combustion engines
GB813343A (en) * 1955-10-21 1959-05-13 Power Jets Res & Dev Ltd Improvements in or relating to apparatus for the control of ducted fluids
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
US3074689A (en) * 1960-06-06 1963-01-22 Chrysler Corp Adjustable nozzle ring support
US3318513A (en) * 1965-03-03 1967-05-09 Gen Motors Corp Variable vane ring
US3352537A (en) * 1965-12-29 1967-11-14 Rolls Royce Vane operating mechanism for fluid flow machines

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE20668E (en) * 1938-03-08 Multistage fan
GB544440A (en) * 1939-07-05 1942-04-14 Alessandro Baj Improvements in centrifugal compressors for supercharging internal combustion engines
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
GB813343A (en) * 1955-10-21 1959-05-13 Power Jets Res & Dev Ltd Improvements in or relating to apparatus for the control of ducted fluids
US3074689A (en) * 1960-06-06 1963-01-22 Chrysler Corp Adjustable nozzle ring support
US3318513A (en) * 1965-03-03 1967-05-09 Gen Motors Corp Variable vane ring
US3352537A (en) * 1965-12-29 1967-11-14 Rolls Royce Vane operating mechanism for fluid flow machines

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3685921A (en) * 1969-08-14 1972-08-22 Bennes Marrcl Gas turbine with variable blade distributor
US3801216A (en) * 1970-08-19 1974-04-02 Mtu Muenchen Gmbh Installation for adjusting power turbine guide blades in twin-shaft gas turbine engines, especially for the drive of motor vehicles
US3893784A (en) * 1972-11-08 1975-07-08 Bbc Sulzer Turbomaschinen Apparatus for adjusting stator blades
US3904309A (en) * 1974-08-12 1975-09-09 Caterpillar Tractor Co Variable angle turbine nozzle actuating mechanism
US4003675A (en) * 1975-09-02 1977-01-18 Caterpillar Tractor Co. Actuating mechanism for gas turbine engine nozzles
US4720237A (en) * 1986-02-24 1988-01-19 United Technologies Corporation Unison ring actuator assembly
US4890977A (en) * 1988-12-23 1990-01-02 Pratt & Whitney Canada, Inc. Variable inlet guide vane mechanism
US20140127003A1 (en) * 2012-11-07 2014-05-08 Rolls-Royce Deutschland Ltd & Co Kg Stator vane adjusting device of a gas turbine
US9453426B2 (en) * 2012-11-07 2016-09-27 Rolls-Royce Deutschland Ltd & Co Kg Stator vane adjusting device of a gas turbine
US10774662B2 (en) 2018-07-17 2020-09-15 Rolls-Royce Corporation Separable turbine vane stage
CN110159364A (en) * 2019-05-28 2019-08-23 哈尔滨电气股份有限公司 A kind of adjustable guide vane executing agency applied to gas turbine

Also Published As

Publication number Publication date
GB1211447A (en) 1970-11-04

Similar Documents

Publication Publication Date Title
US3574479A (en) Turbine having variable-angle nozzle guide vanes
US3990809A (en) High ratio actuation linkage
US4295784A (en) Variable stator
US2933234A (en) Compressor stator assembly
US3314595A (en) Adjustment mechanism for axial flow compressors
US3954349A (en) Lever connection to syncring
US10927699B2 (en) Variable-pitch blade control ring for a turbomachine
GB1067930A (en) Vane operating mechanism for fluid flow machines
US4003675A (en) Actuating mechanism for gas turbine engine nozzles
GB1368353A (en) Actuation ring for variable geometry axial flow compressors
US2955744A (en) Compressor
US11111810B2 (en) Control assembly for a stage of variable-pitch vanes for a turbine engine
US3904309A (en) Variable angle turbine nozzle actuating mechanism
US3029067A (en) Variable area nozzle means for turbines
US2746713A (en) Distributor vane operating apparatus for hydraulic turbines
US3564934A (en) Link mechanism
US20180223685A1 (en) System for controlling variable-setting blades for a turbine engine
GB737472A (en) Turbines and like machines having adjustable guide blades
US4183209A (en) Gas turbine guide apparatus
GB1430609A (en) Variable angle turbine nozzle actuating mechanism
US4955788A (en) Driving linkage device
US3284048A (en) Variable area turbine nozzle
GB837649A (en) Improvements in compressor stator vane assembly
GB738987A (en) Improvements in and relating to turbines having movable directive vanes
US3146626A (en) Adjusting mechanism for blades of fluid flow machines, especially torque converters