US3893784A - Apparatus for adjusting stator blades - Google Patents

Apparatus for adjusting stator blades Download PDF

Info

Publication number
US3893784A
US3893784A US413313A US41331373A US3893784A US 3893784 A US3893784 A US 3893784A US 413313 A US413313 A US 413313A US 41331373 A US41331373 A US 41331373A US 3893784 A US3893784 A US 3893784A
Authority
US
United States
Prior art keywords
adjusting
strips
rings
ring
combination
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
US413313A
Other languages
English (en)
Inventor
Ferdinand Zerlauth
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.)
Brown Boveri Sulzer Turbomaschinen AG
ABB Stal AB
Original Assignee
Brown Boveri Sulzer Turbomaschinen AG
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 Brown Boveri Sulzer Turbomaschinen AG filed Critical Brown Boveri Sulzer Turbomaschinen AG
Application granted granted Critical
Publication of US3893784A publication Critical patent/US3893784A/en
Assigned to ABB STAL AB, A CORP. OF SWEDEN reassignment ABB STAL AB, A CORP. OF SWEDEN ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BROWN BOVERI-SULZER TURBOMACHINERY LTD., A CORP. OF SWITZERLAND
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

  • ABSTRACT The adjustably mounted stator blades are movable in a g" Application y Data linear manner by means of adjusting rings which are Nov. 8, 1972 Switzerland 16246/72 both rotatable about the axis of the turbornachine and slidable longitudinally, i.e. axially, of the turboma- [52] U.S. C]. 415/149 R; 415/147 chine.
  • the adjusting rings are interconnected by resil- [5 l] Int. Cl.
  • This invention relates to an apparatus for adjusting stator blades and particularly to an apparatus for ad justing stator blades of multi-stage axial turbomachines.
  • axial turbomachines have been constructed with stator blades, particularly the stator blades of at least individual stages, which are adjustable in order to improve the part load characteristics of the turbomachines so as to enable very small minimum loads to be operated or, for example, in the case of gas turbine plants, to reduce the starting power which must be supplied by an auxiliary drive.
  • adjusting mechanisms have been used to carry out this function.
  • some adjusting mechanisms have used a rotatable adjusting ring to adjust the blades of one stage by con necting the ring to each blade over a lever.
  • the adjusting rings of the individual stages have been coupled to each other through connecting elements which are rotatably mounted at their downstream ends on the casing of the turbomachine so as to be adapted for simultaneous adjustment in the same sense.
  • the adjusting mechanisms have been constructed so that the angles of rotation above which the blades of the individual stages are to be pivoted through a specific distance of an adjusting mechanism should be in a practically linear relationship, for example, so that the angle for the stages with a higher pressure diminishes with a linearly diminishing function. This relationship may be obtained by using levers of different length for the individual stages between the blades and their adjusting rings, which may for example, be combined into a sleeve.
  • Constructions have also been known in which a rod which is pivotably supported on the casing is pivoted in one plane for the purpose of adjusting the stator blades of a plurality of stages practically in a linear relationship.
  • the adjusting rings are rotated by the aforementioned pivoting action; the rotation is then transmitted to the blades via trunnions and levers which extend at least substantially axially. Since the pivoting motion of the rod in this construction does not proceed parallel to the rotating motion of the adjusting rings, a mechanism is required which has large tolerances and substantial clearance between the individual elements which move relative to each other.
  • the known construction is therefore completely unsuitable for a large number of stages. Also, the construction is not suitable if the accuracy requirements of blade adjustment are only slight increased.
  • the known adjusting mechanism is liable to jam or at least become cumbersome, that is, it may require very large adjusting forces.
  • the invention is directed to a multi-stage axial flow turbomachine having a casing and a plurality of stages of adjustable stator blades mounted about a longitudinal axis.
  • an apparatus is provided in this turbomachine for adjusting the adjustable stator blades in each stage.
  • This apparatus includes a plurality of adjusting rings which are connected to the stator blades by levers.
  • the rings are rotatably mounted in concentric relation about the longitudinal axis of the turbomachine and each is mounted adjacent a respective stator stage.
  • the levers connect each blade of a stage to the adjacent ring.
  • a plurality of resilient twistable strips are secured across and to the rings and each strip is pivotally mounted at one end on the casing.
  • a drive means is also secured to at least one adjusting ring for rotating the ring and the other rings via the twistable strips. As the rings are rotated, they simultaneously move axially under the influence of the twistable strips and cause the stator blades, which are supported between the two axial extreme positions of the adjacent adjusting ring, to turn in a linear pattern.
  • the blade adjustment of the present construction is obtained by the axial motion of the adjusting ring which is imposed in linearly diminishing manner by rotation of the rings with the aid of the strips in accordance with requirements.
  • one of the upstream disposed adjusting rings is driven because the adjusting forces are relatively small for relatively large angles of rotation in the rings which are the first as seen in the flow direction.
  • twistable strips preferably stamped from thin spring steel sheet, tend to kink if they are stressed in compression with the distance between two adjusting rings is excessive. This kinking can, however, be prevented in a simple manner by securing the strips between two adjusting rings to a support collar which is floatingly disposed between the rings.
  • FIG. 1 illustrates in a sectional view of the first stages of a compressor of a gas turbine plant and an apparatus according to the invention, the view being a longitudinal section along a vertical axial plane of the machine;
  • FIG. 2 illustrates an enlarged detail of FIG. 1'
  • FIG. 3 illustrates a view taken on line Ill-Ill of FIG. 4 through an adjusting ring, the sectional plane being disposed slightly before or behind that of FIG. 2 as seen in the circumferential direction of the ring to show the ring cross-section in the zone of its bearing elements instead of the connection of the ring to one of the strips;
  • H0. 4 illustrates a perspective schematic view showing the method of operation of the adjusting apparatus of the invention by reference to two adjustable stator blade rows, only one blade being shown for each row.
  • the compressor has a suction end which is associated with a gas turbine (not shown) and in which a plurality of stages l-5 of stator blades 6, 7 are mounted.
  • the blades 6 of the inlet stator stage 1 and the blades 7 of the first four stator blades stages 2-5 are adjustably constructed while the stator blades 8 of the higher compression stages are fixed.
  • the blades 6, 7 are pivotally supported by means of a dry bearing system 9 in a stator blade support 10 which is divided along a horizontal axial plane as viewed and concentrically surrounds a rotor 12 which supports rotor blades II.
  • the adjustable blades 6, 7 are adjusted via an adjusting apparatus which includes annular adjusting rings 16 connected to the adjustable blades 6, 7 by means of levers 13 which are of identical construction for manufacutring reasons and are retained in the blade roots 15 by means of screw fasteners 14.
  • sliding blocks 17, e.g. of rectangular shape which are supported on spigots that are welded to the free ends of the levers l3 engage in corresponding annular grooves 18 of the rings 16.
  • the rings 16 themselves, whose diameter becomes smaller for the higher pressure stages, are supported by means of lateral flange extensions 20 (FIG. 3) on three bearing elements 19 (FIG. 3) which are uniformly distributed circumferentially about the rings 16 and are covered with dryrunning material represented in block form in FIG. 3.
  • the bearing elements 19, in turn, are mounted on corresponding extensions 21 on the outside of the stator blade support 10.
  • the adjusting rings 16 of the individual stages 1-5 are also divided along their horizontal plane and are connected to each other by means of free resiliently twistable strips 22 e.g. three as shown which are distributed over the circumference.
  • the downstream end of each strip 22 is pivotably supported in corresponding extensions in the blade support 10 by means of spigot mountings 23 which are of a construction that is identical to that for the connections 24 between the rings 16 and the strips 22 and which will be described subsequently.
  • a floating support ring 27 that is, a ring which is secured only by means of mountings 26 in the strips 22, is provided between the stages 1 and 2.
  • the adjusting apparatus is driven by means of two servo pistons 28 (FIG. 1) which are mounted laterally on the ring 16 of the second stage 2, one end of the pistons 28 being supported in the compressor casing 10 and the other end being adapted to act with clearance on a bifurcated extension of the aforementioned ring 16 which is situated close to the horizontal parting plane.
  • the mounting means 24 are disposed in eyelet extensions 30 (FIG. 2) of the rings 16 and, in the same way as the mounting means 23 and 26, are provided with a spigot 32 which is secured by means of a pin 31 against rotation in the eyelet 30.
  • the spitot 32 additionally bears by means of a shoulder 33 upon the extension 30.
  • the spigot 32 is surrounded by a clamping or reinforcing element 34 via an interposed layer of dry running material.
  • the reinforcing element 34 comprises two parts and bears on the other annular surface of the shoulder 33, the two parts being bolted to each other while clamping the strip 22.
  • the elements 34 are retained with a clearance on the spigot 32 via a washer 36 by means of a screw bolt 35 which is screw mounted into the spigot 32.
  • FIG. 4 illustrates the path 40 and 41 of two rings 16 from a first position shown in dash dot form into a second position shown in solid form and vice versa when rotated in the direction indicated by the double arrow 42.
  • the strips 22 which may comprise stamped sheet metal strips of approximately 60 millimeters (mm) width and L5 millimeters (mm) thickness will be subjected to twisting as indicated in FIG. 4 while the rings 16, in addition to rotating, carry out an axial sliding motion on the bearing elements 19 with a linear interdependence.
  • a multi-stage axial flow turbornachine having a casing and a plurality of stages of adjustable stator blades mounted in said casing about a longitudinal axis; an apparatus for adjusting said stator blades of each stage comprising a plurality of axially movable adjusting rings rotatably mounted in concentric relation about said axis, each adjusting ring being mounted adjacent a respective stator stage;

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
US413313A 1972-11-08 1973-11-06 Apparatus for adjusting stator blades Expired - Lifetime US3893784A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1624672A CH557960A (de) 1972-11-08 1972-11-08 Vorrichtung fuer die leitschaufelverstellung.

Publications (1)

Publication Number Publication Date
US3893784A true US3893784A (en) 1975-07-08

Family

ID=4415655

Family Applications (1)

Application Number Title Priority Date Filing Date
US413313A Expired - Lifetime US3893784A (en) 1972-11-08 1973-11-06 Apparatus for adjusting stator blades

Country Status (8)

Country Link
US (1) US3893784A (ja)
JP (1) JPS5222446B2 (ja)
CA (1) CA987236A (ja)
CH (1) CH557960A (ja)
DE (1) DE2255853C2 (ja)
FR (1) FR2205952A5 (ja)
GB (1) GB1395310A (ja)
IT (1) IT999287B (ja)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4767264A (en) * 1986-10-31 1988-08-30 United Technologies Corporation Vane lever arm construction
US5096374A (en) * 1989-02-02 1992-03-17 Hitachi, Ltd. Vane controller
EP1531237A2 (en) * 2003-11-14 2005-05-18 Rolls-Royce Plc Supporting an actuating ring for variable guide vanes of a compressor
EP2261466A1 (de) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Verstelleinrichtung für Leitschaufeln einer Turbine
EP3228823A1 (en) * 2016-03-24 2017-10-11 United Technologies Corporation Sliding gear actuation for variable vanes
US10107130B2 (en) 2016-03-24 2018-10-23 United Technologies Corporation Concentric shafts for remote independent variable vane actuation
US10190599B2 (en) 2016-03-24 2019-01-29 United Technologies Corporation Drive shaft for remote variable vane actuation
CN109707671A (zh) * 2019-02-02 2019-05-03 沈阳透平机械股份有限公司 一种轴流式压缩机的内置静叶可调机构
US10288087B2 (en) 2016-03-24 2019-05-14 United Technologies Corporation Off-axis electric actuation for variable vanes
US10294813B2 (en) 2016-03-24 2019-05-21 United Technologies Corporation Geared unison ring for variable vane actuation
US10301962B2 (en) 2016-03-24 2019-05-28 United Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears
US10329947B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation 35Geared unison ring for multi-stage variable vane actuation
US10415596B2 (en) 2016-03-24 2019-09-17 United Technologies Corporation Electric actuation for variable vanes
US10443431B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Idler gear connection for multi-stage variable vane actuation
US10443430B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Variable vane actuation with rotating ring and sliding links
US10458271B2 (en) 2016-03-24 2019-10-29 United Technologies Corporation Cable drive system for variable vane operation

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1511723A (en) * 1975-05-01 1978-05-24 Rolls Royce Variable stator vane actuating mechanism
GB2078865B (en) * 1980-06-28 1983-06-08 Rolls Royce A variable stator vane operating mechanism for a gas turbine engine
DE3042191C1 (de) * 1980-11-05 1982-04-01 Gebrüder Sulzer AG, 8401 Winterthur Verstelleinrichtung fuer die Leitschaufeln eines Axialverdichters
EP0130408B1 (de) * 1983-06-29 1987-09-30 BBC Aktiengesellschaft Brown, Boveri & Cie. Einrichtung zur Verstellung des Turbinenzuströmquerschnittes eines Abgasturboladers
US4652208A (en) * 1985-06-03 1987-03-24 General Electric Company Actuating lever for variable stator vanes
JPS645936U (ja) * 1987-06-30 1989-01-13
DE10351202A1 (de) * 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln
DE102012019950A1 (de) 2012-10-11 2014-04-17 Man Diesel & Turbo Se Vorrichtung zum Verändern des Leitschaufelwinkels bei axialen Strömungsmaschinen

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858062A (en) * 1955-01-24 1958-10-28 Gen Electric Variable stator mechanism
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
US3574479A (en) * 1968-09-17 1971-04-13 Leyland Gas Turbines Ltd Turbine having variable-angle nozzle guide vanes
US3685920A (en) * 1971-02-01 1972-08-22 Gen Electric Actuation ring for variable geometry compressors or gas turbine engines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858062A (en) * 1955-01-24 1958-10-28 Gen Electric Variable stator mechanism
US2955744A (en) * 1955-05-20 1960-10-11 Gen Electric Compressor
US3574479A (en) * 1968-09-17 1971-04-13 Leyland Gas Turbines Ltd Turbine having variable-angle nozzle guide vanes
US3685920A (en) * 1971-02-01 1972-08-22 Gen Electric Actuation ring for variable geometry compressors or gas turbine engines

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4767264A (en) * 1986-10-31 1988-08-30 United Technologies Corporation Vane lever arm construction
US5096374A (en) * 1989-02-02 1992-03-17 Hitachi, Ltd. Vane controller
EP1531237A2 (en) * 2003-11-14 2005-05-18 Rolls-Royce Plc Supporting an actuating ring for variable guide vanes of a compressor
US20050106010A1 (en) * 2003-11-14 2005-05-19 Evans Dale E. Variable stator vane arrangement for a compressor
EP1531237A3 (en) * 2003-11-14 2006-07-19 Rolls-Royce Plc Supporting an actuating ring for variable guide vanes of a compressor
US7198454B2 (en) 2003-11-14 2007-04-03 Rolls-Royce Plc Variable stator vane arrangement for a compressor
EP2261466A1 (de) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Verstelleinrichtung für Leitschaufeln einer Turbine
US10329946B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation Sliding gear actuation for variable vanes
US10329947B2 (en) 2016-03-24 2019-06-25 United Technologies Corporation 35Geared unison ring for multi-stage variable vane actuation
US10190599B2 (en) 2016-03-24 2019-01-29 United Technologies Corporation Drive shaft for remote variable vane actuation
US11131323B2 (en) 2016-03-24 2021-09-28 Raytheon Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears
US10288087B2 (en) 2016-03-24 2019-05-14 United Technologies Corporation Off-axis electric actuation for variable vanes
US10294813B2 (en) 2016-03-24 2019-05-21 United Technologies Corporation Geared unison ring for variable vane actuation
US10301962B2 (en) 2016-03-24 2019-05-28 United Technologies Corporation Harmonic drive for shaft driving multiple stages of vanes via gears
US10107130B2 (en) 2016-03-24 2018-10-23 United Technologies Corporation Concentric shafts for remote independent variable vane actuation
EP3228823A1 (en) * 2016-03-24 2017-10-11 United Technologies Corporation Sliding gear actuation for variable vanes
US10415596B2 (en) 2016-03-24 2019-09-17 United Technologies Corporation Electric actuation for variable vanes
US10443431B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Idler gear connection for multi-stage variable vane actuation
US10443430B2 (en) 2016-03-24 2019-10-15 United Technologies Corporation Variable vane actuation with rotating ring and sliding links
US10458271B2 (en) 2016-03-24 2019-10-29 United Technologies Corporation Cable drive system for variable vane operation
CN109707671A (zh) * 2019-02-02 2019-05-03 沈阳透平机械股份有限公司 一种轴流式压缩机的内置静叶可调机构

Also Published As

Publication number Publication date
CA987236A (en) 1976-04-13
IT999287B (it) 1976-02-20
GB1395310A (en) 1975-05-21
CH557960A (de) 1975-01-15
JPS49133909A (ja) 1974-12-23
JPS5222446B2 (ja) 1977-06-17
FR2205952A5 (ja) 1974-05-31
DE2255853C2 (de) 1975-01-23
DE2255853B1 (de) 1974-05-30

Similar Documents

Publication Publication Date Title
US3893784A (en) Apparatus for adjusting stator blades
US2999630A (en) Compressor
US3085398A (en) Variable-clearance shroud structure for gas turbine engines
US4773817A (en) Labyrinth seal adjustment device for incorporation in a turbomachine
US3487992A (en) Stator adjusting mechanism for axial flow compressors
US3549272A (en) Improvements in or relating to blading arrangement for turbomachines
US4502276A (en) Casing structure for a gas turbine engine
US3999883A (en) Variable turbomachine stator
US3458118A (en) Low profile stator adjusting mechanism
US3314595A (en) Adjustment mechanism for axial flow compressors
JPH0686820B2 (ja) ステ−タベ−ン一体リングを周方向に変位させるリンク機構
GB1560388A (en) Plant having a tube turbine or tube pump
US4618311A (en) Vane angle changing device for an axial fluid machine
CN108350906A (zh) 可变静叶片操作装置
US2778564A (en) Stator blade ring assemblies for axial flow compressors and the like
JPS6225842B2 (ja)
US3162421A (en) Gas turbine construction
US1491423A (en) Supporting means for turbine-driven units and the like
GB1067930A (en) Vane operating mechanism for fluid flow machines
US3502260A (en) Stator vane linkage for axial flow compressors
US5224820A (en) Operating mechanism for variably settable blades of a turbomachine
US4373859A (en) Unison ring support system
US2817475A (en) Centrifugal compressor and method of controlling the same
US2972441A (en) Variable blade system
CN1035543A (zh) 低压汽轮机进汽导向器

Legal Events

Date Code Title Description
AS Assignment

Owner name: ABB STAL AB, FINSPANG, SWEDEN, A CORP. OF SWEDEN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:BROWN BOVERI-SULZER TURBOMACHINERY LTD., A CORP. OF SWITZERLAND;REEL/FRAME:005186/0295

Effective date: 19890913