US3532437A - Stator blade assembly for axial-flow turbines - Google Patents

Stator blade assembly for axial-flow turbines Download PDF

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Publication number
US3532437A
US3532437A US740600A US3532437DA US3532437A US 3532437 A US3532437 A US 3532437A US 740600 A US740600 A US 740600A US 3532437D A US3532437D A US 3532437DA US 3532437 A US3532437 A US 3532437A
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United States
Prior art keywords
blade assembly
axial
segments
stator blade
assembly
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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
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US740600A
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English (en)
Inventor
Rene Strub
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Sulzer AG
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Sulzer AG
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    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • stator blade assembly for axial-flow turbines comprising inner and outer concentric rings with stator blades extending between them, the outer ring including a flange extending axially of the turbine past the rotor blades of the associated stage of the turbine.
  • the outer ring is made up of circumferentially overlapping segments to permit radial expansion and contraction of the assembly with changes in temperature, and is also provided with a radially extending rib which fits into a groove on the inside of the turbine housing to prevent flow of the working substance past the outside of the assembly. Suitable means are provided to hold the assembly in fixed position in the housing.
  • the present invention pertains to a stator blade assembly for axial-flow turbines.
  • This assembly comprises blades extending between radially inner and outer rings, and a stationary annular flange or shroud for the turbine rotor.
  • stator blade assembly is extensible in a radially outward direction, and the cover ring forms a part thereof.
  • FIG. 1 is a fragmentary axial section through a turbine including a stator blade assembly according to the invention
  • FIG. 2 is an axial view in plan of the stator blade assembly of FIG. 1;
  • FIG. 3 is a fragmentary developed view, radially inward, of the stator assembly of FIGS. 1 and 2;
  • FIG. 4 is a fragmentary plan axial view of the apparatus of FIG. 3, being thus a fragmentary view at an enlarged scale of the peripheral portion of the apparatus shown in FIG. 2;
  • FIG. 5 is a fragmentary perspective exploded view at an enlarged scale of two adjacent segments in the outer ring of the stator blade assembly of FIGS. 1 to 4;
  • FIG. 6 is a view similar to that of FIG. 4, but showing another construction according to the invention.
  • FIG. 7 is still another view similar to that of FIG. 4 and showing still another embodiment of the invention.
  • reference character 1 denotes generally the stator blade assembly for the nth stage of an axial-flow turbine whose rotor is generally indicated at 2.
  • the assembly comprises a set of blades 6 extending between radially inner an (8 and 5. It also comprises a cover ring or flange constituting a shroud 7 for the rotor blades 8 of that stage.
  • the inner ring 4 extends over 360 about the turbine axis but may be made of two parts for easy assembly as indicated in FIG. 2, where the joints between the two parts of ring 4 are indicated at 3. Slits 10 are provided at the exterior periphery 9 of the ring 4.
  • the inside periphery 11 has a lower temperature than the exterior surface 9 by reason of the passage, during operation of the turbine, of a coolant in the space between the inside limit 11 of the ring 4 and the outside 12 of the rotor 2 (FIG. 1).
  • the outer ring 5 of the stator blade assembly 1 is made up of a number of segments 13 (FIG. 2), of which three successive segments, generally identified at 14, 15 and 16, are shown in FIG. 3. Two further such segments are shown at 30 and 31 in FIG. 2.
  • the segments are movable with respect to each other in the plane of the assembly, i.e., in the plane of FIG. 2.
  • successive segments such as the segments 14, 15 and 16 are provided with end portions or tabs 17 and 18 whose overlapping surfaces 19 and 20 engage each other in the plane of the assembly and can slide over each other. It will be recognized that the plane of FIG. 3, onto which part of the outer periphery of the stator assembly has been developed, is perpendicular to that of FIG. 2.
  • the segments are provided with a circumferentially and radially extending exterior rib 21.
  • This rib is received in an annular groove 22 in the inner wall 23 of the turbine housing 24, as illustrated in FIGS. 1 and 2.
  • the rib portion of each segment includes an axial extension 21a of short circumferential extent.
  • Rotation of the blade assembly within its plane which would otherwise occur under influence of the working substance (e.g., steam) passing through the turbine is prevented by abutments which are provided on the turbine housing at several points about its inner periphery. As indicated in FIG.
  • two pairs of abutments are thus provided. Of the first of these pairs, one abutment is shown at 28 and of the second pair one abutment is shown at 29.
  • the abutment 28 lies between the rectangular extensions 21a of the two adjacent segments 30 and 31 of the assembly outer ring 5.
  • the abutment 29 is similarly engaged between two segments of the ring 5.
  • Each segment of the ring 5 possesses a flange 33 extending axially of the turbine beyond the rotor blades 8 of the turbine stage to which that ring 5 belongs. These flanges together make up the shroud or covering ring 7 of that stage, dimensioned with suitable clearance 34 from the rotor blades 8.
  • the flanges 33 have been indicated as integral parts of the segments. They can, of course, be separate therefrom and screwed or otherwise fastened thereto.
  • the ribs 21 of the successive segments constitute together a sealing ring against the axially flowing working substance.
  • FIG. 5 The construction of the outer ring of the stator blade assembly of FIGS. 1 to 4 is further illustrated in FIG. 5 where two adjacent segments 14 and 15 are shown, separated from each other in an exploded view which shows the overlapping tabs 17 and 18 thereof. The surface 19 on tab 17 is visible on segment 14.
  • the surfaces identified by reference characters a and b on segment 15 are cylindrical surfaces coaxial in the axis of the assembly.
  • Surfaces c, d, c and 3 d instead may be plane surfaces perpendicular to that axis.
  • the blades 6 shown in FIG. extend radially toward the axis of the assembly.
  • surfaces a and a are continuous and make up the surface previously referred to.
  • the surfaces c and c also form part of a single surface, namely a plane surface, as do the surfaces d and d.
  • FIG. 6 A further embodiment of the invention permitting the stator blade assembly to be fastened in position free of dilficulties attendant upon the thermal expansion and contraction of the parts is illustrated in FIG. 6.
  • the segments which make up the outer ring of the stator blade assembly are here provided each with a eircuferentially extending foot 36. On each segment, this foot is fastened at one end, as indicated at 37, to the housing 24 in the circular groove 22 thereof, for example by means of bolts.
  • the feet are so dimensioned as to possess the elasticity necessary to accommodate the expansion of the blade assembly.
  • the segments may be provided with sealing ribs 21 extending circumferentially.
  • the blade assembly is supported by springs 39 engaged between the outer ring of the assembly (made up of segments 46) and the inner wall of the housing 24.
  • Each spring is supported at its ends 40 and 41 in notches 42 and 43 of the housing whereas the proturberant middle part 44 of the spring is received in a notch 45 of the ring segment 46.
  • cup-like springs may be employed.
  • the blade assembly 1 On starting up of the turbine, the blade assembly 1Liteergoes radially outward expansion.
  • the flange 7, which constitutes a part of the blade assembly, is consequently moved outwardly by an equal amount. Since the rotor blades 8 undergo substantially the same radially outward expansion as does the stator blade assembly, the original clearance between the flange and the rotor blades is substantially preserved.
  • the advantage of this construction is that the turbine may be built with a small clearance 34, the equality of these expansions insuring against undesired contact of the rotor blades against the flange.
  • a stator blade assembly for an axial-flow turbine comprising a radially inner ring having a plurality of radially inwardly extending slits in the outer periphery thereof, a radially outer ring made up of circumferentially overlapping segments, a plurality of blades extending between the inner and outer rings, each of said segments including an axially extending rotor blade covering portion and a radially outwardly extending rib adapted to be received in a groove on the inside of the turbine housing.
  • a blade assembly according to claim 1 further comprising axial extensions on said rib, and abutments afilxed to the turbine housing engaging between circumferentially adjacent ones of said extensions.
  • a blade assembly according to claim 2 wherein said extensions comprise pins received in bores in the turbine housing and in said segments.
  • each of said segments has affixed thereto an elastic supporting member adapted to be received in a circumferential groove of the turbine housing.
  • a blade assembly according to claim 1 further including resilient means engaged between each of said segments and the turbine housing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US740600A 1967-11-03 1968-06-27 Stator blade assembly for axial-flow turbines Expired - Lifetime US3532437A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1543767A CH482915A (de) 1967-11-03 1967-11-03 Leitvorrichtung für Axialturbine

Publications (1)

Publication Number Publication Date
US3532437A true US3532437A (en) 1970-10-06

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Family Applications (1)

Application Number Title Priority Date Filing Date
US740600A Expired - Lifetime US3532437A (en) 1967-11-03 1968-06-27 Stator blade assembly for axial-flow turbines

Country Status (4)

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US (1) US3532437A (de)
CH (1) CH482915A (de)
DE (1) DE6601211U (de)
FR (1) FR1589865A (de)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3904324A (en) * 1972-11-06 1975-09-09 Tech Dev Inc Tip turbine inflating device
US4248569A (en) * 1978-11-13 1981-02-03 General Motors Corporation Stator mounting
EP0103260A2 (de) * 1982-09-06 1984-03-21 Hitachi, Ltd. Einstellung des Spiels zwischen Turbinenschaufelspitzen und Gehäuse
US4509238A (en) * 1983-03-21 1985-04-09 General Electric Company Method for fabricating a steam turbine diaphragm
US4623298A (en) * 1983-09-21 1986-11-18 Societe Nationale D'etudes Et De Construction De Moteurs D'aviation Turbine shroud sealing device
US4787817A (en) * 1985-02-13 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Device for monitoring clearance between rotor blades and a housing
EP0999349A3 (de) * 1998-11-04 2002-03-13 ABB Turbo Systems AG Axialturbine
US6679679B1 (en) * 2000-11-30 2004-01-20 Snecma Moteurs Internal stator shroud
EP1505260A2 (de) * 2002-08-03 2005-02-09 ALSTOM (Switzerland) Ltd Abdichtungsvorrichtung in einer Turbomaschine
EP1548232A1 (de) * 2003-12-23 2005-06-29 Siemens Aktiengesellschaft Strömungsmaschine mit einem Leitschaufelträger und Verfahren zum Montieren von Leitschaufeln an einen Leitschaufelträger
US20090208332A1 (en) * 2008-02-19 2009-08-20 United Technologies Corporation LPC exit guide vane and assembly
EP2211025A3 (de) * 2009-01-21 2014-01-22 General Electric Company Einzellastrippen für individuelle Leitschaufeln
US20140037438A1 (en) * 2012-07-31 2014-02-06 General Electric Company Turbine shroud for a turbomachine
US20170356298A1 (en) * 2016-06-08 2017-12-14 Rolls-Royce Plc Stator vane
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2061396B (en) * 1979-10-24 1983-05-18 Rolls Royce Turbine blade tip clearance control
FR2728015B1 (fr) * 1994-12-07 1997-01-17 Snecma Distributeur monobloc sectorise d'un stator de turbine de turbomachine
FR2761119B1 (fr) * 1997-03-20 1999-04-30 Snecma Stator de compresseur de turbomachine
DE102015201782A1 (de) 2015-02-02 2016-08-18 MTU Aero Engines AG Leitschaufelring für eine Strömungsmaschine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL282822A (de) * 1961-09-04
US998820A (en) * 1908-05-13 1911-07-25 George Westinghouse Turbine-blading.
US2282894A (en) * 1940-04-02 1942-05-12 Gen Electric Elastic fluid turbine
US2488875A (en) * 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine
DE852789C (de) * 1951-02-08 1952-10-20 Maschf Augsburg Nuernberg Ag Leitschaufeltraeger fuer Axialturbinen
DE928746C (de) * 1952-12-04 1955-06-10 Maschf Augsburg Nuernberg Ag Leitapparat fuer Abgasturbogeblaese
GB881880A (en) * 1959-05-22 1961-11-08 Power Jets Res & Dev Ltd Turbo-machine stator construction
US3427000A (en) * 1966-11-14 1969-02-11 Westinghouse Electric Corp Axial flow turbine structure

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US998820A (en) * 1908-05-13 1911-07-25 George Westinghouse Turbine-blading.
US2282894A (en) * 1940-04-02 1942-05-12 Gen Electric Elastic fluid turbine
US2488875A (en) * 1947-05-07 1949-11-22 Rolls Royce Gas turbine engine
DE852789C (de) * 1951-02-08 1952-10-20 Maschf Augsburg Nuernberg Ag Leitschaufeltraeger fuer Axialturbinen
DE928746C (de) * 1952-12-04 1955-06-10 Maschf Augsburg Nuernberg Ag Leitapparat fuer Abgasturbogeblaese
GB881880A (en) * 1959-05-22 1961-11-08 Power Jets Res & Dev Ltd Turbo-machine stator construction
NL282822A (de) * 1961-09-04
US3427000A (en) * 1966-11-14 1969-02-11 Westinghouse Electric Corp Axial flow turbine structure

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3904324A (en) * 1972-11-06 1975-09-09 Tech Dev Inc Tip turbine inflating device
US4248569A (en) * 1978-11-13 1981-02-03 General Motors Corporation Stator mounting
EP0103260A2 (de) * 1982-09-06 1984-03-21 Hitachi, Ltd. Einstellung des Spiels zwischen Turbinenschaufelspitzen und Gehäuse
EP0103260A3 (de) * 1982-09-06 1984-09-26 Hitachi, Ltd. Einstellung des Spiels zwischen Turbinenschaufelspitzen und Gehäuse
US4509238A (en) * 1983-03-21 1985-04-09 General Electric Company Method for fabricating a steam turbine diaphragm
US4623298A (en) * 1983-09-21 1986-11-18 Societe Nationale D'etudes Et De Construction De Moteurs D'aviation Turbine shroud sealing device
US4787817A (en) * 1985-02-13 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Device for monitoring clearance between rotor blades and a housing
EP0999349A3 (de) * 1998-11-04 2002-03-13 ABB Turbo Systems AG Axialturbine
US6679679B1 (en) * 2000-11-30 2004-01-20 Snecma Moteurs Internal stator shroud
EP1505260A2 (de) * 2002-08-03 2005-02-09 ALSTOM (Switzerland) Ltd Abdichtungsvorrichtung in einer Turbomaschine
EP1505260A3 (de) * 2002-08-03 2005-10-26 Alstom Technology Ltd Abdichtungsvorrichtung in einer Turbomaschine
EP1548232A1 (de) * 2003-12-23 2005-06-29 Siemens Aktiengesellschaft Strömungsmaschine mit einem Leitschaufelträger und Verfahren zum Montieren von Leitschaufeln an einen Leitschaufelträger
WO2005066463A1 (de) * 2003-12-23 2005-07-21 Siemens Aktiengesellschaft Strömungsmaschine mit einem leitschaufelträger und verfahren zum montieren von leitschaufeln an einen leitschaufelträger
US20090208332A1 (en) * 2008-02-19 2009-08-20 United Technologies Corporation LPC exit guide vane and assembly
US8511983B2 (en) * 2008-02-19 2013-08-20 United Technologies Corporation LPC exit guide vane and assembly
EP2211025A3 (de) * 2009-01-21 2014-01-22 General Electric Company Einzellastrippen für individuelle Leitschaufeln
US20140037438A1 (en) * 2012-07-31 2014-02-06 General Electric Company Turbine shroud for a turbomachine
US20170356298A1 (en) * 2016-06-08 2017-12-14 Rolls-Royce Plc Stator vane
US20200072070A1 (en) * 2018-09-05 2020-03-05 United Technologies Corporation Unified boas support and vane platform

Also Published As

Publication number Publication date
FR1589865A (de) 1970-04-06
DE6601211U (de) 1969-02-27
CH482915A (de) 1969-12-15

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