GB804010A - Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines - Google Patents

Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines

Info

Publication number
GB804010A
GB804010A GB4507/56A GB450756A GB804010A GB 804010 A GB804010 A GB 804010A GB 4507/56 A GB4507/56 A GB 4507/56A GB 450756 A GB450756 A GB 450756A GB 804010 A GB804010 A GB 804010A
Authority
GB
United Kingdom
Prior art keywords
platforms
vanes
end surfaces
notches
parallel
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
GB4507/56A
Inventor
Lionel Haworth
Ralph John Shire
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB4507/56A priority Critical patent/GB804010A/en
Priority to US637758A priority patent/US2982519A/en
Priority to FR1166270D priority patent/FR1166270A/en
Publication of GB804010A publication Critical patent/GB804010A/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

804,010. Turbine stator vane assemblies. ROLLS-ROYCE, Ltd. Jan. 30, 1957 [Feb. 13, 1956], No. 4507/56. Class 110 (3). A stator vane assembly, for example the nozzle guide vane assembly of an axial-flow turbine of a gas turbine engine, comprises a fully annular (i.e. an unsplit) casing and a plurality of stator vanes each having a vane platform at its outer end, each of a number of the platforms having its circumferentiallyspaced end surfaces parallel and projecting into a corresponding one of an equal number of circumferentially-spaced parallel-sided notches in the casing, and each of the remaining platforms having plane end surfaces inclined to each other at such angles that when the vanes are assembled in the casing, the platforms form a complete annulus with the end surfaces of the platforms in contact. The fully annular casing 10 is formed with internal circumferential ribs 17 each of which is formed with peripheral grooves 16 open at the down-stream end, and with parallel-sided notches 23 equal in number to half the number of nozzle guide vanes 11. The platform 13 of each alternate guide vane 11 has its circumferentially-spaced end surfaces 13a formed as planes parallel to one another and to the radius 13b from the axis of the turbine through the centre of the platform 13, the platforms 13 being engaged in the notches 23. The circumferentially-spaced end surfaces 33a of each of the remaining platforms 33 are formed as plane surfaces which are inclined to one another, these surfaces in the assembly engaging the surfaces 13a of the adjacent platforms 13. The vanes are all located in the circumferential direction by engagement of the platforms 13 in the notches 23. All the platforms 13 and 33 are formed with axial flanges 15 which upon assembly engage the peripheral grooves 16 to locate the vanes radially, and with radial flange portions 19 which in the assembly are located between a pair of rings 20, 21 so as to locate the vanes axially. The platforms 33 are cut away so as to clear the portion of the circumferential rib 17 between the notches 23. The circumferentially-spaced end surfaces of the inner platforms 12 are formed parallel to corresponding surfaces of the outer platforms 13, 33. The end surfaces of the vane platforms may.lie in axial planes or they may lie in planes helically disposed.
GB4507/56A 1956-02-13 1956-02-13 Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines Expired GB804010A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB4507/56A GB804010A (en) 1956-02-13 1956-02-13 Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines
US637758A US2982519A (en) 1956-02-13 1957-02-01 Stator vane assembly for axial-flow fluid machine
FR1166270D FR1166270A (en) 1956-02-13 1957-02-12 Improvements to stator vane assemblies such as those used in axial flow fluid machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4507/56A GB804010A (en) 1956-02-13 1956-02-13 Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines

Publications (1)

Publication Number Publication Date
GB804010A true GB804010A (en) 1958-11-05

Family

ID=9778514

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4507/56A Expired GB804010A (en) 1956-02-13 1956-02-13 Improvements in or relating to stator vane assemblies such as are used in axial-flowfluid machines

Country Status (3)

Country Link
US (1) US2982519A (en)
FR (1) FR1166270A (en)
GB (1) GB804010A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5411369A (en) * 1994-02-22 1995-05-02 Pratt & Whitney Canada, Inc. Gas turbine engine component retention
CN111561394A (en) * 2020-05-25 2020-08-21 中国航发沈阳发动机研究所 Structure of engine air inlet casing and assembling method thereof

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3072380A (en) * 1959-02-05 1963-01-08 Dresser Ind Stator blade carrier assembly mounting
US4648792A (en) * 1985-04-30 1987-03-10 United Technologies Corporation Stator vane support assembly
US5004402A (en) * 1989-09-05 1991-04-02 United Technologies Corporation Axial compressor stator construction
US5248240A (en) * 1993-02-08 1993-09-28 General Electric Company Turbine stator vane assembly
US5449272A (en) * 1993-12-22 1995-09-12 Solar Turbines Incorporated Mounting apparatus for a nozzle guide vane assembly
US5584654A (en) * 1995-12-22 1996-12-17 General Electric Company Gas turbine engine fan stator
EP0943785A1 (en) * 1998-03-18 1999-09-22 Asea Brown Boveri AG Fixing a vane to a stator
SI1917419T1 (en) * 2005-08-17 2009-10-31 Alstom Technology Ltd Guide vane arrangement of a turbo-machine
CA2624517C (en) * 2005-10-06 2014-05-13 Alstom Technology Ltd Vane arrangement of a turbo machine
JP5180556B2 (en) * 2006-10-13 2013-04-10 昭和電工株式会社 Skin external preparations and cosmetics containing ubiquinone derivatives or salts thereof, and methods of use thereof
US9546571B2 (en) * 2012-08-22 2017-01-17 United Technologies Corporation Mounting lug for connecting a vane to a turbine engine case

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR957575A (en) * 1946-10-02 1950-02-23
FR965713A (en) * 1947-05-07 1950-09-20
US2625013A (en) * 1948-11-27 1953-01-13 Gen Electric Gas turbine nozzle structure

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5411369A (en) * 1994-02-22 1995-05-02 Pratt & Whitney Canada, Inc. Gas turbine engine component retention
CN111561394A (en) * 2020-05-25 2020-08-21 中国航发沈阳发动机研究所 Structure of engine air inlet casing and assembling method thereof

Also Published As

Publication number Publication date
US2982519A (en) 1961-05-02
FR1166270A (en) 1958-11-04

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