GB1009619A - Improvements relating to compressors and turbines - Google Patents

Improvements relating to compressors and turbines

Info

Publication number
GB1009619A
GB1009619A GB4210463A GB4210463A GB1009619A GB 1009619 A GB1009619 A GB 1009619A GB 4210463 A GB4210463 A GB 4210463A GB 4210463 A GB4210463 A GB 4210463A GB 1009619 A GB1009619 A GB 1009619A
Authority
GB
United Kingdom
Prior art keywords
slot
platform
blades
compressor
blade
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
GB4210463A
Inventor
Thomas Shelley
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 GB4210463A priority Critical patent/GB1009619A/en
Publication of GB1009619A publication Critical patent/GB1009619A/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
    • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,009,619. Stator blade fixing. ROLLSROYCE Ltd. Aug. 11, 1964 [Oct. 24, 1963], No. 42104/63. Heading F1T. A compressor or turbine has a row of stator blades each of which has a platform mounted in a slot in the outer casing of the machine, and a flexible tube whose interior is supplied with fluid pressure for urging each stator blade towards a fixed position in its slot, the tube contacting the platform(s) of one or more blades. A turbine or compressor stator blade 16, Fig. 4, has a tapered platform 23 mounted in a corresponding circumferential slot 21 in a gas turbine engine outer casing. An annular seamless flexible metal tube 25 is supplied with pressurised air from the engine compressor, or an external source, to urge blade 16 radially inwardly tightly against slot walls 24. The engine casing is in two halves 15a, 15b, Fig. 3, and the ends of flexible tube 25 are clamped between adjacent flanges 30, 31 at one of the joints. A radially extending plate 32 is also clamped at the joint to prevent circumferential movement of blades 16 within slot 21. In a modification, Fig. 2 (not shown), each blade platform has an axially extending flange. In a further modification, Fig. 5 (not shown), the flexible tube 25 is formed of two metal strips welded together.
GB4210463A 1963-10-24 1963-10-24 Improvements relating to compressors and turbines Expired GB1009619A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4210463A GB1009619A (en) 1963-10-24 1963-10-24 Improvements relating to compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4210463A GB1009619A (en) 1963-10-24 1963-10-24 Improvements relating to compressors and turbines

Publications (1)

Publication Number Publication Date
GB1009619A true GB1009619A (en) 1965-11-10

Family

ID=10422866

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4210463A Expired GB1009619A (en) 1963-10-24 1963-10-24 Improvements relating to compressors and turbines

Country Status (1)

Country Link
GB (1) GB1009619A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4621976A (en) * 1985-04-23 1986-11-11 United Technologies Corporation Integrally cast vane and shroud stator with damper
EP0331837A1 (en) * 1988-01-11 1989-09-13 General Electric Company Method and device for mounting guide vanes in turbines
FR2859509A1 (en) * 2003-09-10 2005-03-11 Snecma Moteurs Rectifier vanes rotation stopping device for turbo-machine, has bar with pair of ends inserted in groove of housing, where each end has axial surface contacting axial surface of respective housing
EP2943658B1 (en) 2013-01-08 2017-03-29 United Technologies Corporation Stator anti-rotation device

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4621976A (en) * 1985-04-23 1986-11-11 United Technologies Corporation Integrally cast vane and shroud stator with damper
EP0331837A1 (en) * 1988-01-11 1989-09-13 General Electric Company Method and device for mounting guide vanes in turbines
FR2859509A1 (en) * 2003-09-10 2005-03-11 Snecma Moteurs Rectifier vanes rotation stopping device for turbo-machine, has bar with pair of ends inserted in groove of housing, where each end has axial surface contacting axial surface of respective housing
EP1515002A1 (en) * 2003-09-10 2005-03-16 Snecma Moteurs Anti-rotation means for turbine stator vanes in the split plane of the casing
US7059832B2 (en) 2003-09-10 2006-06-13 Snecma Moteurs Rotation-locking of sectors of rectifier blades by bars in the parting planes of the housing
EP2943658B1 (en) 2013-01-08 2017-03-29 United Technologies Corporation Stator anti-rotation device

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