GB1121512A - Improvements in stator structure for a gas turbine engine - Google Patents

Improvements in stator structure for a gas turbine engine

Info

Publication number
GB1121512A
GB1121512A GB52939/66A GB5293966A GB1121512A GB 1121512 A GB1121512 A GB 1121512A GB 52939/66 A GB52939/66 A GB 52939/66A GB 5293966 A GB5293966 A GB 5293966A GB 1121512 A GB1121512 A GB 1121512A
Authority
GB
United Kingdom
Prior art keywords
flange
engaging
platform
gas turbine
turbine engine
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
GB52939/66A
Inventor
Henry Edward Lynch
Joseph Savage Alford
William Bowles Campbell
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1121512A publication Critical patent/GB1121512A/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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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

1, 121, 512. Gas turbine engine blade fixing. GENERAL ELECTRIC CO. Nov.25, 1966 [Feb. 28, 1966], No. 52939/66. Heading F1T. A stator structure for a turbine or compressor of a gas turbine engine comprises an outer casing 18 having internal rings 28, 30 with respective annular slots 32, 36 into which fit flanges 40, 42 on the platform 24 of a guide blade segment 20. A downstream segmental shroud ring 38 has a lip 60 engaging in a further annular slot 34 in ring 30 and a lip 62 engaging a slot 48 in platform flange 42 so as to lock the blade segment 20 radially in position. The segment 20 is located circumferentially by a stop 50 comprising a bolt engaging a recess 52 in flange 42 and attached to casing 18 by a nut 56. The downstream shroud 38 is located circumferentially by a tab 66 engaging a recess 64 in flange 42. A similar upstream shroud 38 has a lip engaging in a slot 46 in platform flange 40. A flange 68 on the blade segment inner platform 26 is attached to a support ring 72 for sealing structure.
GB52939/66A 1966-02-28 1966-11-25 Improvements in stator structure for a gas turbine engine Expired GB1121512A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US53043266A 1966-02-28 1966-02-28

Publications (1)

Publication Number Publication Date
GB1121512A true GB1121512A (en) 1968-07-31

Family

ID=24113622

Family Applications (1)

Application Number Title Priority Date Filing Date
GB52939/66A Expired GB1121512A (en) 1966-02-28 1966-11-25 Improvements in stator structure for a gas turbine engine

Country Status (7)

Country Link
BE (1) BE690197A (en)
CH (1) CH482920A (en)
DE (1) DE1476805A1 (en)
FR (1) FR1501671A (en)
GB (1) GB1121512A (en)
NL (1) NL6616482A (en)
SE (1) SE326200B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2161220A (en) * 1984-07-02 1986-01-08 Gen Electric Gas turbine stator vane assembly
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2674909B1 (en) * 1991-04-03 1993-06-18 Snecma COMPRESSOR STATOR OF TURBOMACHINE WITH REMOVABLE BLADES.

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2161220A (en) * 1984-07-02 1986-01-08 Gen Electric Gas turbine stator vane assembly
GB2272027A (en) * 1992-10-28 1994-05-04 Snecma Interlocking the ends of blades
GB2272027B (en) * 1992-10-28 1996-04-10 Snecma System for interlocking the ends of blades

Also Published As

Publication number Publication date
NL6616482A (en) 1967-08-29
SE326200B (en) 1970-07-20
BE690197A (en) 1967-05-25
DE1476805A1 (en) 1969-12-04
FR1501671A (en) 1967-11-10
CH482920A (en) 1969-12-15

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