GB786689A - Improvements relating to elastic-fluid turbines - Google Patents

Improvements relating to elastic-fluid turbines

Info

Publication number
GB786689A
GB786689A GB3202155A GB3202155A GB786689A GB 786689 A GB786689 A GB 786689A GB 3202155 A GB3202155 A GB 3202155A GB 3202155 A GB3202155 A GB 3202155A GB 786689 A GB786689 A GB 786689A
Authority
GB
United Kingdom
Prior art keywords
casing
flange
stage
segments
groove
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
GB3202155A
Inventor
Donald G Zimmerman
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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 Motors Liquidation Co filed Critical Motors Liquidation Co
Priority to GB3202155A priority Critical patent/GB786689A/en
Publication of GB786689A publication Critical patent/GB786689A/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
    • 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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

786,689. Bladed turbine casings. GENERAL MOTORS CORPORATION. Nov. 9, 1955, No. 32021/55. Class 110 (3). An elastic-fluid axial-flow turbine comprises an annular casing, a pair of stator vane shroud rings each divided axially into segments, a circumferentially-extending tongue and groove joint between the casing and the segments of both rings by which joint the segments are mounted and centred within the casing with freedom for expansion in the circumferential direction, keys being inserted into slots in the joint to locate the segments of each ring circumferentially so that there are expansion gaps between them when cold. A multi-stage axialflow gas turbine is shown and comprises four blading stages 54 carried on shroud rings 82, 88, 76, 70 which are in turn carried by the outer casing comprising an inlet portion 14, an intermediate portion 12 and an outlet portion 10. An exhaust casing structure 20 is connected to the portion 10. The bladed rotor discs are shown at 40 and the spacer discs at 42. The first stage shroud ring 82 is formed with a grooved flange 84 at its downstream end and a ridge 86 which bears against the casing portion 14. Flanges 66 on the intermediate casing 12 and 90 on the second stage shroud ring 88 are received in the groove in the flange 84 of the first stage shroud ring, the inlet and intermediate casings being connected together by bolts 18. The second stage shroud ring 88 is formed at its downstream end with a flange 92 which together with a flange 80 on the third stage shroud ring 76 is formed with a flange 78 and this together with a flange 62 on the downstream end of the intermediate casing 12 is received in a groove in the flange 72 on the upstream end of the fourth stage shroud ring 70. A flange 74 on the downstream end of the fourth stage shroud ring 70 is received in a groove 60 in the outlet casing portion 10. The circumferential tongue and groove joints between the shroud rings and the casing portions are slotted axially to receive keys 98, 96. The shroud rings are cut into segments by slots more or less parallel to the rotor axis so as to allow for expansion.
GB3202155A 1955-11-09 1955-11-09 Improvements relating to elastic-fluid turbines Expired GB786689A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3202155A GB786689A (en) 1955-11-09 1955-11-09 Improvements relating to elastic-fluid turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3202155A GB786689A (en) 1955-11-09 1955-11-09 Improvements relating to elastic-fluid turbines

Publications (1)

Publication Number Publication Date
GB786689A true GB786689A (en) 1957-11-20

Family

ID=10331869

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3202155A Expired GB786689A (en) 1955-11-09 1955-11-09 Improvements relating to elastic-fluid turbines

Country Status (1)

Country Link
GB (1) GB786689A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2422026A1 (en) * 1978-04-04 1979-11-02 Rolls Royce TURBOMOTOR HOUSING
US4573867A (en) * 1981-11-26 1986-03-04 Rolls-Royce Limited Housing for turbomachine rotors
US4650396A (en) * 1984-01-09 1987-03-17 Bbc Brown, Boveri & Company, Limited Externally adjustable axial location for a vane carrier in a turbine
WO1991019078A1 (en) * 1990-06-02 1991-12-12 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Guide-vane ring for a gas-turbine engine
US5320486A (en) * 1993-01-21 1994-06-14 General Electric Company Apparatus for positioning compressor liner segments
US5387082A (en) * 1992-10-05 1995-02-07 Asea Brown Boveri Ltd. Guide wave suspension for an axial-flow turbomachine
EP0973999A1 (en) * 1997-02-21 2000-01-26 Dresser-Rand Company Turbine diaphragm assembly and method thereof
JP2006183486A (en) * 2004-12-27 2006-07-13 Hitachi Ltd Steam turbine
CN102877901A (en) * 2012-10-23 2013-01-16 中国航空动力机械研究所 Cartridge receiver connection structure and gas turbine engine with same

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2422026A1 (en) * 1978-04-04 1979-11-02 Rolls Royce TURBOMOTOR HOUSING
US4573867A (en) * 1981-11-26 1986-03-04 Rolls-Royce Limited Housing for turbomachine rotors
US4650396A (en) * 1984-01-09 1987-03-17 Bbc Brown, Boveri & Company, Limited Externally adjustable axial location for a vane carrier in a turbine
WO1991019078A1 (en) * 1990-06-02 1991-12-12 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Guide-vane ring for a gas-turbine engine
US5269651A (en) * 1990-06-02 1993-12-14 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Guide vane ring of a turbine of a gas turbine engine
US5387082A (en) * 1992-10-05 1995-02-07 Asea Brown Boveri Ltd. Guide wave suspension for an axial-flow turbomachine
EP0608080A1 (en) * 1993-01-21 1994-07-27 General Electric Company Positioning means for a turbo engine liner
US5320486A (en) * 1993-01-21 1994-06-14 General Electric Company Apparatus for positioning compressor liner segments
EP0973999A1 (en) * 1997-02-21 2000-01-26 Dresser-Rand Company Turbine diaphragm assembly and method thereof
EP0973999A4 (en) * 1997-02-21 2001-10-17 Dresser Rand Co Turbine diaphragm assembly and method thereof
JP2006183486A (en) * 2004-12-27 2006-07-13 Hitachi Ltd Steam turbine
JP4507877B2 (en) * 2004-12-27 2010-07-21 株式会社日立製作所 Steam turbine
CN102877901A (en) * 2012-10-23 2013-01-16 中国航空动力机械研究所 Cartridge receiver connection structure and gas turbine engine with same
CN102877901B (en) * 2012-10-23 2015-07-15 中国航空动力机械研究所 Cartridge receiver connection structure and gas turbine engine with same

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