GB881880A - Turbo-machine stator construction - Google Patents

Turbo-machine stator construction

Info

Publication number
GB881880A
GB881880A GB1748859A GB1748859A GB881880A GB 881880 A GB881880 A GB 881880A GB 1748859 A GB1748859 A GB 1748859A GB 1748859 A GB1748859 A GB 1748859A GB 881880 A GB881880 A GB 881880A
Authority
GB
United Kingdom
Prior art keywords
flanges
segments
segment
secured
bracket
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
GB1748859A
Inventor
Leslie Thomas Whitehead
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB1748859A priority Critical patent/GB881880A/en
Publication of GB881880A publication Critical patent/GB881880A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • 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

Landscapes

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

Abstract

881,880. Turbine and compressor stator casings. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. May 17, 1960 [May 22, 1959], No. 17488/59. Classes 110 (1) and 110 (3). A turbine or compressor stator assembly comprises an outer casing and an inner shroud, the shroud comprising a circumferential series of segments, each segment being supported from the outer casing with freedom for radial movement and being resiliently loaded inwardly so that the adjacent edges of the segments are maintained in contact with one another. In a first embodiment the casing is shown at 1 and the shroud segments at 2, the segments being formed of sheet metal and having end flanges 2a and side flanges 2b, the axially-extending flanges 2a of adjacent segments abutting together. A channel-section bracket 3 having rectangular shaped slots 7 formed in its side flanges is secured to the outer surface of each segment and a guide member 4 secured to the outer casing 1 engages between the flanges of the bracket. A rectangular section key 6 is secured to the guide member 4 and projects through the rectangular slots 7 in the flanges of the bracket. Two arcuate-shaped leafsprings 8 are disposed one on either side of the flanges of the bracket 3, each spring bearing at its ends against the outer surface of a segment 2 and at its mid-point against the lower surface of a key 6, the spring being secured at one end to the segment, for example by welding. The side flanges 2b of the segments are extended at one end so as to close the triangular gaps between the end flanges 2a. In a second embodiment, Fig. 5, the side flanges of the brackets 3 are bent over at their outer ends to form flanges 3a, and the arcuate leaf springs 10 bear at their ends against the inner surface of the stator casing 1 and at their mid-points against the flanges 3a.
GB1748859A 1959-05-22 1959-05-22 Turbo-machine stator construction Expired GB881880A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1748859A GB881880A (en) 1959-05-22 1959-05-22 Turbo-machine stator construction

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1748859A GB881880A (en) 1959-05-22 1959-05-22 Turbo-machine stator construction

Publications (1)

Publication Number Publication Date
GB881880A true GB881880A (en) 1961-11-08

Family

ID=10096051

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1748859A Expired GB881880A (en) 1959-05-22 1959-05-22 Turbo-machine stator construction

Country Status (1)

Country Link
GB (1) GB881880A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3532437A (en) * 1967-11-03 1970-10-06 Sulzer Ag Stator blade assembly for axial-flow turbines
FR2450345A1 (en) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh DEVICE FOR MINIMIZING AND CONSTANTLY MAINTAINING GAMES EXISTING IN AXIAL TURBINES, IN PARTICULAR GAS TURBOMACHINES
FR2450344A1 (en) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh DEVICE FOR MINIMIZING AND MAINTAINING CONSTANT GAMES OF EXISTING BLADES IN AXIAL TURBINES, ESPECIALLY FOR GAS TURBOMACHINES
GB2117843A (en) * 1982-04-01 1983-10-19 Rolls Royce Compressor shrouds
GB2235730A (en) * 1989-09-08 1991-03-13 Gen Electric Blade tip clearance control apparatus for a gas turbine engine
EP0462735A2 (en) * 1990-06-21 1991-12-27 ROLLS-ROYCE plc Improvements in shroud assemblies for turbine rotors
WO1995013456A1 (en) * 1993-11-08 1995-05-18 United Technologies Corporation Turbine shroud segment
WO1996007018A1 (en) * 1994-08-31 1996-03-07 United Technologies Corporation Dynamic control of tip clearance
WO2004038182A1 (en) * 2002-10-23 2004-05-06 Pratt & Whitney Canada Corp. Sheet metal turbine or compressor static shroud
WO2018174739A1 (en) * 2017-03-21 2018-09-27 Siemens Aktiengesellschaft A system of providing mobility of a stator shroud in a turbine stage
FR3066782A1 (en) * 2017-05-24 2018-11-30 Safran Aircraft Engines TURBOMACHINE ARRANGEMENT COMPRISING A SEAL RING CONNECTED TO A CASING, AND METHOD OF MOUNTING
US10941942B2 (en) * 2014-12-31 2021-03-09 Rolls-Royce North American Technologies Inc. Retention system for gas turbine engine assemblies

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3532437A (en) * 1967-11-03 1970-10-06 Sulzer Ag Stator blade assembly for axial-flow turbines
FR2450345A1 (en) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh DEVICE FOR MINIMIZING AND CONSTANTLY MAINTAINING GAMES EXISTING IN AXIAL TURBINES, IN PARTICULAR GAS TURBOMACHINES
FR2450344A1 (en) * 1979-02-28 1980-09-26 Mtu Muenchen Gmbh DEVICE FOR MINIMIZING AND MAINTAINING CONSTANT GAMES OF EXISTING BLADES IN AXIAL TURBINES, ESPECIALLY FOR GAS TURBOMACHINES
GB2117843A (en) * 1982-04-01 1983-10-19 Rolls Royce Compressor shrouds
US4529355A (en) * 1982-04-01 1985-07-16 Rolls-Royce Limited Compressor shrouds and shroud assemblies
US5104287A (en) * 1989-09-08 1992-04-14 General Electric Company Blade tip clearance control apparatus for a gas turbine engine
GB2235730A (en) * 1989-09-08 1991-03-13 Gen Electric Blade tip clearance control apparatus for a gas turbine engine
FR2651831A1 (en) * 1989-09-08 1991-03-15 Gen Electric DEVICE FOR CONTROLLING THE EXTREMITY OF THE AUBES FOR GAS TURBINE ENGINE.
EP0462735A3 (en) * 1990-06-21 1992-07-22 Rolls-Royce Plc Improvements in shroud assemblies for turbine rotors
GB2245316A (en) * 1990-06-21 1992-01-02 Rolls Royce Plc Improvements in shroud assemblies for turbine rotors
EP0462735A2 (en) * 1990-06-21 1991-12-27 ROLLS-ROYCE plc Improvements in shroud assemblies for turbine rotors
US5161944A (en) * 1990-06-21 1992-11-10 Rolls-Royce Plc Shroud assemblies for turbine rotors
GB2245316B (en) * 1990-06-21 1993-12-15 Rolls Royce Plc Improvements in shroud assemblies for turbine rotors
WO1995013456A1 (en) * 1993-11-08 1995-05-18 United Technologies Corporation Turbine shroud segment
WO1996007018A1 (en) * 1994-08-31 1996-03-07 United Technologies Corporation Dynamic control of tip clearance
WO2004038182A1 (en) * 2002-10-23 2004-05-06 Pratt & Whitney Canada Corp. Sheet metal turbine or compressor static shroud
US6918743B2 (en) 2002-10-23 2005-07-19 Pratt & Whitney Canada Ccorp. Sheet metal turbine or compressor static shroud
US10941942B2 (en) * 2014-12-31 2021-03-09 Rolls-Royce North American Technologies Inc. Retention system for gas turbine engine assemblies
WO2018174739A1 (en) * 2017-03-21 2018-09-27 Siemens Aktiengesellschaft A system of providing mobility of a stator shroud in a turbine stage
FR3066782A1 (en) * 2017-05-24 2018-11-30 Safran Aircraft Engines TURBOMACHINE ARRANGEMENT COMPRISING A SEAL RING CONNECTED TO A CASING, AND METHOD OF MOUNTING

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