GB805545A - Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines - Google Patents

Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines

Info

Publication number
GB805545A
GB805545A GB370356A GB370356A GB805545A GB 805545 A GB805545 A GB 805545A GB 370356 A GB370356 A GB 370356A GB 370356 A GB370356 A GB 370356A GB 805545 A GB805545 A GB 805545A
Authority
GB
United Kingdom
Prior art keywords
casing
ring
dogs
axial
shroud ring
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
GB370356A
Inventor
Frederick William Walto Morley
Leslie James Pratt
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 GB370356A priority Critical patent/GB805545A/en
Publication of GB805545A publication Critical patent/GB805545A/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
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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

805,545. Turbine stator structure. ROLLSROYCE Ltd. Feb. 6, 1957 [Feb. 6, 1956], No. 3703/56. Class 110 (3). In an axial-flow machine such as an axialflow turbine of a gas turbine engine, the casing 10 is wholly tubular (i.e. it is unsplit diametrically) and shrouding for a ring of rotor blades is disposed within the casing. The shrouding consists of an undivided annular shroud ring 20 which encircles the rotor blades 12 and is so dimensioned as to be spaced radially inwards from the casing, the shroud ring being located circumferentially by means of radial dogs 24 at the downstream end of the ring which engage between radial dogs 25 formed on the inner surface of the casing. The shroud ring abuts at its downstream end against a ring member 26 which is located axially by means of radial lugs 27 thereon engaging in a circumferentially-extending groove formed between the dogs 25 and aligned dogs 28 on the casing. The ring member 26 is located circumferentially by means of an axial projection 30 thereon which engages between a pair of the dogs 29 formed on the nozzle guide vanes 15, the dogs 29 also interengaging with the dogs 28 on the casing whereby the guide vanes are positioned circumferentially. Axial movement of the shroud ring 20 in an upstream direction is limited by means of an abutment surface 33 on the casing 10. A piston-ring type of sealing ring 31 is disposed within a groove 32 at the upstream end of the shroud ring 20 and cooperates with the casing 10 to prevent flow of working fluid through the space between the casing and the shroud ring 20. The downstream surfaces of the sealing ring and the groove in which it is mounted are frusto-conical, the sealing ring and groove being in contact only over these surfaces. The casing 10 is formed of a number of axially-abutting sections which are joined by means of bolting flanges 11. The shroud ring 20 is formed with circumferential ribs 21, 22, the ribs 21 on the inner surface co-operating with ribs 23 on the rotor blade tip shrouds 17 to prevent leakage of working fluid
GB370356A 1956-02-06 1956-02-06 Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines Expired GB805545A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB370356A GB805545A (en) 1956-02-06 1956-02-06 Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB370356A GB805545A (en) 1956-02-06 1956-02-06 Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines

Publications (1)

Publication Number Publication Date
GB805545A true GB805545A (en) 1958-12-10

Family

ID=9763355

Family Applications (1)

Application Number Title Priority Date Filing Date
GB370356A Expired GB805545A (en) 1956-02-06 1956-02-06 Improvements in or relating to axial-flow fluid machines for example axial-flow turbines of gas-turbine engines

Country Status (1)

Country Link
GB (1) GB805545A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3053510A (en) * 1959-02-20 1962-09-11 United Aircraft Corp Radiator spline and support system
US3064947A (en) * 1959-02-20 1962-11-20 United Aircraft Corp Involute flat tube and plate fin radiator
DE1278178B (en) * 1966-06-10 1968-09-19 Rolls Royce Inlet guide vane ring for axial compressors of gas turbine engines
GB2171458A (en) * 1985-02-25 1986-08-28 Gen Electric Removable stiffening disk
EP0668434A1 (en) * 1994-02-22 1995-08-23 Pratt & Whitney Canada, Inc. Gas turbine engine component retention
WO2003001036A1 (en) * 2001-06-25 2003-01-03 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
JP2004176911A (en) * 2002-11-27 2004-06-24 General Electric Co <Ge> Structure for mounting components having different coefficient or rate of thermal expansion or sealing space between the components
CN101952556A (en) * 2008-03-31 2011-01-19 三菱重工业株式会社 Rotary mechanism scroll structure and rotary mechanism
FR2980235A1 (en) * 2011-09-20 2013-03-22 Snecma Low pressure turbine for use in e.g. turboprop engine of aircraft, has ring radially guided on turbine casing such that casing is deformed freely in radial direction, by thermal dilation, without forcing ring to deform radially
EP2824278A1 (en) * 2013-07-08 2015-01-14 MTU Aero Engines GmbH Device, blade-device group, method and flow engine
CN109882255A (en) * 2019-03-01 2019-06-14 西安航天动力研究所 Position limiting structure is obturaged at the top of stators with blade type wire casing
CN110735667A (en) * 2018-07-18 2020-01-31 赛峰飞机发动机公司 Sealing assembly for a turbine rotor of a turbomachine and corresponding turbine

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3053510A (en) * 1959-02-20 1962-09-11 United Aircraft Corp Radiator spline and support system
US3064947A (en) * 1959-02-20 1962-11-20 United Aircraft Corp Involute flat tube and plate fin radiator
DE1278178B (en) * 1966-06-10 1968-09-19 Rolls Royce Inlet guide vane ring for axial compressors of gas turbine engines
GB2171458A (en) * 1985-02-25 1986-08-28 Gen Electric Removable stiffening disk
GB2171458B (en) * 1985-02-25 1989-11-22 Gen Electric Improvements in gas turbine engines
EP0668434A1 (en) * 1994-02-22 1995-08-23 Pratt & Whitney Canada, Inc. Gas turbine engine component retention
WO2003001036A1 (en) * 2001-06-25 2003-01-03 Pratt & Whitney Canada Corp. Segmented turbine vane support structure
EP1426561A3 (en) * 2002-11-27 2005-05-25 General Electric Company Structures for attaching or sealing a space between components having different coefficients or rates of thermal expansion
JP2004176911A (en) * 2002-11-27 2004-06-24 General Electric Co <Ge> Structure for mounting components having different coefficient or rate of thermal expansion or sealing space between the components
CN101952556A (en) * 2008-03-31 2011-01-19 三菱重工业株式会社 Rotary mechanism scroll structure and rotary mechanism
US8757964B2 (en) 2008-03-31 2014-06-24 Pebble Bed Modular Reactor (Pty) Limited Rotary machine scroll structure and rotary machine
CN101952556B (en) * 2008-03-31 2015-03-04 三菱重工业株式会社 Rotary machine
FR2980235A1 (en) * 2011-09-20 2013-03-22 Snecma Low pressure turbine for use in e.g. turboprop engine of aircraft, has ring radially guided on turbine casing such that casing is deformed freely in radial direction, by thermal dilation, without forcing ring to deform radially
EP2824278A1 (en) * 2013-07-08 2015-01-14 MTU Aero Engines GmbH Device, blade-device group, method and flow engine
US10323527B2 (en) 2013-07-08 2019-06-18 Mtu Aero Engines Gmbh Blade row poisitioning device, blade-device combination, method and turbomachine
CN110735667A (en) * 2018-07-18 2020-01-31 赛峰飞机发动机公司 Sealing assembly for a turbine rotor of a turbomachine and corresponding turbine
CN109882255A (en) * 2019-03-01 2019-06-14 西安航天动力研究所 Position limiting structure is obturaged at the top of stators with blade type wire casing

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