GB1328426A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1328426A
GB1328426A GB1328426DA GB1328426A GB 1328426 A GB1328426 A GB 1328426A GB 1328426D A GB1328426D A GB 1328426DA GB 1328426 A GB1328426 A GB 1328426A
Authority
GB
United Kingdom
Prior art keywords
lining
guide vanes
shroud ring
gas turbine
guide vane
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
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.)
British Leyland Truck and Bus Div Ltd
Original Assignee
British Leyland Truck and Bus Div 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 British Leyland Truck and Bus Div Ltd filed Critical British Leyland Truck and Bus Div Ltd
Publication of GB1328426A publication Critical patent/GB1328426A/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

Landscapes

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

Abstract

1328426 Gas turbine inlet nozzle guide vane assembly BRITISH LEYLAND TRUCK & BUS DIVISION Ltd 5 July 1972 [28 Aug 1971] 40463/71 Heading FIT The invention relates to a nozzle guide vane assembly of a gas turbine engine which comprises a series of nozzle guide vanes 3 surrounded by but not connected to an outer shroud ring 5. The surface 4 of the shroud ring adjacent the tips of the guide vanes is afforded by a lining 6 such that when the guide vanes 3 and the shroud ring 5 are cold there is minimal clearance between the tips of the guide vanes and the surface 4 of the lining 6. The lining is formed of soft material such as porous nickel felt which is both erosion- and heatresistant and which is indented by the guide vanes when these expand relative to the shroud ring. In normal operation a gap is formed between the tip of each guide vane and the indentation in the lining. The lining is brazed into position and subsequently chrome-aluminized.
GB1328426D 1971-08-28 1971-08-28 Gas turbine engines Expired GB1328426A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4046371 1971-08-28

Publications (1)

Publication Number Publication Date
GB1328426A true GB1328426A (en) 1973-08-30

Family

ID=10415023

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1328426D Expired GB1328426A (en) 1971-08-28 1971-08-28 Gas turbine engines

Country Status (4)

Country Link
JP (1) JPS4833212A (en)
DE (1) DE2238178A1 (en)
GB (1) GB1328426A (en)
IT (1) IT962228B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110311355A1 (en) * 2009-02-13 2011-12-22 Francois Benkler Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses
US9260784B2 (en) 2009-08-06 2016-02-16 Mtu Aero Engines Gmbh Blade tip coating that can be rubbed off
FR3082555A1 (en) * 2018-06-18 2019-12-20 Safran Aircraft Engines RECTIFIER BLADE WHEEL OF AN AIRCRAFT ENGINE, SUCH AS A TURBOJET

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2039756A1 (en) * 1990-05-31 1991-12-01 Larry Wayne Plemmons Stator having selectively applied thermal conductivity coating
EP1571181A3 (en) 2004-02-24 2008-08-13 FUJIFILM Corporation Inorganic fine particle dispersion and manufacturing method thereof as well as image-recording material

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110311355A1 (en) * 2009-02-13 2011-12-22 Francois Benkler Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses
US9260784B2 (en) 2009-08-06 2016-02-16 Mtu Aero Engines Gmbh Blade tip coating that can be rubbed off
FR3082555A1 (en) * 2018-06-18 2019-12-20 Safran Aircraft Engines RECTIFIER BLADE WHEEL OF AN AIRCRAFT ENGINE, SUCH AS A TURBOJET

Also Published As

Publication number Publication date
IT962228B (en) 1973-12-20
DE2238178A1 (en) 1973-03-01
JPS4833212A (en) 1973-05-08

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees