GB2107405B - Nozzle guide vane for a gas turbine engine - Google Patents

Nozzle guide vane for a gas turbine engine

Info

Publication number
GB2107405B
GB2107405B GB08130908A GB8130908A GB2107405B GB 2107405 B GB2107405 B GB 2107405B GB 08130908 A GB08130908 A GB 08130908A GB 8130908 A GB8130908 A GB 8130908A GB 2107405 B GB2107405 B GB 2107405B
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
guide vane
nozzle guide
nozzle
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
GB08130908A
Other versions
GB2107405A (en
Inventor
Geoffrey Mathew Dailey
Anthony George Gale
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 GB08130908A priority Critical patent/GB2107405B/en
Publication of GB2107405A publication Critical patent/GB2107405A/en
Application granted granted Critical
Publication of GB2107405B publication Critical patent/GB2107405B/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
GB08130908A 1981-10-13 1981-10-13 Nozzle guide vane for a gas turbine engine Expired GB2107405B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB08130908A GB2107405B (en) 1981-10-13 1981-10-13 Nozzle guide vane for a gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08130908A GB2107405B (en) 1981-10-13 1981-10-13 Nozzle guide vane for a gas turbine engine

Publications (2)

Publication Number Publication Date
GB2107405A GB2107405A (en) 1983-04-27
GB2107405B true GB2107405B (en) 1985-08-14

Family

ID=10525140

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08130908A Expired GB2107405B (en) 1981-10-13 1981-10-13 Nozzle guide vane for a gas turbine engine

Country Status (1)

Country Link
GB (1) GB2107405B (en)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2242941B (en) * 1990-04-11 1994-05-04 Rolls Royce Plc A cooled gas turbine engine aerofoil
US5197852A (en) * 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
FR2672003B1 (en) * 1991-01-30 1993-04-09 Snecma PROCESS FOR PRODUCING COMPLEX CERAMIC CORES FOR FOUNDRY.
FR2672338B1 (en) * 1991-02-06 1993-04-16 Snecma TURBINE BLADE PROVIDED WITH A COOLING SYSTEM.
GB2253443A (en) * 1991-03-05 1992-09-09 Rolls Royce Plc Gas turbine nozzle guide vane arrangement
FR2678318B1 (en) * 1991-06-25 1993-09-10 Snecma COOLED VANE OF TURBINE DISTRIBUTOR.
GB9305010D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc A cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly
US7452189B2 (en) 2006-05-03 2008-11-18 United Technologies Corporation Ceramic matrix composite turbine engine vane
WO2009016744A1 (en) * 2007-07-31 2009-02-05 Mitsubishi Heavy Industries, Ltd. Wing for turbine
FR3074521B1 (en) 2017-12-06 2019-11-22 Safran Aircraft Engines TURBINE DISPENSER SECTOR FOR AN AIRCRAFT TURBOMACHINE
US11078844B2 (en) 2018-11-21 2021-08-03 Raytheon Technologies Corporation Thermal gradient reducing device for gas turbine engine component

Also Published As

Publication number Publication date
GB2107405A (en) 1983-04-27

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee

Effective date: 19961013