FR2005832A1 - Guide vane for gas turbine or jet engine nozzle - Google Patents

Guide vane for gas turbine or jet engine nozzle

Info

Publication number
FR2005832A1
FR2005832A1 FR6910375A FR6910375A FR2005832A1 FR 2005832 A1 FR2005832 A1 FR 2005832A1 FR 6910375 A FR6910375 A FR 6910375A FR 6910375 A FR6910375 A FR 6910375A FR 2005832 A1 FR2005832 A1 FR 2005832A1
Authority
FR
France
Prior art keywords
cooling air
leading edge
gas turbine
annulus
jet engine
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.)
Withdrawn
Application number
FR6910375A
Other languages
French (fr)
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
Publication of FR2005832A1 publication Critical patent/FR2005832A1/en
Withdrawn legal-status Critical Current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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

Guide vane for gas turbine or jet engine nozzle having at least a part of its annulus extending up stream of leading edge of vane and presenting an opening allowing-during operation - for hte cooling air to flow in the direction of the exterior surface of this leading edge. (1) vane has a part of annulus in advance of each of its opposite extremities, in the radial direction, allowing it to receive during operation cooling air coming from each of its extremities. (1) At least a part of, or each part of, the annulus in pierced in order to direct cooling air-with a substantial radial flow component - onto the leading edge. Same openings at least have short tubes fitted which improve penetration of cooling air into gas flow; each tube is of silicum nitride.
FR6910375A 1968-04-09 1969-04-04 Guide vane for gas turbine or jet engine nozzle Withdrawn FR2005832A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB06961/68A GB1193587A (en) 1968-04-09 1968-04-09 Nozzle Guide Vanes for Gas Turbine Engines.

Publications (1)

Publication Number Publication Date
FR2005832A1 true FR2005832A1 (en) 1969-12-19

Family

ID=10086767

Family Applications (1)

Application Number Title Priority Date Filing Date
FR6910375A Withdrawn FR2005832A1 (en) 1968-04-09 1969-04-04 Guide vane for gas turbine or jet engine nozzle

Country Status (3)

Country Link
DE (1) DE1917906A1 (en)
FR (1) FR2005832A1 (en)
GB (1) GB1193587A (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4733538A (en) * 1978-10-02 1988-03-29 General Electric Company Combustion selective temperature dilution
USH903H (en) 1982-05-03 1991-04-02 General Electric Company Cool tip combustor
JP2862536B2 (en) * 1987-09-25 1999-03-03 株式会社東芝 Gas turbine blades
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
GB9305012D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Sealing structures for gas turbine engines
RU2143562C1 (en) * 1997-09-23 1999-12-27 Открытое акционерное общество "А.Люлька-Сатурн" Gas turbine nozzle unit
US7234304B2 (en) 2002-10-23 2007-06-26 Pratt & Whitney Canada Corp Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
US9650903B2 (en) 2009-08-28 2017-05-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
US9010122B2 (en) * 2012-07-27 2015-04-21 United Technologies Corporation Turbine engine combustor and stator vane assembly

Also Published As

Publication number Publication date
DE1917906A1 (en) 1970-02-19
GB1193587A (en) 1970-06-03

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Legal Events

Date Code Title Description
TP Transmission of property
TP Transmission of property
ST Notification of lapse