GB1193587A - Nozzle Guide Vanes for Gas Turbine Engines. - Google Patents

Nozzle Guide Vanes for Gas Turbine Engines.

Info

Publication number
GB1193587A
GB1193587A GB06961/68A GB1696168A GB1193587A GB 1193587 A GB1193587 A GB 1193587A GB 06961/68 A GB06961/68 A GB 06961/68A GB 1696168 A GB1696168 A GB 1696168A GB 1193587 A GB1193587 A GB 1193587A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
guide vanes
passages
vane
nozzle guide
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
GB06961/68A
Inventor
Kenneth Miller
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 GB06961/68A priority Critical patent/GB1193587A/en
Priority to FR6910375A priority patent/FR2005832A1/en
Priority to DE19691917906 priority patent/DE1917906A1/en
Publication of GB1193587A publication Critical patent/GB1193587A/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
    • F01D9/041—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

1,193,587. Turbines; gas turbine plant. ROLLS-ROYCE Ltd. April 2, 1969 [April 9, 1968], No.16961/68. Headings F1G and F1T. The nozzle guide vanes 20 at the downstream end of a combustion chamber flame tube 16 in a gas turbine engine are cooled by air directed through passages 24, 25 in the inner and outer shrouds 22, 23 of each vane on to the vane leading edge 21. Some of the passages 24, 25 may have short silicon nitride tubes (30) fitted therein, Fig. 3 (not shown). Each vane may be solid or hollow and the leading edge 21 is radially channelled so as to guide the air from passages 23, 24 along the edge. The flame tube 16 may be annular or cylindrical.
GB06961/68A 1968-04-09 1968-04-09 Nozzle Guide Vanes for Gas Turbine Engines. Expired GB1193587A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB06961/68A GB1193587A (en) 1968-04-09 1968-04-09 Nozzle Guide Vanes for Gas Turbine Engines.
FR6910375A FR2005832A1 (en) 1968-04-09 1969-04-04 Guide vane for gas turbine or jet engine nozzle
DE19691917906 DE1917906A1 (en) 1968-04-09 1969-04-08 Nozzle guide vane for gas turbine engines

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
GB1193587A true GB1193587A (en) 1970-06-03

Family

ID=10086767

Family Applications (1)

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

Country Status (3)

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

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2119861A (en) * 1982-05-03 1983-11-23 Gen Electric Cooling high pressure turbine blade tips in a gas turbine engine
US4733538A (en) * 1978-10-02 1988-03-29 General Electric Company Combustion selective temperature dilution
GB2210415A (en) * 1987-09-25 1989-06-07 Toshiba Kk Turbine vane with cooling features
US5407319A (en) * 1993-03-11 1995-04-18 Rolls-Royce Plc Sealing structures for gas turbine engines
US5417545A (en) * 1993-03-11 1995-05-23 Rolls-Royce Plc Cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly
WO2004038181A1 (en) * 2002-10-23 2004-05-06 Pratt & Whitney Canada Corp. Aerodynamic method to reduce noise level in gas turbines
EP2290195A3 (en) * 2009-08-28 2013-10-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
EP2877726A4 (en) * 2012-07-27 2016-08-03 United Technologies Corp Turbine engine combustor and stator vane assembly

Cited By (13)

* 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
GB2119861A (en) * 1982-05-03 1983-11-23 Gen Electric Cooling high pressure turbine blade tips in a gas turbine engine
GB2210415A (en) * 1987-09-25 1989-06-07 Toshiba Kk Turbine vane with cooling features
GB2210415B (en) * 1987-09-25 1992-04-22 Toshiba Kk Gas turbine vane
US5470198A (en) * 1993-03-11 1995-11-28 Rolls-Royce Plc Sealing structures for gas turbine engines
US5417545A (en) * 1993-03-11 1995-05-23 Rolls-Royce Plc Cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly
US5407319A (en) * 1993-03-11 1995-04-18 Rolls-Royce Plc Sealing structures for gas turbine engines
WO2004038181A1 (en) * 2002-10-23 2004-05-06 Pratt & Whitney Canada Corp. Aerodynamic method to reduce noise level in gas turbines
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
US7533534B2 (en) 2002-10-23 2009-05-19 Pratt & Whitney Canada Corp. HPT aerodynamic trip to improve acoustic transmission loss and reduce noise level for auxiliary power unit
EP2290195A3 (en) * 2009-08-28 2013-10-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
US9650903B2 (en) 2009-08-28 2017-05-16 United Technologies Corporation Combustor turbine interface for a gas turbine engine
EP2877726A4 (en) * 2012-07-27 2016-08-03 United Technologies Corp Turbine engine combustor and stator vane assembly

Also Published As

Publication number Publication date
DE1917906A1 (en) 1970-02-19
FR2005832A1 (en) 1969-12-19

Similar Documents

Publication Publication Date Title
GB1351029A (en) Turbo machinery blade cooling
GB1473866A (en) Gas turbine power plant
GB1048968A (en) Combustion chamber for a gas turbine engine
GB1052328A (en) Improvements in or relating to gas turbine engine combustion equipment
GB1427146A (en) Combustion apparatus for gas turbine engines
GB925388A (en) Improvements relating to turbine nozzle vane mounting means
GB584820A (en) Improvements relating to internal combustion prime movers
GB1034260A (en) Aerofoil-shaped blade for use in a fluid flow machine
GB774425A (en) Improvements in or relating to turbine engines
GB1094540A (en) Improvements in or relating to annular combustion chambers for gas turbine engines
GB1193587A (en) Nozzle Guide Vanes for Gas Turbine Engines.
GB1116930A (en) Improvements in cooled flameholder assembly
GB1524956A (en) Gas tubine engine
GB1318167A (en) Inlet structure for turbo machine
GB924333A (en) Annular transition duct for a gas turbine jet propulsion engine
GB1017900A (en) Combustion chambers
GB1070480A (en) Aerofoil shaped blade for a fluid flow machine such as a gas turbine engine
US3390521A (en) Gas turbine engine
GB1424552A (en) Inlet structure for turbine
GB737081A (en) Improvements relating to jet propulsion engines
GB1069199A (en) Improvements in means for starting gas turbine engines
GB744548A (en) Improvements in or relating to gas turbines
GB1516177A (en) Fuel combustion apparatus
GB622411A (en) Improvements relating to gas-turbine-engines
GB579511A (en) Improvements in or relating to jet-propulsion apparatus for aircraft

Legal Events

Date Code Title Description
PS Patent sealed
PLE Entries relating assignments, transmissions, licences in the register of patents
PLNP Patent lapsed through nonpayment of renewal fees