GB201209016D0 - Gas turbine - Google Patents

Gas turbine

Info

Publication number
GB201209016D0
GB201209016D0 GBGB1209016.3A GB201209016A GB201209016D0 GB 201209016 D0 GB201209016 D0 GB 201209016D0 GB 201209016 A GB201209016 A GB 201209016A GB 201209016 D0 GB201209016 D0 GB 201209016D0
Authority
GB
United Kingdom
Prior art keywords
ports
gas turbine
nozzle guide
dilution air
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.)
Pending
Application number
GBGB1209016.3A
Other versions
GB2502302A (en
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.)
Cranfield University
Original Assignee
Cranfield University
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 Cranfield University filed Critical Cranfield University
Priority to GB1209016.3A priority Critical patent/GB2502302A/en
Publication of GB201209016D0 publication Critical patent/GB201209016D0/en
Publication of GB2502302A publication Critical patent/GB2502302A/en
Pending 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
    • 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
    • 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

Abstract

In a gas turbine, a substantial amount of dilution air is introduced into turbine nozzle guide vane 80 from which it leaves via a plurality of ports 100, 101 in the external surfaces 110, 112 which extend between the leading and trailing edges 81, 82 of the vane. The ports 100, 101 are spaced and configured so as to provide a predetermined radial distribution of gas temperature at the nozzle guide vane exit plane (P, fig.3). The ports 100, 101 may be oriented at an angle T to promote tangential flow of dilution air as indicated by arrows 60.
GB1209016.3A 2012-05-22 2012-05-22 Gas turbine nozzle guide vane with dilution air exhaust ports Pending GB2502302A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1209016.3A GB2502302A (en) 2012-05-22 2012-05-22 Gas turbine nozzle guide vane with dilution air exhaust ports

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1209016.3A GB2502302A (en) 2012-05-22 2012-05-22 Gas turbine nozzle guide vane with dilution air exhaust ports

Publications (2)

Publication Number Publication Date
GB201209016D0 true GB201209016D0 (en) 2012-07-04
GB2502302A GB2502302A (en) 2013-11-27

Family

ID=46546494

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1209016.3A Pending GB2502302A (en) 2012-05-22 2012-05-22 Gas turbine nozzle guide vane with dilution air exhaust ports

Country Status (1)

Country Link
GB (1) GB2502302A (en)

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2725474B1 (en) * 1984-03-14 1996-12-13 Snecma COOLING TURBINE DISTRIBUTOR BLADE
JP3794868B2 (en) * 1999-06-15 2006-07-12 三菱重工業株式会社 Gas turbine stationary blade
IT1319140B1 (en) * 2000-11-28 2003-09-23 Nuovo Pignone Spa REFRIGERATION SYSTEM FOR STATIC GAS TURBINE NOZZLES
US6547524B2 (en) * 2001-05-21 2003-04-15 United Technologies Corporation Film cooled article with improved temperature tolerance
GB2405451B (en) * 2003-08-23 2008-03-19 Rolls Royce Plc Vane apparatus for a gas turbine engine
JP5039837B2 (en) * 2005-03-30 2012-10-03 三菱重工業株式会社 High temperature components for gas turbines
US7862299B1 (en) * 2007-03-21 2011-01-04 Florida Turbine Technologies, Inc. Two piece hollow turbine blade with serpentine cooling circuits
GB0905736D0 (en) * 2009-04-03 2009-05-20 Rolls Royce Plc Cooled aerofoil for a gas turbine engine

Also Published As

Publication number Publication date
GB2502302A (en) 2013-11-27

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Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)
S20A Reinstatement of application (sect. 20a/patents act 1977)

Free format text: REQUEST FOR REINSTATEMENT FILED

Effective date: 20141212

S20A Reinstatement of application (sect. 20a/patents act 1977)

Free format text: REQUEST FOR REINSTATEMENT REFUSED

Effective date: 20150130