GB1516757A - Turbomachinery vane or blade with cooled platforms - Google Patents

Turbomachinery vane or blade with cooled platforms

Info

Publication number
GB1516757A
GB1516757A GB39956/76A GB3995676A GB1516757A GB 1516757 A GB1516757 A GB 1516757A GB 39956/76 A GB39956/76 A GB 39956/76A GB 3995676 A GB3995676 A GB 3995676A GB 1516757 A GB1516757 A GB 1516757A
Authority
GB
United Kingdom
Prior art keywords
platform
cooled
drillings
blade
ribs
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
GB39956/76A
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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
Priority claimed from US05/622,322 external-priority patent/US4017213A/en
Priority claimed from US05/622,321 external-priority patent/US4012167A/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of GB1516757A publication Critical patent/GB1516757A/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
    • 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
    • F01D5/187—Convection cooling
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Landscapes

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

Abstract

1516757 Turbine and compressor blades UNITED TECHNOLOGIES CORP 27 Sept 1976 [14 Oct 1975 (2)] 39956/76 Heading F1T A compressor or turbine rotor or stator blade platform is cooled using a combination of impingement, convection and film cooling. In the case of a gas turbine nozzle blade 14 having outer and inner platforms, the latter 18 has recesses 90, 92 in its surface remote from the working gas which are covered by plates 106, 124 having ports 108, 126 through which impingement cooling air enters the recesses. Ribs 110 adjacent ports 108 divide recess 90 into discrete cavities 112 from which the air flows into a rearwardly directed main flow duct 114 before exhausting through passages 118 to film cool the working gas surface 24 of the platform. Ribs 110 are omitted from recess 92. The trailing edge region of the platform is cooled by air flowing through intersecting drillings 136, 132. In the region of feather seals 142, the drillings 136 are replaced by elongated slots 148 connecting with two adjacent drillings 132a, b. Outer platform (16) Figs. 1, 2 (not shown) may be similarly cooled.
GB39956/76A 1975-10-14 1976-09-27 Turbomachinery vane or blade with cooled platforms Expired GB1516757A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US05/622,322 US4017213A (en) 1975-10-14 1975-10-14 Turbomachinery vane or blade with cooled platforms
US05/622,321 US4012167A (en) 1975-10-14 1975-10-14 Turbomachinery vane or blade with cooled platforms

Publications (1)

Publication Number Publication Date
GB1516757A true GB1516757A (en) 1978-07-05

Family

ID=27089183

Family Applications (1)

Application Number Title Priority Date Filing Date
GB39956/76A Expired GB1516757A (en) 1975-10-14 1976-09-27 Turbomachinery vane or blade with cooled platforms

Country Status (7)

Country Link
BR (1) BR7606847A (en)
DE (1) DE2643049A1 (en)
FR (1) FR2328106A1 (en)
GB (1) GB1516757A (en)
IT (1) IT1068785B (en)
NO (1) NO763456L (en)
SE (1) SE7610963L (en)

Cited By (11)

* 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
GB2223276A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Cooling turbine blade shrouds
GB2253443A (en) * 1991-03-05 1992-09-09 Rolls Royce Plc Gas turbine nozzle guide vane arrangement
GB2290833A (en) * 1994-07-02 1996-01-10 Rolls Royce Plc Turbine blade cooling
WO2000012869A1 (en) * 1998-08-31 2000-03-09 Siemens Aktiengesellschaft Turbine guide blade
EP1329593A1 (en) * 2002-01-17 2003-07-23 Siemens Aktiengesellschaft Turbine-blade
GB2408780A (en) * 2003-12-04 2005-06-08 Gen Electric Cooling sidewalls of turbine nozzle segments
US10041357B2 (en) 2015-01-20 2018-08-07 United Technologies Corporation Cored airfoil platform with outlet slots
US10156150B2 (en) 2013-03-14 2018-12-18 United Technologies Corporation Gas turbine engine stator vane platform cooling
US10612390B2 (en) 2017-01-26 2020-04-07 United Technologies Corporation Trailing edge pressure and flow regulator
CN113202567A (en) * 2021-05-25 2021-08-03 中国航发沈阳发动机研究所 Design method for cooling structure of guide cooling blade edge plate of high-pressure turbine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002512334A (en) 1998-04-21 2002-04-23 シーメンス アクチエンゲゼルシヤフト Turbine blade
DE10016081A1 (en) * 2000-03-31 2001-10-04 Alstom Power Nv Plate-shaped, projecting component section of a gas turbine
GB2395987B (en) 2002-12-02 2005-12-21 Alstom Turbine blade with cooling bores
CN103786996A (en) * 2012-10-31 2014-05-14 鎧悅國際有限公司 Flower freshness retaining pipe

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3515499A (en) * 1968-04-22 1970-06-02 Aerojet General Co Blades and blade assemblies for turbine engines,compressors and the like
BE755567A (en) * 1969-12-01 1971-02-15 Gen Electric FIXED VANE STRUCTURE, FOR GAS TURBINE ENGINE AND ASSOCIATED TEMPERATURE ADJUSTMENT ARRANGEMENT
US3800864A (en) * 1972-09-05 1974-04-02 Gen Electric Pin-fin cooling system
IT1079131B (en) * 1975-06-30 1985-05-08 Gen Electric IMPROVED COOLING APPLICABLE IN PARTICULAR TO ELEMENTS OF GAS TURBO ENGINES

Cited By (22)

* 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
GB2223276A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Cooling turbine blade shrouds
US4948338A (en) * 1988-09-30 1990-08-14 Rolls-Royce Plc Turbine blade with cooled shroud abutment surface
GB2223276B (en) * 1988-09-30 1992-09-02 Rolls Royce Plc Turbine aerofoil blade
GB2253443A (en) * 1991-03-05 1992-09-09 Rolls Royce Plc Gas turbine nozzle guide vane arrangement
GB2290833A (en) * 1994-07-02 1996-01-10 Rolls Royce Plc Turbine blade cooling
US5531568A (en) * 1994-07-02 1996-07-02 Rolls-Royce Plc Turbine blade
GB2290833B (en) * 1994-07-02 1998-08-05 Rolls Royce Plc Turbine blade
WO2000012869A1 (en) * 1998-08-31 2000-03-09 Siemens Aktiengesellschaft Turbine guide blade
US6558115B2 (en) 1998-08-31 2003-05-06 Siemens Aktiengesellschaft Turbine guide blade
US6887040B2 (en) 2001-09-12 2005-05-03 Siemens Aktiengesellschaft Turbine blade/vane
EP1329593A1 (en) * 2002-01-17 2003-07-23 Siemens Aktiengesellschaft Turbine-blade
GB2408780A (en) * 2003-12-04 2005-06-08 Gen Electric Cooling sidewalls of turbine nozzle segments
US7029228B2 (en) 2003-12-04 2006-04-18 General Electric Company Method and apparatus for convective cooling of side-walls of turbine nozzle segments
GB2408780B (en) * 2003-12-04 2008-01-30 Gen Electric Method and apparatus for convective cooling of side-walls of turbine nozzle segments
US10156150B2 (en) 2013-03-14 2018-12-18 United Technologies Corporation Gas turbine engine stator vane platform cooling
US10041357B2 (en) 2015-01-20 2018-08-07 United Technologies Corporation Cored airfoil platform with outlet slots
US10808549B2 (en) 2015-01-20 2020-10-20 Raytheon Technologies Corporation Cored airfoil platform with outlet slots
US10612390B2 (en) 2017-01-26 2020-04-07 United Technologies Corporation Trailing edge pressure and flow regulator
US11492912B2 (en) 2017-01-26 2022-11-08 Raytheon Technologies Corporation Trailing edge pressure and flow regulator
CN113202567A (en) * 2021-05-25 2021-08-03 中国航发沈阳发动机研究所 Design method for cooling structure of guide cooling blade edge plate of high-pressure turbine
CN113202567B (en) * 2021-05-25 2022-10-28 中国航发沈阳发动机研究所 Design method of cooling structure of guide cooling blade edge plate of high-pressure turbine

Also Published As

Publication number Publication date
BR7606847A (en) 1977-08-30
IT1068785B (en) 1985-03-21
NO763456L (en) 1977-04-15
SE7610963L (en) 1977-04-15
FR2328106A1 (en) 1977-05-13
DE2643049A1 (en) 1977-04-21

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee