GB641146A - Improvements in turbine blades - Google Patents

Improvements in turbine blades

Info

Publication number
GB641146A
GB641146A GB2051248A GB2051248A GB641146A GB 641146 A GB641146 A GB 641146A GB 2051248 A GB2051248 A GB 2051248A GB 2051248 A GB2051248 A GB 2051248A GB 641146 A GB641146 A GB 641146A
Authority
GB
United Kingdom
Prior art keywords
passages
cooling
turbine blades
gas turbine
cores
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
GB2051248A
Inventor
Austin Geoffrey Smith
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB2051248A priority Critical patent/GB641146A/en
Publication of GB641146A publication Critical patent/GB641146A/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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall

Landscapes

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

Abstract

641,146. Gas turbine blades. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Aug. 3, 1948, No. 20512. [Class 110(iii)] Longitudinal passages for cooling fluid in gas turbine blades are arranged to provide a differential cooling such that a constant temperature obtains over any normal section. The Figure shows a rotor blade with cooling passages 2 more crowded at the leading and trailing portions where the absorption of heat from the working gas is greater. In an alternative, large holes, evenly spaced, are provided with finned cores or multi-start threaded cores which vary the cooling value of the several passages. The flow of coolant may be determined by metering constrictions in the passages. Reference has been directed by the Comptroller to Specification 651,830.
GB2051248A 1948-08-03 1948-08-03 Improvements in turbine blades Expired GB641146A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2051248A GB641146A (en) 1948-08-03 1948-08-03 Improvements in turbine blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2051248A GB641146A (en) 1948-08-03 1948-08-03 Improvements in turbine blades

Publications (1)

Publication Number Publication Date
GB641146A true GB641146A (en) 1950-08-02

Family

ID=10147111

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2051248A Expired GB641146A (en) 1948-08-03 1948-08-03 Improvements in turbine blades

Country Status (1)

Country Link
GB (1) GB641146A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2906494A (en) * 1956-06-12 1959-09-29 Daniel J Mccarty Heat responsive means for blade cooling
US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US4531889A (en) * 1980-08-08 1985-07-30 General Electric Co. Cooling system utilizing flow resistance devices to distribute liquid coolant to air foil distribution channels
US5125798A (en) * 1990-04-13 1992-06-30 General Electric Company Method and apparatus for cooling air flow at gas turbine bucket trailing edge tip
EP1947295A1 (en) * 2007-01-18 2008-07-23 Siemens Aktiengesellschaft Vane plug of an axial turbine vane
CN102762816B (en) * 2009-09-04 2015-08-12 西门子公司 The assembly of turbo machine

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US2906494A (en) * 1956-06-12 1959-09-29 Daniel J Mccarty Heat responsive means for blade cooling
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US4531889A (en) * 1980-08-08 1985-07-30 General Electric Co. Cooling system utilizing flow resistance devices to distribute liquid coolant to air foil distribution channels
US5125798A (en) * 1990-04-13 1992-06-30 General Electric Company Method and apparatus for cooling air flow at gas turbine bucket trailing edge tip
EP1947295A1 (en) * 2007-01-18 2008-07-23 Siemens Aktiengesellschaft Vane plug of an axial turbine vane
CN102762816B (en) * 2009-09-04 2015-08-12 西门子公司 The assembly of turbo machine
US9249671B2 (en) 2009-09-04 2016-02-02 Siemens Aktiengesellschaft Method and a device of tangentially biasing internal cooling on nozzle guide vanes

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