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GB834811A - Cooled hollow turbine blades - Google Patents

Cooled hollow turbine blades

Info

Publication number
GB834811A
GB834811A GB15147/56A GB1514756A GB834811A GB 834811 A GB834811 A GB 834811A GB 15147/56 A GB15147/56 A GB 15147/56A GB 1514756 A GB1514756 A GB 1514756A GB 834811 A GB834811 A GB 834811A
Authority
GB
United Kingdom
Prior art keywords
blade
passage
partition
internal surface
adjacent
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
GB15147/56A
Inventor
Michael Joseph French
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son 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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Publication of GB834811A publication Critical patent/GB834811A/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
    • 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

834,811. Turbine blades. NAPIER & SON Ltd., D. May 7, 1957 [May 15, 1956], No. 15147/56. Class 110 (3). A hollow turbine blade is provided with a partition which divides the hollow interior of the blade chordwise so as to provide two longitudinal passages for the flow of cooling fluid through it, the cooling fluid flowing longitudinally through one of the passages from the root end of the blade, through at least one aperture in the partition adjacent the leading edge of the blade in a direction approximately transverse to the length of the blade and thence transversely through the second passage to an outlet in the trailing edge of the blade. The hollow blade shown has a partition 17 disposed therein so as to define a passage 22 adjacent the internal surface of the convex blade surface 15 and a passage 23 adjacent the internal surface of the concave blade surface 16. The partition is secured at its trailing edge 20 to the internal surface of the convex blade surface and is formed at its leading edge with cut-away portions 18, the portions 19 between the cutaway portions being curved and secured to the internal surface of the blade. Cooling fluid is supplied through the inlet 21 to the passage 22 and then flows through the openings 18 in a direction transverse to the length of the blade to the passage 23. The fluid flows across the passage 23 in the same direction and discharges through outlets 24 formed along the trailing edge of the blade. The partition 17 may be increased in thickness so that the width of the passage 23 is reduced so as to provide a greater velocity in the coolant fluid in this passage.
GB15147/56A 1956-05-15 1956-05-15 Cooled hollow turbine blades Expired GB834811A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB342413X 1956-05-15

Publications (1)

Publication Number Publication Date
GB834811A true GB834811A (en) 1960-05-11

Family

ID=10363183

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15147/56A Expired GB834811A (en) 1956-05-15 1956-05-15 Cooled hollow turbine blades

Country Status (6)

Country Link
US (1) US2956773A (en)
BE (1) BE557503A (en)
CH (1) CH342413A (en)
DE (1) DE1056427B (en)
FR (1) FR1175169A (en)
GB (1) GB834811A (en)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB895077A (en) * 1959-12-09 1962-05-02 Rolls Royce Blades for fluid flow machines such as axial flow turbines
US3420502A (en) * 1962-09-04 1969-01-07 Gen Electric Fluid-cooled airfoil
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3301526A (en) * 1964-12-22 1967-01-31 United Aircraft Corp Stacked-wafer turbine vane or blade
US3844678A (en) * 1967-11-17 1974-10-29 Gen Electric Cooled high strength turbine bucket
US3963368A (en) * 1967-12-19 1976-06-15 General Motors Corporation Turbine cooling
US3529902A (en) * 1968-05-22 1970-09-22 Gen Motors Corp Turbine vane
US4221539A (en) * 1977-04-20 1980-09-09 The Garrett Corporation Laminated airfoil and method for turbomachinery
US4416585A (en) * 1980-01-17 1983-11-22 Pratt & Whitney Aircraft Of Canada Limited Blade cooling for gas turbine engine
US5002460A (en) * 1989-10-02 1991-03-26 General Electric Company Internally cooled airfoil blade
US5704763A (en) * 1990-08-01 1998-01-06 General Electric Company Shear jet cooling passages for internally cooled machine elements
US5165852A (en) * 1990-12-18 1992-11-24 General Electric Company Rotation enhanced rotor blade cooling using a double row of coolant passageways
JP3192854B2 (en) * 1993-12-28 2001-07-30 株式会社東芝 Turbine cooling blade
DE50010300D1 (en) * 2000-11-16 2005-06-16 Siemens Ag Gas turbine blade
US6981840B2 (en) * 2003-10-24 2006-01-03 General Electric Company Converging pin cooled airfoil
US10156143B2 (en) * 2007-12-06 2018-12-18 United Technologies Corporation Gas turbine engines and related systems involving air-cooled vanes
US8535006B2 (en) * 2010-07-14 2013-09-17 Siemens Energy, Inc. Near-wall serpentine cooled turbine airfoil
GB2515464B (en) * 2013-04-24 2021-01-27 Intelligent Energy Ltd A water separator
US10502066B2 (en) 2015-05-08 2019-12-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10344619B2 (en) * 2016-07-08 2019-07-09 United Technologies Corporation Cooling system for a gaspath component of a gas powered turbine
WO2019245546A1 (en) * 2018-06-20 2019-12-26 Siemens Energy, Inc. Cooled turbine blade assembly, corresponding methods for cooling and manufacturing
CN112459849B (en) * 2020-10-27 2022-08-30 哈尔滨广瀚燃气轮机有限公司 Cooling structure for turbine blade of gas turbine

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE710289C (en) * 1938-02-08 1941-09-09 Bbc Brown Boveri & Cie Blade with a device for the formation of a boundary layer protecting against high temperatures and a method for producing this blade
DE853534C (en) * 1943-02-27 1952-10-27 Maschf Augsburg Nuernberg Ag Air-cooled gas turbine blade
DE920641C (en) * 1943-07-15 1954-11-25 Maschf Augsburg Nuernberg Ag Cooled hollow blade, especially for gas turbines
DE852786C (en) * 1943-11-10 1952-10-20 Versuchsanstalt Fuer Luftfahrt Time-graded cooling air throughput through the blades of gas or exhaust gas turbines
US2556736A (en) * 1945-06-22 1951-06-12 Curtiss Wright Corp Deicing system for aircraft
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means
GB680581A (en) * 1949-05-09 1952-10-08 Hermann Oestrich Means for cooling the blades of gas turbine engines
GB685769A (en) * 1949-11-22 1953-01-14 Rolls Royce Improvements relating to compressor and turbine blading

Also Published As

Publication number Publication date
CH342413A (en) 1959-11-15
FR1175169A (en) 1959-03-20
US2956773A (en) 1960-10-18
BE557503A (en)
DE1056427B (en) 1959-04-30

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