GB808837A - Blades and blade assemblies of turbines and compressors - Google Patents

Blades and blade assemblies of turbines and compressors

Info

Publication number
GB808837A
GB808837A GB788055A GB788055A GB808837A GB 808837 A GB808837 A GB 808837A GB 788055 A GB788055 A GB 788055A GB 788055 A GB788055 A GB 788055A GB 808837 A GB808837 A GB 808837A
Authority
GB
United Kingdom
Prior art keywords
blade
passages
cross
root portion
passage
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
GB788055A
Inventor
Frank Bernard Halford
David Mark Cockburn
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.)
Bristol Siddeley Engines Ltd
Original Assignee
De Havilland Engine Co 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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to GB788055A priority Critical patent/GB808837A/en
Priority to FR1143952D priority patent/FR1143952A/en
Publication of GB808837A publication Critical patent/GB808837A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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

Abstract

808,837. Turbine and compressor blades. DE HAVILLAND ENGINE CO. Ltd. March 14, 1956 [March 17, 1955], No. 7880/55. Class 110(3). A blade for a turbine or compressor comprises an aerofoil portion B<SP>3</SP>, a root portion B<SP>1</SP> formed for engagement with a slot A<SP>1</SP> in a supporting member such as a rotor disc A, and at least one substantially straight passage for cooling or heating fluid extending through the root portion into the aerofoil portion. In a first embodiment, the blade is formed with a plurality of straight passages B<SP>2</SP> which when viewed in cross-section in planes normal to the length of the blade are distributed along the curved centre lines of the cross-sections of the blade in these planes. In Fig. 5 the blade is formed with a single straight passage E, this passage extending along the centre lines of the transverse cross-sections of the blade. The aerofoil portion B<SP>3</SP> of the blade is twisted about a longitudinal axis so that the passages B<SP>2</SP> or passage E at the root end of the aerofoil portion lie or lies on a curve different from that at any other cross-section of the aerofoil portion. The root portion B<SP>1</SP> or D<SP>1</SP> in the case of Fig. 5, is curved in cross-sections transverse to the length of the blade, the concave side of the curve being on the same side as the concavity of the aerofoil portion and the root portion is of such a width that although the passages B<SP>2</SP> or passage E do not or does not break out through its sides, a part of the aerofoil portion B<SP>3</SP> or D<SP>3</SP> when projected into the plane of the top of the root portion extends beyond the limits of the root portion B<SP>1</SP> or D<SP>1</SP> in this plane. The blade may be either from a single piece of material or from two or more pieces, for example from two pieces the contact surface of which passes through the cooling passages of the blade. The root portion of the blade may taper when viewed in cross-sectional planes transverse to the length of the blade. Passages A<SP>3</SP> in Fig. 2 and F<SP>2</SP> in Fig. 5 are provided in the rotor disc at the bottom of the blade-mounting slot for the supply of cooling or heating fluid. Alternatively two passages may be provided one for the supply and one for the discharge of the fluid.
GB788055A 1955-03-17 1955-03-17 Blades and blade assemblies of turbines and compressors Expired GB808837A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB788055A GB808837A (en) 1955-03-17 1955-03-17 Blades and blade assemblies of turbines and compressors
FR1143952D FR1143952A (en) 1955-03-17 1956-03-16 Blades and blades of compressors or turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB788055A GB808837A (en) 1955-03-17 1955-03-17 Blades and blade assemblies of turbines and compressors

Publications (1)

Publication Number Publication Date
GB808837A true GB808837A (en) 1959-02-11

Family

ID=9841553

Family Applications (1)

Application Number Title Priority Date Filing Date
GB788055A Expired GB808837A (en) 1955-03-17 1955-03-17 Blades and blade assemblies of turbines and compressors

Country Status (2)

Country Link
FR (1) FR1143952A (en)
GB (1) GB808837A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0194883A2 (en) * 1985-03-13 1986-09-17 Westinghouse Electric Corporation Fabricated blade with spanwise cooling passages for gas turbine
EP1234949A2 (en) * 2001-02-26 2002-08-28 United Technologies Corporation Cooling air inlet configuration for a blade root
GB2415018A (en) * 2004-06-03 2005-12-14 Gen Electric Turbine blade with cooling passages
CN102213109A (en) * 2010-04-12 2011-10-12 通用电气公司 Turbine bucket having a radial cooling hole
US20140255187A1 (en) * 2013-03-10 2014-09-11 Rolls-Royce Corporation Attachment feature of a gas turbine engine blade having a curved profile
EP2208859A3 (en) * 2009-01-14 2017-11-08 Kabushiki Kaisha Toshiba Steam turbine and cooling method thereof

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB846277A (en) * 1956-11-20 1960-08-31 Rolls Royce Turbine and compressor blades
US4621979A (en) * 1979-11-30 1986-11-11 United Technologies Corporation Fan rotor blades of turbofan engines
JP4911286B2 (en) * 2006-03-14 2012-04-04 株式会社Ｉｈｉ Fan dovetail structure

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0194883A2 (en) * 1985-03-13 1986-09-17 Westinghouse Electric Corporation Fabricated blade with spanwise cooling passages for gas turbine
EP0194883A3 (en) * 1985-03-13 1989-01-18 Westinghouse Electric Corporation Fabricated blade with spanwise cooling passages for gas turbine
EP1234949A2 (en) * 2001-02-26 2002-08-28 United Technologies Corporation Cooling air inlet configuration for a blade root
EP1234949A3 (en) * 2001-02-26 2004-01-14 United Technologies Corporation Cooling air inlet configuration for a blade root
GB2415018B (en) * 2004-06-03 2009-01-07 Gen Electric Turbine bucket with optimized cooling circuit
US7207775B2 (en) 2004-06-03 2007-04-24 General Electric Company Turbine bucket with optimized cooling circuit
GB2415018A (en) * 2004-06-03 2005-12-14 Gen Electric Turbine blade with cooling passages
EP2208859A3 (en) * 2009-01-14 2017-11-08 Kabushiki Kaisha Toshiba Steam turbine and cooling method thereof
CN102213109A (en) * 2010-04-12 2011-10-12 通用电气公司 Turbine bucket having a radial cooling hole
JP2011220337A (en) * 2010-04-12 2011-11-04 General Electric Co <Ge> Turbine bucket having radial cooling hole
EP2374998A3 (en) * 2010-04-12 2013-07-10 General Electric Company Turbine bucket having a radial cooling hole
US8727724B2 (en) 2010-04-12 2014-05-20 General Electric Company Turbine bucket having a radial cooling hole
US20140255187A1 (en) * 2013-03-10 2014-09-11 Rolls-Royce Corporation Attachment feature of a gas turbine engine blade having a curved profile
US9739158B2 (en) * 2013-03-10 2017-08-22 Rolls-Royce Corporation Attachment feature of a gas turbine engine blade having a curved profile

Also Published As

Publication number Publication date
FR1143952A (en) 1957-10-08

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