GB1276200A - Improvements in or relating to blades for fluid flow machines - Google Patents

Improvements in or relating to blades for fluid flow machines

Info

Publication number
GB1276200A
GB1276200A GB58758/69A GB5875869A GB1276200A GB 1276200 A GB1276200 A GB 1276200A GB 58758/69 A GB58758/69 A GB 58758/69A GB 5875869 A GB5875869 A GB 5875869A GB 1276200 A GB1276200 A GB 1276200A
Authority
GB
United Kingdom
Prior art keywords
aero
apertures
foil portion
platform
shroud
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
GB58758/69A
Inventor
Douglas Herbert Williamson
Thomas Steel
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB58758/69A priority Critical patent/GB1276200A/en
Publication of GB1276200A publication Critical patent/GB1276200A/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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Landscapes

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

Abstract

1276200 Turbine blades ROLLS ROYCE Ltd 2 Dec 1969 58758/69 Heading FIT A gas turbine rotor blade has a hollow aero-foil portion to the tip of which is attached a hollow shroud having apertures 26, 30 for the flow of cooling air from the interior of the aero-foil portion, through the shroud and thence into the gas stream. The aero-foil portion is made of three layers of sheet metal 12a, b, c bonded together, the intermediate layer 12b having a pattern of channels and apertures so that cooling air flowing through apertures in the inner layer 12a can flow to the blade exterior through these channels and further apertures in the outer layer 12c. In the arrangement shown the shroud includes a cover member 20, a tapered core shaped to fit in the flared tip of the aero-foil portion and a platform which may be split into two or more parts to fit around the outside of the aero-foil, all the parts being brazed together. In a modification, Fig. 3 (not shown) the core and platform are formed integrally. The platform may include strengthening ribs.
GB58758/69A 1969-12-02 1969-12-02 Improvements in or relating to blades for fluid flow machines Expired GB1276200A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB58758/69A GB1276200A (en) 1969-12-02 1969-12-02 Improvements in or relating to blades for fluid flow machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB58758/69A GB1276200A (en) 1969-12-02 1969-12-02 Improvements in or relating to blades for fluid flow machines

Publications (1)

Publication Number Publication Date
GB1276200A true GB1276200A (en) 1972-06-01

Family

ID=10482357

Family Applications (1)

Application Number Title Priority Date Filing Date
GB58758/69A Expired GB1276200A (en) 1969-12-02 1969-12-02 Improvements in or relating to blades for fluid flow machines

Country Status (1)

Country Link
GB (1) GB1276200A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4127358A (en) * 1976-04-08 1978-11-28 Rolls-Royce Limited Blade or vane for a gas turbine engine
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
US4218178A (en) * 1978-03-31 1980-08-19 General Motors Corporation Turbine vane structure
US4411597A (en) * 1981-03-20 1983-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Tip cap for a rotor blade
US4487550A (en) * 1983-01-27 1984-12-11 The United States Of America As Represented By The Secretary Of The Air Force Cooled turbine blade tip closure
US4948338A (en) * 1988-09-30 1990-08-14 Rolls-Royce Plc Turbine blade with cooled shroud abutment surface
EP0935052A3 (en) * 1998-02-04 2000-03-29 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor blade
EP1267037A2 (en) * 2001-04-16 2002-12-18 United Technologies Corporation Cooled hollow tip shroud of a turbine blade
EP1734227A1 (en) * 2005-06-13 2006-12-20 General Electric Company V-shaped blade tip shroud and method of fabricating same
JP2010031865A (en) * 2008-07-29 2010-02-12 General Electric Co <Ge> Rotor blade and method of fabricating the same

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4127358A (en) * 1976-04-08 1978-11-28 Rolls-Royce Limited Blade or vane for a gas turbine engine
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
US4218178A (en) * 1978-03-31 1980-08-19 General Motors Corporation Turbine vane structure
US4411597A (en) * 1981-03-20 1983-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Tip cap for a rotor blade
US4487550A (en) * 1983-01-27 1984-12-11 The United States Of America As Represented By The Secretary Of The Air Force Cooled turbine blade tip closure
US4948338A (en) * 1988-09-30 1990-08-14 Rolls-Royce Plc Turbine blade with cooled shroud abutment surface
EP0935052A3 (en) * 1998-02-04 2000-03-29 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor blade
US6152695A (en) * 1998-02-04 2000-11-28 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade
EP1267037A2 (en) * 2001-04-16 2002-12-18 United Technologies Corporation Cooled hollow tip shroud of a turbine blade
EP1267037A3 (en) * 2001-04-16 2004-02-04 United Technologies Corporation Cooled hollow tip shroud of a turbine blade
EP1734227A1 (en) * 2005-06-13 2006-12-20 General Electric Company V-shaped blade tip shroud and method of fabricating same
JP2010031865A (en) * 2008-07-29 2010-02-12 General Electric Co <Ge> Rotor blade and method of fabricating the same

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees