GB846583A - Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines - Google Patents

Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines

Info

Publication number
GB846583A
GB846583A GB2464857A GB2464857A GB846583A GB 846583 A GB846583 A GB 846583A GB 2464857 A GB2464857 A GB 2464857A GB 2464857 A GB2464857 A GB 2464857A GB 846583 A GB846583 A GB 846583A
Authority
GB
United Kingdom
Prior art keywords
passage
blade
grooves
trailing edge
lengthwise
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
GB2464857A
Inventor
Frederick William Walto Morley
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 GB2464857A priority Critical patent/GB846583A/en
Publication of GB846583A publication Critical patent/GB846583A/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
    • 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
    • F01D5/186—Film 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Landscapes

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

Abstract

846,583. Turbine and compressor blades. ROLLS-ROYCE Ltd. July 22, 1958 [Aug. 2, 1957], No. 24648/57. Class 110 (3). A turbine or compressor rotor blade provided with cooling means, has an internal lengthwise passage 14 which supplies cooling fluid from the root recess 12d to a multiplicity of lengthwise spaced grooves 21 extending chordwise on both surfaces of the blade. Enclosing the leading edge and extending part way towards the trailing edge of the blade is a metal cover plate 23 which directs the cooling fluid, issuing from outlets 20 of passage 14, rearwardly along the grooves to the trailing portions of the blade. The cover plate is secured by brazing to the lands 22 between the grooves, and its side portions 23b are corrugated so as to project slightly into the grooves. A further lengthwise passage 16 may be provided connected to passage 14 by a cross passage 17. Cooling of the trailing edge may be effected by providing additional passage outlets similar to 20 between the passage 16 and the trailing edge of the blade.
GB2464857A 1957-08-02 1957-08-02 Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines Expired GB846583A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2464857A GB846583A (en) 1957-08-02 1957-08-02 Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2464857A GB846583A (en) 1957-08-02 1957-08-02 Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines

Publications (1)

Publication Number Publication Date
GB846583A true GB846583A (en) 1960-08-31

Family

ID=10215042

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2464857A Expired GB846583A (en) 1957-08-02 1957-08-02 Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines

Country Status (1)

Country Link
GB (1) GB846583A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3423069A (en) * 1967-09-29 1969-01-21 Trw Inc Airfoil
FR2533262A1 (en) * 1982-09-16 1984-03-23 Rolls Royce IMPROVEMENTS RELATING TO COOLED AERODYNAMIC GAS TURBOMACHINES
US4753575A (en) * 1987-08-06 1988-06-28 United Technologies Corporation Airfoil with nested cooling channels
US4767268A (en) * 1987-08-06 1988-08-30 United Technologies Corporation Triple pass cooled airfoil
US4859147A (en) * 1988-01-25 1989-08-22 United Technologies Corporation Cooled gas turbine blade
GB2395235A (en) * 2002-11-13 2004-05-19 Ishikawajima Harima Heavy Ind A lightweight cooled turbine blade
CN109779733A (en) * 2017-11-14 2019-05-21 福特环球技术公司 Vehicle radiator component with the coolant path via removable blade

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3423069A (en) * 1967-09-29 1969-01-21 Trw Inc Airfoil
FR2533262A1 (en) * 1982-09-16 1984-03-23 Rolls Royce IMPROVEMENTS RELATING TO COOLED AERODYNAMIC GAS TURBOMACHINES
GB2127105A (en) * 1982-09-16 1984-04-04 Rolls Royce Improvements in cooled gas turbine engine aerofoils
US4753575A (en) * 1987-08-06 1988-06-28 United Technologies Corporation Airfoil with nested cooling channels
US4767268A (en) * 1987-08-06 1988-08-30 United Technologies Corporation Triple pass cooled airfoil
WO1989001564A1 (en) * 1987-08-06 1989-02-23 United Technologies Corporation Airfoil with nested cooling channels
US4859147A (en) * 1988-01-25 1989-08-22 United Technologies Corporation Cooled gas turbine blade
GB2395235A (en) * 2002-11-13 2004-05-19 Ishikawajima Harima Heavy Ind A lightweight cooled turbine blade
US6926499B2 (en) 2002-11-13 2005-08-09 Ishikawajima-Harima Heavy Industries Co., Ltd. Thin-walled, lightweight cooled turbine blade
GB2395235B (en) * 2002-11-13 2006-03-29 Ishikawajima Harima Heavy Ind Thin-walled,lightweight cooled turbine blade
CN109779733A (en) * 2017-11-14 2019-05-21 福特环球技术公司 Vehicle radiator component with the coolant path via removable blade

Similar Documents

Publication Publication Date Title
GB1357713A (en) Cooled rotor blades for gas turbines
GB1359983A (en) Cooled guide blades for gas turbines
SE8008320L (en) FLEXTROTOR SHEET OF TURBO FLOW ENGINES
GB1491556A (en) Rotor blades for turbomachines
GB1186240A (en) Improvements in Blades for Fluid Flow Machines.
GB1408491A (en) Composite turbomachinery blade root configuration
GB1366924A (en) Compressor blades
GB742477A (en) Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors
GB751128A (en) Improvements in turbine or compressor blades
GB1350424A (en) Cooled blade for a gas turbine engine
GB855058A (en) Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines
GB846583A (en) Improvements in or relating to rotor blading of fluid machines, for example, of compressors and turbines of gas turbine engines
GB1432994A (en) Compressor for gas turbine engines
GB1513338A (en) Rotor blade for a gas turbine engine
GB723394A (en) Improvements in turbine blades
GB1419381A (en) Fan for gas turbine engines
GB1119479A (en) Improvements in multi-stage axial flow compressors
GB1151937A (en) Bladed Rotors for Fluid Flow Machines
GB1033759A (en) Aerofoil-shaped blade
GB1078116A (en) Stator blades for combustion turbines
GB710938A (en) Improvements in or relating to rotor blades for axial-flow fluid machines
GB1450133A (en) Cooling of gas turbine engines
GB833770A (en) Hollow turbine or compressor blades
GB854812A (en) Gas turbine blade
GB904546A (en) Improvements in or relating to rotor blades of turbines and compressors