GB783710A - Improvements in turbine blades and in the cooling thereof - Google Patents

Improvements in turbine blades and in the cooling thereof

Info

Publication number
GB783710A
GB783710A GB3423554A GB3423554A GB783710A GB 783710 A GB783710 A GB 783710A GB 3423554 A GB3423554 A GB 3423554A GB 3423554 A GB3423554 A GB 3423554A GB 783710 A GB783710 A GB 783710A
Authority
GB
United Kingdom
Prior art keywords
outer skin
core
intermediate layer
skin
fluid
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
GB3423554A
Inventor
Cyril Gordon Conway
Michael Charles George 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 GB3423554A priority Critical patent/GB783710A/en
Publication of GB783710A publication Critical patent/GB783710A/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
    • F01D5/182—Transpiration cooling

Landscapes

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

Abstract

783,710. Turbine blades. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Nov. 17, 1955 [Nov. 25, 1954], No. 34235/54. Class 110(3). A turbine blade comprises an inner longitudinal core 1, a fluid-permeable outer skin 2 around the core and spaced therefrom to permit the flow of coolant fluid, a fluid-permeable intermediate layer 3 filling the space and being bonded to the outer skin and the core, the permeability of the intermediate layer being high compared with that of the outer skin. The outer skin and the intermediate layer may be of sintered material and the particle size of the intermediate layer is large compared with the outer skin. The core, the intermediate layer and the outer skin may all be of metal, or the core may be of metal, the intermediate layer of cermet and the outer skin of cermet or ceramic. The thickness and the permeability of the outer skin may be varied around the periphery of the blade, the skin thickness being least at the regions of highest stress, greatest external heat transfer and highest external pressure. As shown, the skin is thinnest at the leading edge, on the concave surface and on the convex surface towards the trailing edge. The core is formed at its tip end with an enlargement 1a with which the tip ends of the outer skin and the intermediate layer engage. In a turbine blade of a gas turbine engine, the coolant fluid may be air tapped from the engine compressor. The core 1 may be of sintered material or it may be formed by forging. Specification 619,634 is referred to.
GB3423554A 1954-11-25 1954-11-25 Improvements in turbine blades and in the cooling thereof Expired GB783710A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3423554A GB783710A (en) 1954-11-25 1954-11-25 Improvements in turbine blades and in the cooling thereof

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3423554A GB783710A (en) 1954-11-25 1954-11-25 Improvements in turbine blades and in the cooling thereof

Publications (1)

Publication Number Publication Date
GB783710A true GB783710A (en) 1957-09-25

Family

ID=10363107

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3423554A Expired GB783710A (en) 1954-11-25 1954-11-25 Improvements in turbine blades and in the cooling thereof

Country Status (1)

Country Link
GB (1) GB783710A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2945531C2 (en) * 1979-11-10 1982-01-07 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbo blade with a material core and a ceramic blade
US4629397A (en) * 1983-07-28 1986-12-16 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Structural component for use under high thermal load conditions

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2945531C2 (en) * 1979-11-10 1982-01-07 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbo blade with a material core and a ceramic blade
US4629397A (en) * 1983-07-28 1986-12-16 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Structural component for use under high thermal load conditions

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