GB778672A - Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades - Google Patents

Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades

Info

Publication number
GB778672A
GB778672A GB29956/54A GB2995654A GB778672A GB 778672 A GB778672 A GB 778672A GB 29956/54 A GB29956/54 A GB 29956/54A GB 2995654 A GB2995654 A GB 2995654A GB 778672 A GB778672 A GB 778672A
Authority
GB
United Kingdom
Prior art keywords
cooling
blade
porous material
channels
gas stream
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
GB29956/54A
Inventor
Ernest John Cole
Vincent Walker
Jack Donald Wells
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.)
Parsons and Marine Engineering Turbine Research and Development Association
Original Assignee
Parsons and Marine Engineering Turbine Research and Development Association
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 Parsons and Marine Engineering Turbine Research and Development Association filed Critical Parsons and Marine Engineering Turbine Research and Development Association
Publication of GB778672A publication Critical patent/GB778672A/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
    • F01D5/183—Blade walls being porous
    • 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

Landscapes

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

Abstract

778,672. Turbine blades. PARSONS & MARINE ENGINEERING TURBINE RESEARCH & DEVELOPMENT ASSOCIATION. Aug. 11, 1955 [Oct. 18, 1954], No. 29956/54. Class 110 (3). A turbine blade (or other member) subject to exposure to a hot gas stream is provided with means including an external covering of porous material for cooling it by effusion, and also means including separate internal cooling passages for cooling it internally. The blade shown in Fig. 1 comprises a spine member a which is formed with the leading and trailing edges band c of the blade, coolant passages d and e being provided in the edge portions. The surfaces of the blade between the leading and trailing edges are provided by sheets of porous material f which afford with the spine member a, channels g through which cooling medium such as air is supplied. The spine member may be formed by extrusion and the porous material sheets may be secured thereto by sintering or electric welding. The air supplied to the channels g may be metered by means of orifices n, and the thickness or permeability of the porous material may be varied. In the blade shown in Fig. 5 cooling air passed upwardly through the passages d and e is caused to flow through openings i, h and j, k into the channels g by means of the shroud m.
GB29956/54A 1954-10-18 1954-10-18 Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades Expired GB778672A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB338057X 1954-10-18
GB110855X 1955-08-11

Publications (1)

Publication Number Publication Date
GB778672A true GB778672A (en) 1957-07-10

Family

ID=26248037

Family Applications (1)

Application Number Title Priority Date Filing Date
GB29956/54A Expired GB778672A (en) 1954-10-18 1954-10-18 Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades

Country Status (4)

Country Link
CH (1) CH338057A (en)
DE (1) DE1031056B (en)
FR (1) FR1130996A (en)
GB (1) GB778672A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3045964A (en) * 1957-02-14 1962-07-24 Stalker Corp Bladed wheels for compressors, turbines and the like
US4629397A (en) * 1983-07-28 1986-12-16 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Structural component for use under high thermal load conditions
EP0995880A3 (en) * 1998-10-19 2002-01-23 Alstom Turbine blade
EP2067929A2 (en) * 2007-12-06 2009-06-10 United Technologies Corporation Air-cooled gas turbine engine vane
US8052389B2 (en) 2004-08-25 2011-11-08 Rolls-Royce Plc Internally cooled airfoils with load carrying members
EP2263938A3 (en) * 2009-06-15 2014-03-26 Deutsches Zentrum für Luft- und Raumfahrt e.V. Cooling device for effusion or transpiration cooling
CN104100380A (en) * 2014-07-02 2014-10-15 北京航空航天大学 Heat exchange method of mainstream gas of aero-engine
CN104110275A (en) * 2014-07-02 2014-10-22 北京航空航天大学 Advanced turbine cooling method based on porous media and super-critical state fluid circulation
WO2018034791A1 (en) * 2016-08-16 2018-02-22 General Electric Company Engine component with porous section

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1097212B (en) * 1956-10-22 1961-01-12 Her Majesty The Queen In The R Blade provided with cooling ducts, especially for gas turbines
GB855058A (en) * 1957-02-22 1960-11-30 Rolls Royce 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
DE1136162B (en) * 1959-05-02 1962-09-06 Wiggin & Co Ltd Henry Gas turbine blade and process for their manufacture
US4501053A (en) * 1982-06-14 1985-02-26 United Technologies Corporation Method of making rotor blade for a rotary machine
US4583914A (en) * 1982-06-14 1986-04-22 United Technologies Corp. Rotor blade for a rotary machine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH225232A (en) * 1941-02-06 1943-01-15 Bmw Flugmotorenbau Gmbh Internally cooled turbine blade.
US2405785A (en) * 1944-03-14 1946-08-13 Daniel And Florence Guggenheim Combustion chamber
GB619634A (en) * 1946-12-17 1949-03-11 Nolan Peter William Moore Improvements relating to internal combustion turbines and like apparatus working with gases at high temperatures
GB680581A (en) * 1949-05-09 1952-10-08 Hermann Oestrich Means for cooling the blades of gas turbine engines
BE496812A (en) * 1949-07-06 1900-01-01

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3045964A (en) * 1957-02-14 1962-07-24 Stalker Corp Bladed wheels for compressors, turbines and the like
US4629397A (en) * 1983-07-28 1986-12-16 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Structural component for use under high thermal load conditions
EP0995880A3 (en) * 1998-10-19 2002-01-23 Alstom Turbine blade
US8052389B2 (en) 2004-08-25 2011-11-08 Rolls-Royce Plc Internally cooled airfoils with load carrying members
US10156143B2 (en) 2007-12-06 2018-12-18 United Technologies Corporation Gas turbine engines and related systems involving air-cooled vanes
EP2067929A2 (en) * 2007-12-06 2009-06-10 United Technologies Corporation Air-cooled gas turbine engine vane
EP2067929A3 (en) * 2007-12-06 2012-03-07 United Technologies Corporation Air-cooled gas turbine engine vane
EP2263938A3 (en) * 2009-06-15 2014-03-26 Deutsches Zentrum für Luft- und Raumfahrt e.V. Cooling device for effusion or transpiration cooling
CN104110275A (en) * 2014-07-02 2014-10-22 北京航空航天大学 Advanced turbine cooling method based on porous media and super-critical state fluid circulation
CN104110275B (en) * 2014-07-02 2016-01-13 北京航空航天大学 A kind of advanced turbine cooling method circulated based on porous medium and supercritical state fluid
CN104100380B (en) * 2014-07-02 2016-04-27 北京航空航天大学 A kind of aeroengine mainstream gas heat exchange method
CN104100380A (en) * 2014-07-02 2014-10-15 北京航空航天大学 Heat exchange method of mainstream gas of aero-engine
WO2018034791A1 (en) * 2016-08-16 2018-02-22 General Electric Company Engine component with porous section
US10612389B2 (en) 2016-08-16 2020-04-07 General Electric Company Engine component with porous section

Also Published As

Publication number Publication date
DE1031056B (en) 1958-05-29
CH338057A (en) 1959-04-30
FR1130996A (en) 1957-02-14

Similar Documents

Publication Publication Date Title
GB778672A (en) Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades
GB1271819A (en) Improvements in film cooling of structural members in gas turbine engines
GB1356355A (en) Transpiration cooled turbine blade with metered coolant flow
GB1177410A (en) Improvements in Gas Turbine Engine Turbine Rotor Shrouds
GB1515499A (en) Transient air temperature sensing systems
GB1101543A (en) Improvements in turbine diaphragm structure
GB1438229A (en) Porous sheet adapted to be cooled by fluid flow
GB989217A (en) Turbine blades
GB1361256A (en) Gas turbine engine blades
GB793886A (en) Improvements in or relating to sealing means between relatively movable parts
GB2053367A (en) Cooled shroud for a gas turbine engine
FR2448136A1 (en) INSTRUMENT PROBE PLACED ADJACENT TO A BLADE OF TURBOMACHINE
GB1295370A (en)
GB1257746A (en)
GB582152A (en) Improvements in or relating to turbine apparatus
GB1282250A (en) Laminated high temperature resistant materials
GB1151177A (en) Improvements in and relating to Gas Turbine Engines
GB1285369A (en) Improvements in or relating to blades for fluid flow machines
US2991973A (en) Cooling of bodies subject to a hot gas stream
GB834811A (en) Cooled hollow turbine blades
GB1218371A (en) Improvements in or relating to aerofoil vanes or blades for high temperature use
GB660007A (en) Improvements relating to turbine rotor blades
GB731292A (en) Improvements in processes of making turbine and compressor blades
GB1404757A (en) Gas turbine engine blades
GB1097300A (en) Improvements in gas turbine blades