GB680118A - Improvements in or relating to turbine and like blades - Google Patents

Improvements in or relating to turbine and like blades

Info

Publication number
GB680118A
GB680118A GB17900/49A GB1790049A GB680118A GB 680118 A GB680118 A GB 680118A GB 17900/49 A GB17900/49 A GB 17900/49A GB 1790049 A GB1790049 A GB 1790049A GB 680118 A GB680118 A GB 680118A
Authority
GB
United Kingdom
Prior art keywords
passage
discs
elements
blade
conductance
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
GB17900/49A
Inventor
Austin Geoffrey 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
Publication of GB680118A publication Critical patent/GB680118A/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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Abstract

680,118. Turbine blades. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. June 27, 1950 [July 6, 1949], No. 17900/49. Class 110 (iii) A turbine blade has a longitudinally-extending passage for the flow of coolant fluid and means which are formed separately from the blade are non-uniformly disposed along the passage in good heat-conducting relationship with the wall thereof so as to increase the heat conductance between the wall and the coolant fluid, the conductance varying progressively along the length of the passage. The heat conductance may increase progressively towards the tip end of the blade or the maximum heat conductance may be provided at a point between the root and tip. In Fig. 8 insert elements 12 are mounted on a rod 13 in the coolant passage and the elements which are spaced apart by means of spacers 15 are spaced more closely where the heat stress is greatest. The insert elements may also comprise perforated discs 7 alternating with imperforate discs 8 as in Fig. 2, the imperforate discs being located in the passage by radial arms 9. The elements may also comprise perforated discs or gauze discs located by means of copper brazing, or may be dished so that centrifugal force assists in their attachment. The coolant passages may be rectangular or triangular in shape as well as circular. A design formula is given. Specifications 641,146, 651,787 and 651,830 are referred to.
GB17900/49A 1949-07-06 1949-07-06 Improvements in or relating to turbine and like blades Expired GB680118A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB286626X 1949-07-06

Publications (1)

Publication Number Publication Date
GB680118A true GB680118A (en) 1952-10-01

Family

ID=10279147

Family Applications (2)

Application Number Title Priority Date Filing Date
GB17900/49A Expired GB680118A (en) 1949-07-06 1949-07-06 Improvements in or relating to turbine and like blades
GB14028/52A Expired GB728834A (en) 1949-07-06 1952-06-03 Cooling of turbine blades

Family Applications After (1)

Application Number Title Priority Date Filing Date
GB14028/52A Expired GB728834A (en) 1949-07-06 1952-06-03 Cooling of turbine blades

Country Status (6)

Country Link
US (1) US2843354A (en)
BE (1) BE496812A (en)
CH (1) CH286626A (en)
FR (2) FR1022398A (en)
GB (2) GB680118A (en)
NL (1) NL73916C (en)

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US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
GB778672A (en) * 1954-10-18 1957-07-10 Parsons & Marine Eng Turbine Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades
US2999669A (en) * 1958-11-21 1961-09-12 Westinghouse Electric Corp Damping apparatus
GB895077A (en) * 1959-12-09 1962-05-02 Rolls Royce Blades for fluid flow machines such as axial flow turbines
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
US3370829A (en) * 1965-12-20 1968-02-27 Avco Corp Gas turbine blade construction
FR2098558A5 (en) * 1970-07-20 1972-03-10 Onera (Off Nat Aerospatiale)
US4080095A (en) * 1976-09-02 1978-03-21 Westinghouse Electric Corporation Cooled turbine vane
NL7712519A (en) * 1976-11-19 1978-05-23 Gen Electric LIQUID COOLED TURBINE BLADE WITH IMPROVED HEAT TRANSFER BEHAVIOR.
US4119390A (en) * 1976-11-19 1978-10-10 General Electric Company Liquid-cooled, turbine bucket with enhanced heat transfer performance
US4142831A (en) * 1977-06-15 1979-03-06 General Electric Company Liquid-cooled turbine bucket with enhanced heat transfer performance
US4383854A (en) * 1980-12-29 1983-05-17 General Electric Company Method of creating a controlled interior surface configuration of passages within a substrate
GB2163219B (en) * 1981-10-31 1986-08-13 Rolls Royce Cooled turbine blade
DE3416087A1 (en) * 1984-04-30 1985-10-31 Klöckner-Humboldt-Deutz AG, 5000 Köln COOLED TURBINE BLADE
US5002460A (en) * 1989-10-02 1991-03-26 General Electric Company Internally cooled airfoil blade
US5704763A (en) * 1990-08-01 1998-01-06 General Electric Company Shear jet cooling passages for internally cooled machine elements
US5253976A (en) * 1991-11-19 1993-10-19 General Electric Company Integrated steam and air cooling for combined cycle gas turbines
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
US5486093A (en) * 1993-09-08 1996-01-23 United Technologies Corporation Leading edge cooling of turbine airfoils
FR2765265B1 (en) * 1997-06-26 1999-08-20 Snecma BLADED COOLING BY HELICAL RAMP, CASCADE IMPACT AND BY BRIDGE SYSTEM IN A DOUBLE SKIN
ES2312890T3 (en) * 2004-07-26 2009-03-01 Siemens Aktiengesellschaft COOLED ELEMENT OF A TURBOMACHINE AND MOLDING PROCEDURE OF THIS COOLED ELEMENT.
US7163373B2 (en) * 2005-02-02 2007-01-16 Siemens Power Generation, Inc. Vortex dissipation device for a cooling system within a turbine blade of a turbine engine
US8297927B1 (en) * 2008-03-04 2012-10-30 Florida Turbine Technologies, Inc. Near wall multiple impingement serpentine flow cooled airfoil
EP2372087A1 (en) * 2010-03-26 2011-10-05 Siemens Aktiengesellschaft Components with an external wall which can be exposed to a hot gas of a gas turbine and method for producing such a component
DE102012017491A1 (en) 2012-09-04 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Turbine blade of a gas turbine with swirl-generating element
GB2518379A (en) * 2013-09-19 2015-03-25 Rolls Royce Deutschland Aerofoil cooling system and method
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane
US9932835B2 (en) * 2014-05-23 2018-04-03 United Technologies Corporation Airfoil cooling device and method of manufacture
WO2016014056A1 (en) * 2014-07-24 2016-01-28 Siemens Aktiengesellschaft Turbine airfoil cooling system with spanwise extending flow blockers
WO2017082868A1 (en) * 2015-11-10 2017-05-18 Siemens Aktiengesellschaft Laminated airfoil for a gas turbine
PL232314B1 (en) * 2016-05-06 2019-06-28 Gen Electric Fluid-flow machine equipped with the clearance adjustment system
US10309246B2 (en) 2016-06-07 2019-06-04 General Electric Company Passive clearance control system for gas turbomachine
US10605093B2 (en) 2016-07-12 2020-03-31 General Electric Company Heat transfer device and related turbine airfoil
US10392944B2 (en) 2016-07-12 2019-08-27 General Electric Company Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium
US10738622B2 (en) 2016-08-09 2020-08-11 General Electric Company Components having outer wall recesses for impingement cooling
US11149550B2 (en) * 2019-02-07 2021-10-19 Raytheon Technologies Corporation Blade neck transition
US10871074B2 (en) 2019-02-28 2020-12-22 Raytheon Technologies Corporation Blade/vane cooling passages
CN112483191B (en) * 2020-11-30 2022-07-19 日照黎阳工业装备有限公司 Turbine blade suitable for gas turbine possesses heat convection function

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US970349A (en) * 1910-02-25 1910-09-13 Theodore B Stubbs Crude-oil burner.
US1864742A (en) * 1923-06-15 1932-06-28 Charles N Koch Combustion turbine and method of burning fuel
US1928504A (en) * 1932-01-09 1933-09-26 Holzwarth Gas Turbine Co Cooled nozzle segment for combustion gas turbines
US2043644A (en) * 1933-09-21 1936-06-09 Cyril C Young Heat transfer apparatus
GB426885A (en) * 1933-11-03 1935-04-11 Dewandre Co Ltd C Improvements in or relating to heat transmitting tubes
CH213483A (en) * 1938-11-23 1941-02-15 Porsche Kg Impeller for internal combustion or steam turbines and process for producing the same.
US2297446A (en) * 1938-12-03 1942-09-29 Zellbeck Gustav Hollow blade for exhaust gas turbine rotors
US2407531A (en) * 1942-05-02 1946-09-10 Fed Reserve Bank Elastic fluid mechanism
US2520373A (en) * 1945-01-24 1950-08-29 Lockheed Aircraft Corp Turbine blade and method of making the same
GB625693A (en) * 1946-10-25 1949-07-01 Brush Electrical Eng Improvements in and relating to turbine blades
US2581252A (en) * 1947-12-31 1952-01-01 Sintercast Corp America Powder metallurgy articles
US2665881A (en) * 1948-06-15 1954-01-12 Chrysler Corp Cooled turbine blade
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade

Also Published As

Publication number Publication date
FR66874E (en) 1957-10-31
BE496812A (en) 1900-01-01
FR1022398A (en) 1953-03-04
NL73916C (en) 1900-01-01
CH286626A (en) 1952-10-31
US2843354A (en) 1958-07-15
GB728834A (en) 1955-04-27

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