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GB712051A - Improvements in or relating to axial-flow fluid machines - Google Patents

Improvements in or relating to axial-flow fluid machines

Info

Publication number
GB712051A
GB712051A GB23637/51A GB2363751A GB712051A GB 712051 A GB712051 A GB 712051A GB 23637/51 A GB23637/51 A GB 23637/51A GB 2363751 A GB2363751 A GB 2363751A GB 712051 A GB712051 A GB 712051A
Authority
GB
United Kingdom
Prior art keywords
vanes
discs
axial
guide vanes
slots
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
GB23637/51A
Inventor
David Omri Davies
John Sutcliffe Jones
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 GB23637/51A priority Critical patent/GB712051A/en
Priority to US313746A priority patent/US2910268A/en
Priority to CH313849D priority patent/CH313849A/en
Priority to FR1068974D priority patent/FR1068974A/en
Publication of GB712051A publication Critical patent/GB712051A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

712,051. Elastic-fluid turbines; axial-flow compressors. ROLLS-ROYCE, Ltd. Oct. 9, 1952 [Oct. 10, 1951], No. 23637/51. Classes 110(1) and 110(3) In axial-flow machines having bladed rotors and stators together with tapping means for drawing off through the rotor drum part of the pressurized fluid flowing in the fluid channel of the machine, the tapping means comprises stator guide vanes 23 which are located radially inwards of the stator blading 11 and are adapted to impart a whirl in the direction of the rotor to the fluid entering the said rotor drum. The guide vanes 23 are brazed to the flanges 20 of the stator blades 11 and to a ring 27. The rotor drum 13 has blade-carrying discs 14 which are splined thereto and separated by a spacer 19 having circumferentially elongated slots 24 for directing the withdrawn fluid into rotor guide vanes 25 carried by the disc 14. The ends of the slots 24 are chamfered so that the walls there-between are inclined. The guide vanes 25 are formed from channel-section strip and are curved so that the flow therebetween is a free vortex whilst the circumferential velocity adjacent the shaft 13 is the same thereas. The vanes 25 are spot welded to discs 28, 29 which have turnedover outer peripheries, the disc 29 being secured to a ring 30 splined to the shaft 13. The vanes 23 make an angle of 80 degrees to the adjacent tangent at their inlet ends and an angle of 48 degrees to the adjacent tangent at their outlet ends and are outwardly concave and inwardly convex. In a modification the convex and concave surfaces of the vanes 23 are outwardly and inwardly facing respectively. In a second modification, the guide vanes 25 are radial to define a forced vortex flow therebetween, the vanes 23 being similar thereto. In a third modification, Fig. 4, the vanes 25 are omitted and the blade-carrying discs are spaced apart by spacer rings 32 through which extend bolts 33, strengthening rings 34 being provided as shown, On a further modification. the axial spacing between a pair of adjacent discs 14 is relatively large compared with the dimension of the slots 24 axially of the machine and the slots 24 are arranged, in the axial sense, substantially symmetrical with respect to the two discs. The ports 22 are also symmetrically disposed with respect to the two discs whereby the central layer of air in the space between the two discs is drawn off with a free vortex motion. Specification 622.181 is referred to.
GB23637/51A 1951-10-10 1951-10-10 Improvements in or relating to axial-flow fluid machines Expired GB712051A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB23637/51A GB712051A (en) 1951-10-10 1951-10-10 Improvements in or relating to axial-flow fluid machines
US313746A US2910268A (en) 1951-10-10 1952-10-08 Axial flow fluid machines
CH313849D CH313849A (en) 1951-10-10 1952-10-09 Axial flow machine
FR1068974D FR1068974A (en) 1951-10-10 1952-10-10 Improvements to axial fluid flow machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB23637/51A GB712051A (en) 1951-10-10 1951-10-10 Improvements in or relating to axial-flow fluid machines

Publications (1)

Publication Number Publication Date
GB712051A true GB712051A (en) 1954-07-14

Family

ID=10198865

Family Applications (1)

Application Number Title Priority Date Filing Date
GB23637/51A Expired GB712051A (en) 1951-10-10 1951-10-10 Improvements in or relating to axial-flow fluid machines

Country Status (4)

Country Link
US (1) US2910268A (en)
CH (1) CH313849A (en)
FR (1) FR1068974A (en)
GB (1) GB712051A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2833220A1 (en) * 1977-08-26 1979-03-01 Snecma DEVICE FOR COOLING GAS TURBINES
EP0049655A1 (en) * 1980-10-08 1982-04-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gas turbine cooling device with air take-off from the compressor
DE3116923A1 (en) * 1980-05-01 1982-04-22 General Electric Co., Schenectady, N.Y. "TURBINE COOLING AIR DEVICE"
US4416111A (en) 1981-02-25 1983-11-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Air modulation apparatus
FR2552164A1 (en) * 1983-09-21 1985-03-22 Snecma COMPRESSOR DISK WITH INTEGRATED CENTRIFUGAL ACCELERATOR FOR AIR SUCTION IN A COOLING DEVICE OF A GAS TURBINE
US4541774A (en) * 1980-05-01 1985-09-17 General Electric Company Turbine cooling air deswirler
US4787820A (en) * 1987-01-14 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbine plant compressor disc with centripetal accelerator for the induction of turbine cooling air
GB2207465A (en) * 1987-07-18 1989-02-01 Rolls Royce Plc A compressor and air bleed arrangement
US5997244A (en) * 1997-05-16 1999-12-07 Alliedsignal Inc. Cooling airflow vortex spoiler
FR2834758A1 (en) * 2002-01-17 2003-07-18 Snecma Moteurs DEVICE FOR STRAIGHTENING THE SUPPLY AIR OF A CENTRIPETE SAMPLING IN A COMPRESSOR

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3085400A (en) * 1959-03-23 1963-04-16 Gen Electric Cooling fluid impeller for elastic fluid turbines
US3034763A (en) * 1959-08-20 1962-05-15 United Aircraft Corp Rotor construction
US3398881A (en) * 1967-01-10 1968-08-27 United Aircraft Corp Compressor bleed device
GB1217807A (en) * 1969-07-19 1970-12-31 Rolls Royce Gas turbine engine
US3609059A (en) * 1969-10-03 1971-09-28 Gen Motors Corp Isothermal wheel
US3647313A (en) * 1970-06-01 1972-03-07 Gen Electric Gas turbine engines with compressor rotor cooling
US3632221A (en) * 1970-08-03 1972-01-04 Gen Electric Gas turbine engine cooling system incorporating a vortex shaft valve
US3897168A (en) * 1974-03-05 1975-07-29 Westinghouse Electric Corp Turbomachine extraction flow guide vanes
US4759688A (en) * 1986-12-16 1988-07-26 Allied-Signal Inc. Cooling flow side entry for cooled turbine blading
DE19617539B4 (en) * 1996-05-02 2006-02-09 Alstom Rotor for a thermal turbomachine
FR2834753B1 (en) * 2002-01-17 2004-09-03 Snecma Moteurs TURBOMACHINE AXIAL COMPRESSOR DISC WITH CENTRIPTED AIR TAKE-OFF
US8047768B2 (en) * 2009-01-12 2011-11-01 General Electric Company Split impeller configuration for synchronizing thermal response between turbine wheels
US8348599B2 (en) * 2010-03-26 2013-01-08 General Electric Company Turbine rotor wheel
US20120003091A1 (en) * 2010-06-30 2012-01-05 Eugenio Yegro Segovia Rotor assembly for use in gas turbine engines and method for assembling the same
US9145772B2 (en) 2012-01-31 2015-09-29 United Technologies Corporation Compressor disk bleed air scallops
US8915057B2 (en) 2012-02-10 2014-12-23 General Electric Company Gas turbine engine sump pressurization system
US9121413B2 (en) * 2012-03-22 2015-09-01 General Electric Company Variable length compressor rotor pumping vanes
US10208668B2 (en) 2015-09-30 2019-02-19 Rolls-Royce Corporation Turbine engine advanced cooling system
US10415465B2 (en) * 2017-12-21 2019-09-17 United Technologies Corporation Axial compressor with inter-stage centrifugal compressor
CN112360761A (en) * 2021-01-12 2021-02-12 中国航发上海商用航空发动机制造有限责任公司 Centripetal pressurization air entraining device and system

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB479427A (en) * 1935-05-31 1938-01-31 Gyoergy Jendrassik Improvements in rotary compressors
US2177159A (en) * 1938-03-11 1939-10-24 Edward A Stalker Pumping machinery
US2294586A (en) * 1941-08-04 1942-09-01 Del Conveyor & Mfg Company Axial flow fan structure
US2419669A (en) * 1942-05-08 1947-04-29 Fed Reserve Bank Diffuser for centrifugal compressors
BE488010A (en) * 1947-03-11 1900-01-01
US2618433A (en) * 1948-06-23 1952-11-18 Curtiss Wright Corp Means for bleeding air from compressors
DE838188C (en) * 1950-08-12 1952-05-05 Köln Dipl.-Ing. Max Adolf Müller Hydrofoil compressor with radial flow from outside to inside

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2833220A1 (en) * 1977-08-26 1979-03-01 Snecma DEVICE FOR COOLING GAS TURBINES
US4231704A (en) 1977-08-26 1980-11-04 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Cooling fluid bleed for axis of turbine rotor
US4541774A (en) * 1980-05-01 1985-09-17 General Electric Company Turbine cooling air deswirler
DE3116923A1 (en) * 1980-05-01 1982-04-22 General Electric Co., Schenectady, N.Y. "TURBINE COOLING AIR DEVICE"
US4415310A (en) 1980-10-08 1983-11-15 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." System for cooling a gas turbine by bleeding air from the compressor
EP0049655A1 (en) * 1980-10-08 1982-04-14 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gas turbine cooling device with air take-off from the compressor
US4416111A (en) 1981-02-25 1983-11-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Air modulation apparatus
FR2552164A1 (en) * 1983-09-21 1985-03-22 Snecma COMPRESSOR DISK WITH INTEGRATED CENTRIFUGAL ACCELERATOR FOR AIR SUCTION IN A COOLING DEVICE OF A GAS TURBINE
EP0140737A1 (en) * 1983-09-21 1985-05-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Compressor disc having an integrated centripetal accelerator for sucking air into the cooling device of a gas turbine
US4595339A (en) * 1983-09-21 1986-06-17 Societe Nationale D'etude Et De Construction De Meteurs D'aviation S.N.E.C.M.A. Centripetal accelerator for air exhaustion in a cooling device of a gas turbine combined with the compressor disc
US4787820A (en) * 1987-01-14 1988-11-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Turbine plant compressor disc with centripetal accelerator for the induction of turbine cooling air
GB2207465A (en) * 1987-07-18 1989-02-01 Rolls Royce Plc A compressor and air bleed arrangement
US4919590A (en) * 1987-07-18 1990-04-24 Rolls-Royce Plc Compressor and air bleed arrangement
GB2207465B (en) * 1987-07-18 1992-02-19 Rolls Royce Plc A compressor and air bleed arrangement
US5997244A (en) * 1997-05-16 1999-12-07 Alliedsignal Inc. Cooling airflow vortex spoiler
FR2834758A1 (en) * 2002-01-17 2003-07-18 Snecma Moteurs DEVICE FOR STRAIGHTENING THE SUPPLY AIR OF A CENTRIPETE SAMPLING IN A COMPRESSOR
EP1329639A1 (en) * 2002-01-17 2003-07-23 Snecma Moteurs Centripetal air bleed device
US6908278B2 (en) 2002-01-17 2005-06-21 Snecma Moteurs Device for straightening the flow of air fed to a centripetal bleed in a compressor

Also Published As

Publication number Publication date
FR1068974A (en) 1954-07-02
CH313849A (en) 1956-05-15
US2910268A (en) 1959-10-27

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