GB1299686A - A supersonic axial-flow compressor - Google Patents

A supersonic axial-flow compressor

Info

Publication number
GB1299686A
GB1299686A GB25077/71A GB2507771A GB1299686A GB 1299686 A GB1299686 A GB 1299686A GB 25077/71 A GB25077/71 A GB 25077/71A GB 2507771 A GB2507771 A GB 2507771A GB 1299686 A GB1299686 A GB 1299686A
Authority
GB
United Kingdom
Prior art keywords
rotor
blading
fixed
fluid
flow
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
GB25077/71A
Inventor
Jean-Marie Friberg
Pierre Maginot
Jean-Marie Merigoux
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.)
Alcatel CIT SA
Original Assignee
Alcatel CIT SA
Compagnie Industrielle de Telecommunication CIT Alcatel SA
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 Alcatel CIT SA, Compagnie Industrielle de Telecommunication CIT Alcatel SA filed Critical Alcatel CIT SA
Publication of GB1299686A publication Critical patent/GB1299686A/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
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Percussion Or Vibration Massage (AREA)

Abstract

1299686 Axial-flow compressors COMPAGNIE INDUSTRIELLE DES TELECOMMUNICATIONS CIT-ALCATEL 19 April 1971 [23 March 1970] 25077/71 Heading F1C A supersonic axial-flow compressor has a rotor 5 and downstream fixed blading 10,11. The rotor blades 8 and fixed blading 10, 11 extend across an annular fluid-flow passage. The angles of incidence of the rotor blades and fixed blades are small, the cross-sectional area of the fluid paths between the rotor blades are non divergent and between the fixed blades 10 are non-convergent, and the leading edges of the rotor and fixed blading are rounded and have a small radius of curvature, e.g. 0À5% of the blade chord. The paths between the rotor blading and fixed blading may be short and convergent and short and divergent respectively to produce respective shock waves. Alternatively, the paths therebetween may be long and of substantlally constant cross-section to produce gradual flow transformation. The blading may be profiled so that the product of the ratios at the inlet and outlet ends of the relative fluid speed to the critical speed of sound, is substantially unity, e.g. relative speed ratio at rotor inlet may be Mach 1À35 and at rotor outlet may be Mach 0À75. The compressor may have a number of stages, the fluid leaving one stage being mixed with a secondary fluid flow re-cycled through a tangential inlet aperture.
GB25077/71A 1970-03-23 1971-04-19 A supersonic axial-flow compressor Expired GB1299686A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7010383A FR2083742A5 (en) 1970-03-23 1970-03-23

Publications (1)

Publication Number Publication Date
GB1299686A true GB1299686A (en) 1972-12-13

Family

ID=9052734

Family Applications (1)

Application Number Title Priority Date Filing Date
GB25077/71A Expired GB1299686A (en) 1970-03-23 1971-04-19 A supersonic axial-flow compressor

Country Status (6)

Country Link
US (1) US3724968A (en)
DE (1) DE2113514C3 (en)
FR (1) FR2083742A5 (en)
GB (1) GB1299686A (en)
NO (1) NO138226C (en)
SE (1) SE376276B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2799721A1 (en) * 2013-05-03 2014-11-05 Techspace Aero S.A. Axial turbomachine stator guide with ailerons on the vane feet

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3873229A (en) * 1973-12-26 1975-03-25 United Aircraft Corp Inlet guide vane configuration for noise control of supersonic fan
US4859145A (en) * 1987-10-19 1989-08-22 Sundstrand Corporation Compressor with supercritical diffuser
US5297930A (en) * 1991-12-31 1994-03-29 Cornell Research Foundation, Inc. Rotating stall suppression
US6206635B1 (en) * 1998-12-07 2001-03-27 Valeo, Inc. Fan stator
JP2002213206A (en) * 2001-01-12 2002-07-31 Mitsubishi Heavy Ind Ltd Blade structure of gas turbine
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US7334990B2 (en) * 2002-01-29 2008-02-26 Ramgen Power Systems, Inc. Supersonic compressor
US7434400B2 (en) * 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
US7293955B2 (en) * 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US8864454B2 (en) * 2010-10-28 2014-10-21 General Electric Company System and method of assembling a supersonic compressor system including a supersonic compressor rotor and a compressor assembly
GB2516648B (en) * 2013-07-29 2016-08-31 Charles Wells John Fitting for a gas turbine engine
US20180156236A1 (en) * 2016-12-02 2018-06-07 Pratt & Whitney Canada Corp. Gas turbine engine bleed configuration
BE1026455B1 (en) * 2018-07-09 2020-02-03 Safran Aero Boosters Sa TURBOMACHINE COMPRESSOR
IL271106B2 (en) * 2019-12-02 2023-11-01 Bar Zohar Dan Nuclear fusion apparatus and method

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3128939A (en) * 1964-04-14 Szydlowski
IT459043A (en) *
US2435236A (en) * 1943-11-23 1948-02-03 Westinghouse Electric Corp Superacoustic compressor
US2623688A (en) * 1945-12-13 1952-12-30 Power Jets Res & Dev Ltd Rotary power conversion machine
US2628768A (en) * 1946-03-27 1953-02-17 Kantrowitz Arthur Axial-flow compressor
US2721693A (en) * 1949-05-24 1955-10-25 Onera (Off Nat Aerospatiale) Supersonic compressor
US2974927A (en) * 1955-09-27 1961-03-14 Elmer G Johnson Supersonic fluid machine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2799721A1 (en) * 2013-05-03 2014-11-05 Techspace Aero S.A. Axial turbomachine stator guide with ailerons on the vane feet
CN104131845A (en) * 2013-05-03 2014-11-05 航空技术空间股份有限公司 Axial turbomachine stator with ailerons at the blade roots
RU2586426C2 (en) * 2013-05-03 2016-06-10 Текспейс Аеро С.А. Stator of axial turbo machine with ailerons in blade roots
US9739154B2 (en) 2013-05-03 2017-08-22 Safran Aero Boosters Sa Axial turbomachine stator with ailerons at the blade roots

Also Published As

Publication number Publication date
DE2113514C3 (en) 1982-02-25
NO138226B (en) 1978-04-17
US3724968A (en) 1973-04-03
NO138226C (en) 1978-08-02
DE2113514B2 (en) 1981-06-04
FR2083742A5 (en) 1971-12-17
DE2113514A1 (en) 1971-10-14
SE376276B (en) 1975-05-12

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee