GB1071865A - Axial-flow compressors - Google Patents

Axial-flow compressors

Info

Publication number
GB1071865A
GB1071865A GB3663/66A GB366366A GB1071865A GB 1071865 A GB1071865 A GB 1071865A GB 3663/66 A GB3663/66 A GB 3663/66A GB 366366 A GB366366 A GB 366366A GB 1071865 A GB1071865 A GB 1071865A
Authority
GB
United Kingdom
Prior art keywords
ring
wall
boundary layer
shroud
compressor
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
GB3663/66A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation Co
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
Priority to US434835A priority Critical patent/US3300121A/en
Application filed by Motors Liquidation Co filed Critical Motors Liquidation Co
Publication of GB1071865A publication Critical patent/GB1071865A/en
Application status is Expired legal-status Critical

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/52Casings; Connections of working fluid for axial pumps
    • F04D29/522Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00Pumping installations or systems
    • F04D25/16Combinations of two or more pumps Producing two or more separate gas flows
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/52Casings; Connections of working fluid for axial pumps
    • F04D29/54Fluid-guiding means, e.g. diffusers
    • F04D29/541Specially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/66Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection

Abstract

1,071,865. Boundary layer control. GENERAL MOTORS CORPORATION. Jan. 27, 1966 [Feb. 24, 1965], No. 3663/66. Heading F2R. An axial flow compressor, wherein the last three stages of compressor blading are shown at 17, 18, 19, discharges into an annular diffuser bounded by walls 2 and 25, the wall 25 diverging sharply from an inner shroud 33. The blading stages are bolted to the flange 21 of shaft 13 and a ring 29, also bolted to flange 21, forms an annular passage 38 within which are housed a ring of stator blades 39 attached to shroud 33 and a ring of rotor blades 41 attached to ring 29. Shroud 33 is spaced at 37 and 43 from blade row 19 and curved transition 30 of wall 25, respectively whereby, in operation, auxiliary compressor 41 draws air through passage 38 to deliver it over transition 30 and cause the boundary layer to adhere to wall 25. The apparatus may be used to cause the boundary layer to adhere to wall 2.
GB3663/66A 1965-02-24 1966-01-27 Axial-flow compressors Expired GB1071865A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US434835A US3300121A (en) 1965-02-24 1965-02-24 Axial-flow compressor

Publications (1)

Publication Number Publication Date
GB1071865A true GB1071865A (en) 1967-06-14

Family

ID=23725894

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3663/66A Expired GB1071865A (en) 1965-02-24 1966-01-27 Axial-flow compressors

Country Status (2)

Country Link
US (1) US3300121A (en)
GB (1) GB1071865A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3101250A1 (en) * 1981-01-16 1982-08-05 Mtu Muenchen Gmbh Rotor for turbo engines, especially axial flow compressor rotor for gas turbine engines
CN102947598A (en) * 2010-06-17 2013-02-27 斯奈克玛 Compressor and turbomachine with optimized efficiency

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3640638A (en) * 1969-07-02 1972-02-08 Rolls Royce Axial flow compressor
GB1314819A (en) * 1969-07-30 1973-04-26 Secr Defence Fluid flow diffusion ducts of gas turbine engines
US3631675A (en) * 1969-09-11 1972-01-04 Gen Electric Combustor primary air control
US3690786A (en) * 1971-05-10 1972-09-12 Westinghouse Electric Corp Low pressure end diffuser for axial flow elastic fluid turbines
US20060198726A1 (en) * 2005-03-07 2006-09-07 General Electric Company Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting
US8282336B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system
US8348592B2 (en) * 2007-12-28 2013-01-08 General Electric Company Instability mitigation system using rotor plasma actuators
US8282337B2 (en) * 2007-12-28 2012-10-09 General Electric Company Instability mitigation system using stator plasma actuators
US8317457B2 (en) * 2007-12-28 2012-11-27 General Electric Company Method of operating a compressor
US20090169363A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Stator
US20100284785A1 (en) * 2007-12-28 2010-11-11 Aspi Rustom Wadia Fan Stall Detection System
US20100290906A1 (en) * 2007-12-28 2010-11-18 Moeckel Curtis W Plasma sensor stall control system and turbomachinery diagnostics
US20090169356A1 (en) * 2007-12-28 2009-07-02 Aspi Rustom Wadia Plasma Enhanced Compression System
US20100205928A1 (en) * 2007-12-28 2010-08-19 Moeckel Curtis W Rotor stall sensor system
US20100047055A1 (en) * 2007-12-28 2010-02-25 Aspi Rustom Wadia Plasma Enhanced Rotor
US8313286B2 (en) * 2008-07-28 2012-11-20 Siemens Energy, Inc. Diffuser apparatus in a turbomachine
US20100172747A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced compressor duct
US20100170224A1 (en) * 2009-01-08 2010-07-08 General Electric Company Plasma enhanced booster and method of operation

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2555576A (en) * 1946-05-07 1951-06-05 Buffalo Forge Co Axial flow fan
US2798661A (en) * 1954-03-05 1957-07-09 Westinghouse Electric Corp Gas turbine power plant apparatus

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3101250A1 (en) * 1981-01-16 1982-08-05 Mtu Muenchen Gmbh Rotor for turbo engines, especially axial flow compressor rotor for gas turbine engines
CN102947598A (en) * 2010-06-17 2013-02-27 斯奈克玛 Compressor and turbomachine with optimized efficiency
CN102947598B (en) * 2010-06-17 2016-05-04 斯奈克玛 Compressor and the turbogenerator with optimum efficiency
US9488179B2 (en) 2010-06-17 2016-11-08 Snecma Compressor and a turbine engine with optimized efficiency

Also Published As

Publication number Publication date
US3300121A (en) 1967-01-24

Similar Documents

Publication Publication Date Title
US3363419A (en) Gas turbine ducted fan engine
US3680309A (en) Two-spool auxiliary power unit and control means
Eck Fans
US2640319A (en) Cooling of gas turbines
EP1252424B1 (en) Method of operating a variable cycle gas turbine engine
US4236869A (en) Gas turbine engine having bleed apparatus with dynamic pressure recovery
US4968216A (en) Two-stage fluid driven turbine
US4981018A (en) Compressor shroud air bleed passages
GB1204734A (en) Improvements in and relating to a single shaft fan compressor and turbine assembly
US3663118A (en) Turbine cooling control
GB1060926A (en) Fan motor cooling arrangement
US3692425A (en) Compressor for handling gases at velocities exceeding a sonic value
US3611724A (en) Choked inlet noise suppression device for a turbofan engine
US3771925A (en) Supersonic centrifugal compressor
US3494129A (en) Fluid compressors and turbofan engines employing same
GB1144036A (en) A vane for an aerial flow turbomachine
US3182898A (en) Axial flow compressor or fan and gas turbine engine provided therewith
US3556680A (en) Aerodynamic pressure-wave machine
GB1137087A (en) Improvements in or relating to driving radial-flow compressors
FR2181407A5 (en)
GB1199974A (en) Turbine Blade Seal Assembly
GB1266585A (en)
FR1211950A (en) Turbo-machine
GB996041A (en) Improvements in compressor or turbine blading
US4711084A (en) Ejector assisted compressor bleed