GB1153134A – Axial Flow Compressor
– Google Patents
GB1153134A – Axial Flow Compressor
– Google Patents
Axial Flow Compressor
Info
Publication number
GB1153134A
GB1153134A
GB3233565A
GB3233565A
GB1153134A
GB 1153134 A
GB1153134 A
GB 1153134A
GB 3233565 A
GB3233565 A
GB 3233565A
GB 3233565 A
GB3233565 A
GB 3233565A
GB 1153134 A
GB1153134 A
GB 1153134A
Authority
GB
United Kingdom
Prior art keywords
flow
passage
downstream
velocity
supersonic
Prior art date
1965-07-28
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
GB3233565A
Inventor
Anthony Sydney De Forge-Dedman
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.)
Individual
Original Assignee
Individual
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.)
1965-07-28
Filing date
1965-07-28
Publication date
1969-05-21
1965-07-28
Application filed by Individual
filed
Critical
Individual
1965-07-28
Priority to GB3233565A
priority
Critical
patent/GB1153134A/en
1969-05-21
Publication of GB1153134A
publication
Critical
patent/GB1153134A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
F01D17/00—Regulating or controlling by varying flow
F01D17/10—Final actuators
F01D17/12—Final actuators arranged in stator parts
F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
F04—POSITIVE – DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
F04D—NON-POSITIVE-DISPLACEMENT PUMPS
F04D19/00—Axial-flow pumps
F04D19/02—Multi-stage pumps
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
F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
F04D29/524—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps shiftable members for obturating part of the flow path
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
F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
Abstract
1,153,134. Axial-flow compressors. A.S. DE FORGE-DEDMAN. July 27, 1967 [July 28, 1965], No. 32335/65. Heading F1C. [Also in Division F2] An axial-flow compressor comprises at least one stage having a rotor capable of discharging at supersonic velocity, an annular flow passage downstream of the rotor having a portion which decreases in cross-sectional area in the downstream direction to reduce the supersonic flow to subsonic velocity by way of a single annular shockwave located in the flow passage, and stator vanes located downstream of the location of the shockwave to reduce the subsonic swirl. The rotor blades 300 of each stage of an axial-flow compressor are of impulse design, producing a relative velocity which is supersonic from inlet to outlet of the blades, the absolute velocity at outlet also being supersonic with a Mach number of 1 to 2À5. Downstream of the rotor blades 300 is an annular flow passage which is initially convergent to decelerate the flow to a subsonic velocity at an annular shock-wave 302 which compresses the fluid. Thereafter, the passage is parallel-sided. There may be a sudden enlargement at the transition between these two parts of the passage to accommodate the thickened boundary layer which occurs immediately downstream of the shock-wave. In the case of the final stage, the passage may include a further section of divergent form to reduce the exit velocity. As shown, the axial position of each shock-wave may be adjusted by moving the inner or outer wall 304 of the convergent part of the passage by means of a rack and pinion 305. Stator vanes 307 are also adjustable. Both adjustments may be effected simultaneously by a piston 306 in response to changes in the fuel system pressure, the piston being operated hydraulically, pneumatically or electromagnetically. Holes may be provided in the passage wall to permit boundary layer suction immediately upstream and/or downstream of each shock-wave. Particularly if the compressor is being used by itself without being followed by a conventional axial-flow or centrifugal compressor, it may be necessary to provide one or more blow-off valves which are opened when starting the compressor to accelerate the air to supersonic flow.
GB3233565A
1965-07-28
1965-07-28
Axial Flow Compressor
Expired
GB1153134A
(en)
Priority Applications (1)
Application Number
Priority Date
Filing Date
Title
GB3233565A
GB1153134A
(en)
1965-07-28
1965-07-28
Axial Flow Compressor
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
GB3233565A
GB1153134A
(en)
1965-07-28
1965-07-28
Axial Flow Compressor
Publications (1)
Publication Number
Publication Date
GB1153134A
true
GB1153134A
(en)
1969-05-21
Family
ID=10337006
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB3233565A
Expired
GB1153134A
(en)
1965-07-28
1965-07-28
Axial Flow Compressor
Country Status (1)
Country
Link
GB
(1)
GB1153134A
(en)
Cited By (7)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
EP1746258A3
(en)
*
2005-07-20
2010-04-07
United Technologies Corporation
Rack and pinion variable van synchronizing mechanism for inner diameter vane shroud
US7753647B2
(en)
2005-07-20
2010-07-13
United Technologies Corporation
Lightweight cast inner diameter vane shroud for variable stator vanes
US7901178B2
(en)
2005-07-20
2011-03-08
United Technologies Corporation
Inner diameter vane shroud system having enclosed synchronizing mechanism
WO2013009643A3
(en)
*
2011-07-09
2013-03-28
Ramgen Power Systems, Llc
Supersonic compressor
EP3173581A1
(en)
*
2015-11-24
2017-05-31
MTU Aero Engines GmbH
Method for and compressor of a turbomachine
EP2431577A3
(en)
*
2010-09-16
2017-08-16
Mitsubishi Hitachi Power Systems, Ltd.
Axial flow compressor, gas turbine system having the axial flow compressor and method of modifying the axial flow compressor
CN116379002A
(en)
*
2023-06-05
2023-07-04
中国空气动力研究与发展中心空天技术研究所
Design method of equal-rotation-speed reversing diffuser structure and diffuser structure
1965
1965-07-28
GB
GB3233565A
patent/GB1153134A/en
not_active
Expired
Cited By (10)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
EP1746258A3
(en)
*
2005-07-20
2010-04-07
United Technologies Corporation
Rack and pinion variable van synchronizing mechanism for inner diameter vane shroud
US7753647B2
(en)
2005-07-20
2010-07-13
United Technologies Corporation
Lightweight cast inner diameter vane shroud for variable stator vanes
US7901178B2
(en)
2005-07-20
2011-03-08
United Technologies Corporation
Inner diameter vane shroud system having enclosed synchronizing mechanism
EP2431577A3
(en)
*
2010-09-16
2017-08-16
Mitsubishi Hitachi Power Systems, Ltd.
Axial flow compressor, gas turbine system having the axial flow compressor and method of modifying the axial flow compressor
WO2013009643A3
(en)
*
2011-07-09
2013-03-28
Ramgen Power Systems, Llc
Supersonic compressor
WO2013009644A3
(en)
*
2011-07-09
2013-04-04
Ramgen Power Systems, Llc
Supersonic compressor
EP3173581A1
(en)
*
2015-11-24
2017-05-31
MTU Aero Engines GmbH
Method for and compressor of a turbomachine
US10641288B2
(en)
2015-11-24
2020-05-05
MTU Aero Engines AG
Method for operating a compressor of a turbomachine comprising providing a plurality of stages in a front compressor area, a rear compressor area, and allowing a swirl in the rear compressor area
CN116379002A
(en)
*
2023-06-05
2023-07-04
中国空气动力研究与发展中心空天技术研究所
Design method of equal-rotation-speed reversing diffuser structure and diffuser structure
CN116379002B
(en)
*
2023-06-05
2023-08-11
中国空气动力研究与发展中心空天技术研究所
Design method of equal-rotation-speed reversing diffuser structure and diffuser structure
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Legal Events
Date
Code
Title
Description
1969-12-17
PS
Patent sealed
1976-02-25
PLNP
Patent lapsed through nonpayment of renewal fees
