GB1357016A - Compressor bleed valves - Google Patents

Compressor bleed valves

Info

Publication number
GB1357016A
GB1357016A GB5124971A GB5124971A GB1357016A GB 1357016 A GB1357016 A GB 1357016A GB 5124971 A GB5124971 A GB 5124971A GB 5124971 A GB5124971 A GB 5124971A GB 1357016 A GB1357016 A GB 1357016A
Authority
GB
United Kingdom
Prior art keywords
compressor
tube
apertures
valve
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
GB5124971A
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 GB5124971A priority Critical patent/GB1357016A/en
Publication of GB1357016A publication Critical patent/GB1357016A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
    • F16K7/00—Diaphragm valves or cut-off apparatus, e.g. with a member deformed, but not moved bodily, to close the passage ; Pinch valves
    • F16K7/18—Diaphragm valves or cut-off apparatus, e.g. with a member deformed, but not moved bodily, to close the passage ; Pinch valves with diaphragm secured at one side only, e.g. to be laid on the seat by rolling action
    • 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
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • 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)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Reciprocating Pumps (AREA)

Abstract

1357016 Axial-flow compressors ROLLSROYCE (1971) Ltd 4 Nov 1971 51249/71 Heading F1C [Also in Division F2] A valve for relieving excess pressure or flow through apertures 16 in the casing 12 of an axialflow compressor, comprises an inflatable tube 15 encircled by a relatively rigid member 24, e.g. of metal, and movable axially of the compressor to uncover the apertures. The tube 15 comprises a pair of elastomeric cylinders joined at their edges by two circular clamps 20, 22 and employing reinforcing wires 18. The member 24 and tube 15 are moved axially as by a hydraulic jack actuated via a switch in response to pressure within the compressor. The tube 15 is inflated via a tapping connected to the downstream end of the compressor or to a position adjacent to the valve.
GB5124971A 1971-11-04 1971-11-04 Compressor bleed valves Expired GB1357016A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5124971A GB1357016A (en) 1971-11-04 1971-11-04 Compressor bleed valves

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5124971A GB1357016A (en) 1971-11-04 1971-11-04 Compressor bleed valves

Publications (1)

Publication Number Publication Date
GB1357016A true GB1357016A (en) 1974-06-19

Family

ID=10459246

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5124971A Expired GB1357016A (en) 1971-11-04 1971-11-04 Compressor bleed valves

Country Status (1)

Country Link
GB (1) GB1357016A (en)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2569785A1 (en) * 1984-09-06 1986-03-07 Snecma HAVE
WO1995010692A1 (en) * 1993-10-15 1995-04-20 United Technologies Corporation Active tip flow bypass in stator vane channel
US6231301B1 (en) 1998-12-10 2001-05-15 United Technologies Corporation Casing treatment for a fluid compressor
US6899513B2 (en) * 2003-07-07 2005-05-31 Pratt & Whitney Canada Corp. Inflatable compressor bleed valve system
WO2006110122A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
EP2305960A1 (en) 2009-09-28 2011-04-06 Techspace Aero S.A. Purging valve in a primary duct of a compressor and corresponding process to suppress the surge effect
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
EP2434163A1 (en) * 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Compressor
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2569785A1 (en) * 1984-09-06 1986-03-07 Snecma HAVE
EP0174892A1 (en) * 1984-09-06 1986-03-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Bypass valve for a compressor
US4679982A (en) * 1984-09-06 1987-07-14 Societe Nationale D'etude Et De Construction De Moteur D'aviation "S. N. E. C. M. A." Compressor blow-off arrangement
WO1995010692A1 (en) * 1993-10-15 1995-04-20 United Technologies Corporation Active tip flow bypass in stator vane channel
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US6231301B1 (en) 1998-12-10 2001-05-15 United Technologies Corporation Casing treatment for a fluid compressor
US6899513B2 (en) * 2003-07-07 2005-05-31 Pratt & Whitney Canada Corp. Inflatable compressor bleed valve system
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
WO2006110122A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
WO2006110122A3 (en) * 2004-12-01 2007-04-05 United Technologies Corp Inflatable bleed valve for a turbine engine and a method of operating therefore
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US8753074B2 (en) 2009-09-28 2014-06-17 Techspace Aero S.A. Aspirator insert for a boundary layer in a fluid, a wall and a compressor equipped with said insert
EP2305960A1 (en) 2009-09-28 2011-04-06 Techspace Aero S.A. Purging valve in a primary duct of a compressor and corresponding process to suppress the surge effect
EP2434163A1 (en) * 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Compressor

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees