[go: up one dir, main page]

GB987625A - Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines - Google Patents

Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines

Info

Publication number
GB987625A
GB987625A GB40522/63A GB4052263A GB987625A GB 987625 A GB987625 A GB 987625A GB 40522/63 A GB40522/63 A GB 40522/63A GB 4052263 A GB4052263 A GB 4052263A GB 987625 A GB987625 A GB 987625A
Authority
GB
United Kingdom
Prior art keywords
chamber
compressor
gas turbine
valve
valve device
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
GB40522/63A
Inventor
Nelson Hector Kent
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 GB40522/63A priority Critical patent/GB987625A/en
Priority to DE19641428228 priority patent/DE1428228A1/en
Publication of GB987625A publication Critical patent/GB987625A/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
    • 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
    • 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)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluid-Driven Valves (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

987,625. Axial-flow compressors; gas turbine jet propulsion plant. ROLLS-ROYCE Ltd. Oct. 14, 1963. No. 40522/63. Headings F1C, F1G and F1J. In an axial-flow compressor 12 mounted within a casing 16 having a chamber 22 disposed externally thereof, the chamber communicates with the compressor by a single aperture or a single set of apertures 21 in the casing, and first and second valve devices 23, 24 communicate with the chamber and are adapted to control air flow therethrough from the chamber. The compressor 12 is the high pressure compressor of a double-spool gas turbine jet propulsion engine of the by-pass type. The valve device 23 comprises an annular valve obturating member 25 co-operating with an annular seat 26, and controls the flow of air to the engine by-pass duct 15 for anti-surge purposes. A detailed description of the valve device 23 appears in Specifications 864,519 and 938,534. The valve device 24 comprises one or more ducts 30 each containing a flap valve 31 controlling air flow to, for example, blown flaps of an aircraft or to auxiliary equipment The valve device 23 may be operated by a speed governor driven by the compressor shaft. The arrangement may be such that the flap valve 31 is closed whilst the valve device 23 is in operation. The chamber 22 may be mounted on the external casing of a simple gas turbine engine.
GB40522/63A 1963-10-14 1963-10-14 Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines Expired GB987625A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB40522/63A GB987625A (en) 1963-10-14 1963-10-14 Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines
DE19641428228 DE1428228A1 (en) 1963-10-14 1964-10-05 compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB40522/63A GB987625A (en) 1963-10-14 1963-10-14 Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines

Publications (1)

Publication Number Publication Date
GB987625A true GB987625A (en) 1965-03-31

Family

ID=10415313

Family Applications (1)

Application Number Title Priority Date Filing Date
GB40522/63A Expired GB987625A (en) 1963-10-14 1963-10-14 Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines

Country Status (2)

Country Link
DE (1) DE1428228A1 (en)
GB (1) GB987625A (en)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3475906A (en) * 1966-04-01 1969-11-04 Entwicklungsring Sued Gmbh Heat exchanger for aircraft air conditioning systems
US3945759A (en) * 1974-10-29 1976-03-23 General Electric Company Bleed air manifold
US4155681A (en) * 1977-02-14 1979-05-22 General Electric Company Manifold protection system
US5117629A (en) * 1989-04-05 1992-06-02 Rolls-Royce Plc Axial flow compressor
US5351478A (en) * 1992-05-29 1994-10-04 General Electric Company Compressor casing assembly
EP0638725A1 (en) * 1993-08-10 1995-02-15 ABB Management AG Device for secondary air bleeding from an axial compressor
EP1249618A1 (en) * 2001-04-12 2002-10-16 Snecma Moteurs Bleed system for a turbofan with simplified control
DE102004043036A1 (en) * 2004-09-06 2006-03-09 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with fluid removal
US7364404B2 (en) 2003-11-26 2008-04-29 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid removal
US7387487B2 (en) 2003-11-26 2008-06-17 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid supply
US7967556B2 (en) 2004-06-24 2011-06-28 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with means for the creation of a peripheral jet on the stator
US8251648B2 (en) 2008-02-28 2012-08-28 Rolls-Royce Deutschland Ltd & Co Kg Casing treatment for axial compressors in a hub area
US8257022B2 (en) 2008-07-07 2012-09-04 Rolls-Royce Deutschland Ltd Co KG Fluid flow machine featuring a groove on a running gap of a blade end
US8262340B2 (en) 2004-11-17 2012-09-11 Rolls-Royce Deutschland Ltd Co KG Turbomachine exerting dynamic influence on the flow
US8382422B2 (en) 2008-08-08 2013-02-26 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine
US8419355B2 (en) 2007-08-10 2013-04-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine featuring an annulus duct wall recess
US8834116B2 (en) 2008-10-21 2014-09-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA982828A (en) * 1972-06-01 1976-02-03 General Electric Company Combustor casing cooling structure
US4463552A (en) * 1981-12-14 1984-08-07 United Technologies Corporation Combined surge bleed and dust removal system for a fan-jet engine
US4546605A (en) * 1983-12-16 1985-10-15 United Technologies Corporation Heat exchange system

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3475906A (en) * 1966-04-01 1969-11-04 Entwicklungsring Sued Gmbh Heat exchanger for aircraft air conditioning systems
US3945759A (en) * 1974-10-29 1976-03-23 General Electric Company Bleed air manifold
US4155681A (en) * 1977-02-14 1979-05-22 General Electric Company Manifold protection system
US5117629A (en) * 1989-04-05 1992-06-02 Rolls-Royce Plc Axial flow compressor
US5351478A (en) * 1992-05-29 1994-10-04 General Electric Company Compressor casing assembly
EP0638725A1 (en) * 1993-08-10 1995-02-15 ABB Management AG Device for secondary air bleeding from an axial compressor
EP1249618A1 (en) * 2001-04-12 2002-10-16 Snecma Moteurs Bleed system for a turbofan with simplified control
FR2823532A1 (en) * 2001-04-12 2002-10-18 Snecma Moteurs DISCHARGE SYSTEM FOR A TURBO-JET OR TURBO-PROPELLER WITH SIMPLIFIED CONTROL
US6622475B2 (en) 2001-04-12 2003-09-23 Snecma Moteurs Bleed system driven in simplified manner for a turbojet or turboprop engine
US7364404B2 (en) 2003-11-26 2008-04-29 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid removal
US7387487B2 (en) 2003-11-26 2008-06-17 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid supply
US7967556B2 (en) 2004-06-24 2011-06-28 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with means for the creation of a peripheral jet on the stator
DE102004043036A1 (en) * 2004-09-06 2006-03-09 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with fluid removal
US7594793B2 (en) 2004-09-06 2009-09-29 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid removal
US8262340B2 (en) 2004-11-17 2012-09-11 Rolls-Royce Deutschland Ltd Co KG Turbomachine exerting dynamic influence on the flow
US8419355B2 (en) 2007-08-10 2013-04-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine featuring an annulus duct wall recess
US8251648B2 (en) 2008-02-28 2012-08-28 Rolls-Royce Deutschland Ltd & Co Kg Casing treatment for axial compressors in a hub area
US8257022B2 (en) 2008-07-07 2012-09-04 Rolls-Royce Deutschland Ltd Co KG Fluid flow machine featuring a groove on a running gap of a blade end
US8382422B2 (en) 2008-08-08 2013-02-26 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine
US8834116B2 (en) 2008-10-21 2014-09-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side

Also Published As

Publication number Publication date
DE1428228A1 (en) 1969-01-09

Similar Documents

Publication Publication Date Title
GB987625A (en) Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines
US3368352A (en) Gas turbine engines
US3487993A (en) Compressor bleed air flow control
US2951340A (en) Gas turbine with control mechanism for turbine cooling air
US3006145A (en) Antisurge control using compressor bleed
GB790836A (en) Improvements in or relating to gas-turbine engine cooling arrangements
GB1308399A (en) Gas turbine type engines
GB1320530A (en) Gas turbine engine
GB955518A (en) Thrust-reversal in turbo-jet devices
US3915587A (en) Variable size bleed port for jet engines
GB1003734A (en) Improvements in gas turbine engines of the by-pass type
GB839344A (en) Improvements in or relating to gas-turbine engines
US3196609A (en) Gas turbine by-pass engine
GB1058927A (en) Improvements in fuel control devices for gas turbine engines
GB981857A (en) Gas turbine engine
GB634095A (en) Fuel feed and power control system of device for gas turbines, jet engines and the like
US3167954A (en) Mass flow rate sensor for compressors
US3586458A (en) Bleed control actuator for gas turbine engine
GB980306A (en) Gas turbine engine
GB701324A (en) Improvements in jet or propeller turbine engines used for aircraft propulsion
US2885856A (en) Apparatus for increasing compressor pressure ratios in a gas turbine engine
GB965465A (en) Improvements relating to compressor thrust bearings
US2544852A (en) Exhaust gas turbine with variable nozzle area for maintaining constant pressure dropthrough the turbine
GB957153A (en) Gas turbine engine
US3385065A (en) Gas turbine jet propulsion engine