GB911535A - Compressors for gas turbine engines - Google Patents

Compressors for gas turbine engines

Info

Publication number
GB911535A
GB911535A GB28932/59A GB2893259A GB911535A GB 911535 A GB911535 A GB 911535A GB 28932/59 A GB28932/59 A GB 28932/59A GB 2893259 A GB2893259 A GB 2893259A GB 911535 A GB911535 A GB 911535A
Authority
GB
United Kingdom
Prior art keywords
vanes
compressor
valve
engine
bleed
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
GB28932/59A
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 GB28932/59A priority Critical patent/GB911535A/en
Publication of GB911535A publication Critical patent/GB911535A/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
    • 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
    • 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
    • F04D27/0223—Control schemes therefor
    • 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
    • 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
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes

Abstract

911,535. Axial-flow compressors; gasturbine plant. ROLLS-ROYCE Ltd. Aug. 16, 1960 [Aug. 24, 1959], No. 28932/59. Classes 110 (1) and 110 (3). In a gas-turbine jet-propulsion engine of the by-pass type, the inlet guide vanes 23 of the high-pressure compressor are pivoted in unison about their spindles 24 by means, which may be as described in Specification 876,504, operated by an hydraulic or pneumatic ram in accordance with engine rotational speed. Air can be bled from an intermediate stage of the high-pressure compressor into the engine bypass passage through bleed holes 30, under the control of an axially movable annular bleed valve 31 which is supported from the outer wall of the by-pass passage by pivoted links 35. When the engine is started, the vanes 23 are initially set to provide maximum swirl to reduce the load on the compressor and the bleed valve 31 is fully open to prevent surging of the compressor. When a speed of 6600 r.p.m. is reached, the control means begins to move the vanes 23 towards their normal operating position. Simultaneously, the bleed valve 31 is moved towards its closed position by means of a number of linkages each connected to a guide vane spindle 24 and comprising a crank 48, link 46 and toggle linkage 40. Rollers 49, 50 carried by the toggle linkage engage parallel cam-plates 51, 52. At 7100 r.p.m. the valve 31 reaches its fullyclosed position, with its flanges 32, 33 engaging flanges 28, 29 on the compressor casing. At the same time the rollers 49, 50 come opposite outwardly-curved portions 53, 54 of the camplates, allowing the toggle linkage 40 to collapse and permit further movement of the guide vanes 23. The normal operating position of the vanes 23 is reached at 7800 r.p.m. Flange 33 has a larger effective area than flange 32 whereby the valve 31 is urged into the closed position by the bleed air.
GB28932/59A 1959-08-24 1959-08-24 Compressors for gas turbine engines Expired GB911535A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB28932/59A GB911535A (en) 1959-08-24 1959-08-24 Compressors for gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB28932/59A GB911535A (en) 1959-08-24 1959-08-24 Compressors for gas turbine engines

Publications (1)

Publication Number Publication Date
GB911535A true GB911535A (en) 1962-11-28

Family

ID=10283532

Family Applications (1)

Application Number Title Priority Date Filing Date
GB28932/59A Expired GB911535A (en) 1959-08-24 1959-08-24 Compressors for gas turbine engines

Country Status (1)

Country Link
GB (1) GB911535A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2502247A1 (en) * 1981-03-23 1982-09-24 Avco Corp INTEGRATED MOTION CONTROL DEVICE IN MULTIPLE PLANS, FOR COMPRESSOR ORIENTABLE FINS AND AIR DISCHARGE VALVE
EP0127219A1 (en) * 1983-05-31 1984-12-05 Sulzer - Escher Wyss AG Actuating device for the variable guide vanes of an axial turbo machine
FR2569783A1 (en) * 1984-09-06 1986-03-07 Snecma RING STRUCTURE AND COMPRESSOR DISCHARGE DEVICE COMPRISING THE RING
FR2569785A1 (en) * 1984-09-06 1986-03-07 Snecma HAVE
FR2611230A1 (en) * 1987-02-25 1988-08-26 Snecma Turbine machine including a device for controlling the throughput of air for cooling the turbine
EP0298015A2 (en) * 1987-06-29 1989-01-04 United Technologies Corporation Stator valve assembly for a rotary machine
EP1041290A3 (en) * 1999-04-02 2003-01-08 Mitsubishi Heavy Industries, Ltd. Gas turbine starting method
WO2004010004A1 (en) * 2002-07-23 2004-01-29 Pratt & Whitney Canada Corp. Pneumatic compressor bleed valve

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2502247A1 (en) * 1981-03-23 1982-09-24 Avco Corp INTEGRATED MOTION CONTROL DEVICE IN MULTIPLE PLANS, FOR COMPRESSOR ORIENTABLE FINS AND AIR DISCHARGE VALVE
EP0127219A1 (en) * 1983-05-31 1984-12-05 Sulzer - Escher Wyss AG Actuating device for the variable guide vanes of an axial turbo machine
FR2569783A1 (en) * 1984-09-06 1986-03-07 Snecma RING STRUCTURE AND COMPRESSOR DISCHARGE DEVICE COMPRISING THE RING
FR2569785A1 (en) * 1984-09-06 1986-03-07 Snecma HAVE
EP0174255A1 (en) * 1984-09-06 1986-03-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Valve ring structure for a compressor bypass valve
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
US4674951A (en) * 1984-09-06 1987-06-23 Societe Nationale D'Etude et de Construction de Meteur D'Aviation (S.N.E.C.M.A.) Ring structure and compressor blow-off arrangement comprising said ring
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
FR2611230A1 (en) * 1987-02-25 1988-08-26 Snecma Turbine machine including a device for controlling the throughput of air for cooling the turbine
EP0298015A2 (en) * 1987-06-29 1989-01-04 United Technologies Corporation Stator valve assembly for a rotary machine
EP0298015A3 (en) * 1987-06-29 1989-07-05 United Technologies Corporation Stator valve assembly for a rotary machine
EP1041290A3 (en) * 1999-04-02 2003-01-08 Mitsubishi Heavy Industries, Ltd. Gas turbine starting method
WO2004010004A1 (en) * 2002-07-23 2004-01-29 Pratt & Whitney Canada Corp. Pneumatic compressor bleed valve
US6755025B2 (en) 2002-07-23 2004-06-29 Pratt & Whitney Canada Corp. Pneumatic compressor bleed valve

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