GB1223490A - Air compressor surge control apparatus - Google Patents

Air compressor surge control apparatus

Info

Publication number
GB1223490A
GB1223490A GB61643/68A GB6164368A GB1223490A GB 1223490 A GB1223490 A GB 1223490A GB 61643/68 A GB61643/68 A GB 61643/68A GB 6164368 A GB6164368 A GB 6164368A GB 1223490 A GB1223490 A GB 1223490A
Authority
GB
United Kingdom
Prior art keywords
pressure
inlet
chamber
total
pressures
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
GB61643/68A
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.)
Bendix Corp
Original Assignee
Bendix Corp
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 Bendix Corp filed Critical Bendix Corp
Publication of GB1223490A publication Critical patent/GB1223490A/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
    • F04D27/023—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
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
  • Supercharger (AREA)

Abstract

1,223,490. Axial-flow compressors. BENDIX CORP. Dec.30, 1968 [Jan.2, 1968], No.61643/68. Heading F1C. [Also in Division G4] Surge control apparatus for a multi-stage axialflow compressor 24, Fig. 1, of a gas turbine engine 20, comprises a normally closed air bleed valve 72 which is opened when surge is imminent in accordance with the relationship Ptx-Psx# K(Pt 3 -Pt 2 ), where Pt 3 is pressure derived from compressor outlet total air-pressure, Pt 2 is compressor inlet total air-pressure, Ptx and Psx are air-pressures derived from total and static air-pressures respectively both taken at the compressor inlet or outlet, and K is a constant. Inlet total pressure and outlet total and static pressures are communicated to first, second and third diaphragm-separated chambers 36, 38, 40 respectively through lines 52, 56, 60 to regulate the position of a servovalve 46 controlling the venting through line 86 of pressurized air from a chamber 84 to control the pressure Px therein and thereby control the air bleed valve 72. In an alternative embodiment, Fig.2 (not shown), the first diaphragm-separated chamber contains an evacuated bellows (116) connected to the diaphragms and to a lever-type servovalve (122) by a rod (114). Moreover, the first chamber is connected to the inlet and outlet total pressures through a respective restrictor, the second chamber is connected to outlet total pressure, and the third chamber is connected to outlet static pressure. The latter two pressures may be sensed in a Venturi (102) or in a diffuser. In another embodiment, Fig.3 (not shown), the first chamber is connected to the inlet static and outlet total pressures through a respective restrictor, the second chamber is connected to the inlet static pressure, and the third chamber is connected to the inlet total pressure. A final embodiment, Fig. 4 (not shown), employs fluidic means to directly control the pressure differential across a diaphragm (200) controlling the air bleed valve, the power jet of the fluidic means being subjected to two opposing transverse control jets connected respectively to inlet total pressure and, through respective restrictors, to inlet static and outlet total pressures.
GB61643/68A 1968-01-02 1968-12-30 Air compressor surge control apparatus Expired GB1223490A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US69524568A 1968-01-02 1968-01-02

Publications (1)

Publication Number Publication Date
GB1223490A true GB1223490A (en) 1971-02-24

Family

ID=24792218

Family Applications (1)

Application Number Title Priority Date Filing Date
GB61643/68A Expired GB1223490A (en) 1968-01-02 1968-12-30 Air compressor surge control apparatus

Country Status (4)

Country Link
US (1) US3473727A (en)
DE (1) DE1900144A1 (en)
FR (1) FR2000008A1 (en)
GB (1) GB1223490A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2909825A1 (en) * 1978-03-14 1979-09-20 Rolls Royce CONTROL SYSTEM FOR A MULTI-STAGE AXIAL FLOW COMPRESSOR OF A GAS TURBINE ENGINE
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
EP3828420A1 (en) * 2019-11-29 2021-06-02 Rolls-Royce plc Flow machine performance map modelling based on correlation with exit mass flow, data carrier and system for analysing flow machine behaviour

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3804112A (en) * 1972-07-20 1974-04-16 United Aircraft Corp Surge control for a compressor
CS175129B1 (en) * 1975-02-11 1977-04-29
USRE30329E (en) * 1975-12-01 1980-07-08 Compressor Controls Corp. Method and apparatus for antisurge protection of a dynamic compressor
US4046490A (en) * 1975-12-01 1977-09-06 Compressor Controls Corporation Method and apparatus for antisurge protection of a dynamic compressor
US4139328A (en) * 1977-05-25 1979-02-13 Gutehoffnungshitte Sterkrade Ag Method of operating large turbo compressors
US4287717A (en) * 1979-01-04 1981-09-08 Cummins Engine Company, Inc. Turbocharged internal combustion engine
US4399651A (en) * 1981-05-28 1983-08-23 Elliott Turbomachinery Co., Inc. Method for starting an FCC power recovery string
US5002459A (en) * 1988-07-28 1991-03-26 Rotoflow Corporation Surge control system
CA2671500C (en) * 2009-07-10 2011-05-24 Thomas Lemmer Pressure differential motor control system and method
US10100730B2 (en) 2015-03-11 2018-10-16 Pratt & Whitney Canada Corp. Secondary air system with venturi
US10527047B2 (en) * 2017-01-25 2020-01-07 Energy Labs, Inc. Active stall prevention in centrifugal fans

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2886968A (en) * 1948-03-17 1959-05-19 Rolls Royce Devices sensitive to the ratio between fluid pressures
US2813672A (en) * 1953-09-03 1957-11-19 Marquardt Aircraft Company Surge limiter
US3047210A (en) * 1958-12-26 1962-07-31 United Aircraft Corp Compressor surge control
US3080712A (en) * 1959-02-05 1963-03-12 Continental Aviat & Eng Corp Compressor anti-surge control for a gas turbine engine
US3248043A (en) * 1963-06-25 1966-04-26 Bendix Corp Fluid pulse surge control indicator

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2909825A1 (en) * 1978-03-14 1979-09-20 Rolls Royce CONTROL SYSTEM FOR A MULTI-STAGE AXIAL FLOW COMPRESSOR OF A GAS TURBINE ENGINE
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
EP3828420A1 (en) * 2019-11-29 2021-06-02 Rolls-Royce plc Flow machine performance map modelling based on correlation with exit mass flow, data carrier and system for analysing flow machine behaviour
US11905892B2 (en) 2019-11-29 2024-02-20 Rolls-Royce Plc Flow machine performance modelling

Also Published As

Publication number Publication date
FR2000008A1 (en) 1969-08-29
DE1900144A1 (en) 1969-07-31
US3473727A (en) 1969-10-21

Similar Documents

Publication Publication Date Title
US3487993A (en) Compressor bleed air flow control
GB1223490A (en) Air compressor surge control apparatus
GB982047A (en) Apparatus for controlling an exhaust driven super-charger for internal combustion engine
US3367256A (en) Cabin air flow control system
US3192848A (en) Air flow control system
US2775231A (en) Pneumatic control apparatus
GB1213573A (en) High-pressure valve with low-pressure operating device
US2863601A (en) Compressor air bleed control
US3849020A (en) Fluidic compressor air bleed valve control apparatus
GB736003A (en) Improvements in or relating to pressure-ratio sensitive mechanisms
US3080712A (en) Compressor anti-surge control for a gas turbine engine
US3531936A (en) Integrating fluid meter with phase lead
US3548795A (en) Fluidic fuel injection system for combustion engine
US3994617A (en) Control apparatus particularly for a plurality of compressor bleed valves of a gas turbine engine
SE7503648L (en) COMPRESSOR DRAINAGE SENSOR AND CONTROL BODY FOR POWER PLANTS, OF TURBINE TYPE.
US3060686A (en) Augmented gas turbine engine and controls
GB1007947A (en) Control means for gas turbine engines
US3167954A (en) Mass flow rate sensor for compressors
GB1432022A (en) Surge control for a compressor
US3207422A (en) Flow regulating means in aircraft air conditioning and pressurizing system
US3137210A (en) Pressure ratio bleed control
US3682192A (en) Fluidic control systems
US3027904A (en) Pneumatic control apparatus
GB827282A (en) Improvements in or relating to pressure-sensitive control mechanisms
GB735159A (en) Improvements in or relating to fuel control systems for gas-turbine power plants