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GB1480366A - Air intake regulating system for aircraft propulsion unit - Google Patents

Air intake regulating system for aircraft propulsion unit

Info

Publication number
GB1480366A
GB1480366A GB4936174A GB4936174A GB1480366A GB 1480366 A GB1480366 A GB 1480366A GB 4936174 A GB4936174 A GB 4936174A GB 4936174 A GB4936174 A GB 4936174A GB 1480366 A GB1480366 A GB 1480366A
Authority
GB
United Kingdom
Prior art keywords
signal
passed
unit
derived
air
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
GB4936174A
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.)
Airbus Defence and Space GmbH
Original Assignee
Messerschmitt Bolkow Blohm AG
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 Messerschmitt Bolkow Blohm AG filed Critical Messerschmitt Bolkow Blohm AG
Publication of GB1480366A publication Critical patent/GB1480366A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/057—Control or regulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2200/00—Mathematical features
    • F05D2200/10—Basic functions
    • F05D2200/11—Sum

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feedback Control In General (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1480366 Gas turbine jet engines - air intake control MESSERSCHMITT-BÍLKOW-BLOHM GmbH 14 Nov 1974 [27 Nov 1973] 49361/74 Heading F I G [ Also in Division G3] The invention relates to a method of regulating the air-flow to a propulsion unit of an aircraft, the air intake comprising a fixed ramp 1 and one or more movable ramp(s) 2,3 which is or are adjustable to match intake air-flow to engine demand. The ratio of the air-pressure above a movable ramp (PSB) to the total pressure of the external air-flow (Pt) forms a parameter (#BACT) which is compared with the required value of the parameter (#BREQ) under the prevailing flight conditions, the result of the comparison (E) being used to effect adjustment of the movable ramp or ramps. The pressure (PSB) above movable ramp 2 is sensed at 17 and the pressure (Pt) is sensed at 16, the ratio PSB/Pt being indicated at #BACT and passed to a comparator 30 to which the parameter #BREQ derived from unit 35 is also passed. The resulting difference signal is passed in parallel through a proportional and an integral device Kp and Kl/s producing a signal XREQ which is compared in a comparator 36 with the signal XACT, the resulting signal #X(i.e. XREQ-XACT) being passed to actuator 19 which controls the position of the movable ramps 2, 3. A signal #BREF is derived in the unit 31 from signals M (Mach number) derived from Pt (total pressure) divided by PS (static pressure), and α(angle of attack, sensed at 14), the signal #BREF being passed to unit 35. A signal XREF is derived from unit 32 from signals M (Mach number) and α(angle of attack), the signal XREF being compared with XACT in comparator 33 (signal XACT being the actual position of the ramps 2, 3). The difference between these two signals #X is passed to a unit 34 from which a signal ##B is derived, this signal being passed to unit 35 where it is compared with signal #BREF derived from unit 31. The resulting signal #BREQ is passed to the comparator 30 to which signal #BACT is also passed.
GB4936174A 1973-11-27 1974-11-14 Air intake regulating system for aircraft propulsion unit Expired GB1480366A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19732358926 DE2358926C3 (en) 1973-11-27 1973-11-27 Regulation of adjustable supersonic air inlets, in particular two-dimensional oblique thrust diffusers for gas turbine jet engines for propelling high-performance aircraft

Publications (1)

Publication Number Publication Date
GB1480366A true GB1480366A (en) 1977-07-20

Family

ID=5899148

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4936174A Expired GB1480366A (en) 1973-11-27 1974-11-14 Air intake regulating system for aircraft propulsion unit

Country Status (5)

Country Link
DE (1) DE2358926C3 (en)
FR (1) FR2252489B1 (en)
GB (1) GB1480366A (en)
IN (1) IN144247B (en)
IT (1) IT1025770B (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000055485A2 (en) * 1999-02-25 2000-09-21 Alliedsignal Inc. Control of the inlet of an auxiliary power unit
EP3412563A1 (en) * 2017-06-08 2018-12-12 Airbus Defence and Space GmbH Variable and adaptable diverterless bump inlet
CN111216905A (en) * 2020-01-09 2020-06-02 中国航空工业集团公司沈阳飞机设计研究所 Method for controlling starting adjustment angle of inclined plate by adopting nonlinear control law

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2833771C2 (en) * 1978-08-02 1985-12-19 Messerschmitt-Bölkow-Blohm GmbH, 8000 München Adjustable air inlet, in particular two-dimensional angled shock diffuser for gas turbine jet engines for propelling high-performance aircraft
US4523603A (en) * 1978-08-02 1985-06-18 Peikert Juergen Air intake control for an adjustable air inlet, particularly two-dimensional oblique shock diffuser for gas turbine jet engines for the propulsion of high performance aircraft
DE2846972C1 (en) * 1978-10-28 1986-07-17 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Adjustable air inlet, in particular a two-dimensional oblique shock diffuser for gas turbine jet engines for propelling aircraft

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000055485A2 (en) * 1999-02-25 2000-09-21 Alliedsignal Inc. Control of the inlet of an auxiliary power unit
WO2000055485A3 (en) * 1999-02-25 2000-12-21 Allied Signal Inc Control of the inlet of an auxiliary power unit
EP3412563A1 (en) * 2017-06-08 2018-12-12 Airbus Defence and Space GmbH Variable and adaptable diverterless bump inlet
RU2696410C1 (en) * 2017-06-08 2019-08-01 Эйрбас Дефенс Энд Спэйс Гмбх Aircraft engine air intake operation method and air intake
US11111028B2 (en) 2017-06-08 2021-09-07 Airbus Defence and Space GmbH Variable and adaptable diverterless bump inlet
CN111216905A (en) * 2020-01-09 2020-06-02 中国航空工业集团公司沈阳飞机设计研究所 Method for controlling starting adjustment angle of inclined plate by adopting nonlinear control law

Also Published As

Publication number Publication date
DE2358926A1 (en) 1975-05-28
IT1025770B (en) 1978-08-30
FR2252489B1 (en) 1978-09-22
FR2252489A1 (en) 1975-06-20
IN144247B (en) 1978-04-15
DE2358926C3 (en) 1979-08-02
DE2358926B2 (en) 1978-12-07

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Legal Events

Date Code Title Description
PS Patent sealed
746 Register noted 'licences of right' (sect. 46/1977)
PCNP Patent ceased through non-payment of renewal fee