IT1248285B - Sistema integrato di prelievo da strato limite per avviatore di motore di aereo - Google Patents

Sistema integrato di prelievo da strato limite per avviatore di motore di aereo

Info

Publication number
IT1248285B
IT1248285B ITMI910585A ITMI910585A IT1248285B IT 1248285 B IT1248285 B IT 1248285B IT MI910585 A ITMI910585 A IT MI910585A IT MI910585 A ITMI910585 A IT MI910585A IT 1248285 B IT1248285 B IT 1248285B
Authority
IT
Italy
Prior art keywords
air
gas turbine
auxiliary compressor
turbine engine
aircraft
Prior art date
Application number
ITMI910585A
Other languages
English (en)
Inventor
Samuel Henry Davison
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of ITMI910585A0 publication Critical patent/ITMI910585A0/it
Publication of ITMI910585A1 publication Critical patent/ITMI910585A1/it
Application granted granted Critical
Publication of IT1248285B publication Critical patent/IT1248285B/it

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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • 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
    • F05D2220/00—Application
    • F05D2220/50—Application for auxiliary power units (APU's)
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

Un turbomotore a gas da aereo è munito di un sistema di rifornimento di aria compressa generalmente usata per soddisfare esigenze specifiche o di aria di prelievo di aereo. Questo sistema di rifornimento di aria compressa comprende un compressore ausiliario, un mezzo per azionare meccanicamente il sistema da un rotore della turbina a gas e un mezzo variatore di ciclo, come un azionatore a velocità variabile, per azionare il ciclo del compressore ausiliario indipendentemente dal ciclo del compressore del turbomotore a gas di aereo. La realizzazione preferita fornisce un mezzo per prelevare aria dallo strato limite fuori dalla navicella o da un'altra parte del guscio esterno di aereo e per usarla come sorgente di aria per il compressore ausiliario. Una realizzazione contiene una turbina ad aria su un albero comune con il compressore ausiliario e un mezzo per dirigere una porzione non usata della corrente di aria dal compressore ausiliario alla turbina ausiliaria allo scopo di aiutare ad azionare il compressore ausiliario e un'altra realizzazione contiene un mezzo per dirigere aria compressa di avviamento alla turbina ad aria per un avviamento a terra e in volo del turbomotore a gas attraverso l'azionatore a velocità variabile e un collegamento meccanico al rotore del turbomotore a gas.
ITMI910585A 1990-03-06 1991-03-06 Sistema integrato di prelievo da strato limite per avviatore di motore di aereo IT1248285B (it)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/489,150 US5136837A (en) 1990-03-06 1990-03-06 Aircraft engine starter integrated boundary bleed system

Publications (3)

Publication Number Publication Date
ITMI910585A0 ITMI910585A0 (it) 1991-03-06
ITMI910585A1 ITMI910585A1 (it) 1992-09-06
IT1248285B true IT1248285B (it) 1995-01-05

Family

ID=23942622

Family Applications (1)

Application Number Title Priority Date Filing Date
ITMI910585A IT1248285B (it) 1990-03-06 1991-03-06 Sistema integrato di prelievo da strato limite per avviatore di motore di aereo

Country Status (7)

Country Link
US (1) US5136837A (it)
JP (1) JPH04219422A (it)
CA (1) CA2036822A1 (it)
DE (1) DE4106752A1 (it)
FR (1) FR2659389A1 (it)
GB (1) GB2242235A (it)
IT (1) IT1248285B (it)

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Also Published As

Publication number Publication date
JPH04219422A (ja) 1992-08-10
GB9104388D0 (en) 1991-04-17
ITMI910585A1 (it) 1992-09-06
ITMI910585A0 (it) 1991-03-06
US5136837A (en) 1992-08-11
GB2242235A (en) 1991-09-25
FR2659389A1 (fr) 1991-09-13
DE4106752A1 (de) 1991-09-12
CA2036822A1 (en) 1991-09-07

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