BR112021019853A2 - Método para operar um motor turbojato de aeronave - Google Patents

Método para operar um motor turbojato de aeronave

Info

Publication number
BR112021019853A2
BR112021019853A2 BR112021019853A BR112021019853A BR112021019853A2 BR 112021019853 A2 BR112021019853 A2 BR 112021019853A2 BR 112021019853 A BR112021019853 A BR 112021019853A BR 112021019853 A BR112021019853 A BR 112021019853A BR 112021019853 A2 BR112021019853 A2 BR 112021019853A2
Authority
BR
Brazil
Prior art keywords
turbojet engine
guide vane
thrust
operating
aircraft turbojet
Prior art date
Application number
BR112021019853A
Other languages
English (en)
Inventor
Anthony Binder
Daniel-Ciprian Mincu
Original Assignee
Safran Aircraft Engines
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 Safran Aircraft Engines filed Critical Safran Aircraft Engines
Publication of BR112021019853A2 publication Critical patent/BR112021019853A2/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/66—Reversing fan flow using reversing fan blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Abstract

método para operar um motor turbojato de aeronave. é descrito um método para uso em um motor turbojato de aeronave (1), compreendendo uma admissão de ar (2), compreendendo uma pluralidade de palhetas guia (3), cada palheta guia (3) sendo montada, de forma móvel, entre uma posição retraída para auxiliar a fase de impulso, e uma posição estendida (b) na qual a palheta guia (3) se projeta a partir da parede interna (21) em uma direção radialmente interna a fim de guiar o fluxo de ar reverso (f-inv) da parede interna (21) para auxiliar uma fase de reversão de empuxo, método o qual pelo menos uma palheta guia (3) está na posição retraída durante uma fase de empuxo do motor turbojato (1), o método compreendendo, durante uma fase de reversão de empuxo do referido motor turbojato (1), uma etapa de movimento da palheta guia (3) para a posição estendida.
BR112021019853A 2019-04-17 2020-04-08 Método para operar um motor turbojato de aeronave BR112021019853A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1904094A FR3095240B1 (fr) 2019-04-17 2019-04-17 Entrée d’air de nacelle de turboréacteur comprenant des aubes de redresseur
PCT/EP2020/060040 WO2020212228A1 (fr) 2019-04-17 2020-04-08 Entrée d'air de nacelle de turboréacteur comprenant des aubes de redresseur

Publications (1)

Publication Number Publication Date
BR112021019853A2 true BR112021019853A2 (pt) 2022-01-18

Family

ID=67441448

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112021019853A BR112021019853A2 (pt) 2019-04-17 2020-04-08 Método para operar um motor turbojato de aeronave

Country Status (7)

Country Link
US (1) US11614051B2 (pt)
EP (1) EP3956225B1 (pt)
CN (1) CN113677595B (pt)
BR (1) BR112021019853A2 (pt)
CA (1) CA3135101A1 (pt)
FR (1) FR3095240B1 (pt)
WO (1) WO2020212228A1 (pt)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3095194B1 (fr) * 2019-04-17 2021-08-13 Safran Aircraft Engines Entrée d’air de nacelle de turboréacteur comprenant un dispositif de déviation pour favoriser une phase d’inversion de poussée
FR3126453A1 (fr) * 2021-08-25 2023-03-03 Safran Aircraft Engines Turboréacteur à aubes de guidage d’entrée
CN113650791B (zh) * 2021-09-08 2022-10-25 中国商用飞机有限责任公司 一种短舱及配备有该短舱的飞行器

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1252193A (pt) * 1969-09-26 1971-11-03
GB1244292A (en) * 1970-01-14 1971-08-25 Rolls Royce Gas turbine engine
GB1319793A (pt) * 1970-11-19 1973-06-06
US3736750A (en) * 1971-03-12 1973-06-05 Rolls Royce Power plant
GB1565212A (en) * 1975-12-22 1980-04-16 British Hovercraft Corp Ltd Ductecd fan propulsors
US4175385A (en) * 1977-12-12 1979-11-27 General Electric Company Thrust reverser for an asymmetric aircraft exhaust nozzle
US4254619A (en) * 1978-05-01 1981-03-10 General Electric Company Partial span inlet guide vane for cross-connected engines
US5156362A (en) * 1991-05-31 1992-10-20 General Electric Company Jet engine fan nacelle
US9091207B2 (en) * 2009-10-16 2015-07-28 Snecma Gas turbine engine air intake in a nacelle
FR2978990A1 (fr) * 2011-08-08 2013-02-15 Aircelle Sa Dispositif d'inversion de poussee
US10378554B2 (en) * 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
US10502160B2 (en) * 2016-02-09 2019-12-10 General Electric Company Reverse thrust engine
US10837362B2 (en) * 2016-10-12 2020-11-17 General Electric Company Inlet cowl for a turbine engine
US10815886B2 (en) * 2017-06-16 2020-10-27 General Electric Company High tip speed gas turbine engine

Also Published As

Publication number Publication date
EP3956225A1 (fr) 2022-02-23
CN113677595A (zh) 2021-11-19
FR3095240A1 (fr) 2020-10-23
FR3095240B1 (fr) 2021-06-25
JP2022529121A (ja) 2022-06-17
US11614051B2 (en) 2023-03-28
CA3135101A1 (fr) 2020-10-22
EP3956225B1 (fr) 2023-10-18
US20220170430A1 (en) 2022-06-02
WO2020212228A1 (fr) 2020-10-22
CN113677595B (zh) 2024-05-17

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