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ES2107521T3 - Sistema para descargar a baja presion y con un alto grado de dilucion; el fluido caliente de un dispositivo de deshielo a la entrada de aire de un turbo-reactor. - Google Patents

Sistema para descargar a baja presion y con un alto grado de dilucion; el fluido caliente de un dispositivo de deshielo a la entrada de aire de un turbo-reactor.

Info

Publication number
ES2107521T3
ES2107521T3 ES92830507T ES92830507T ES2107521T3 ES 2107521 T3 ES2107521 T3 ES 2107521T3 ES 92830507 T ES92830507 T ES 92830507T ES 92830507 T ES92830507 T ES 92830507T ES 2107521 T3 ES2107521 T3 ES 2107521T3
Authority
ES
Spain
Prior art keywords
low pressure
high degree
air inlet
turbo
dilution
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 - Lifetime
Application number
ES92830507T
Other languages
English (en)
Inventor
Enzo Farinazzo
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.)
Leonardo SpA
Original Assignee
Alenia Aeritalia e Selenia SpA
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 Alenia Aeritalia e Selenia SpA filed Critical Alenia Aeritalia e Selenia SpA
Application granted granted Critical
Publication of ES2107521T3 publication Critical patent/ES2107521T3/es
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
    • B64D15/04—Hot gas application
    • 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
    • F02C7/047—Heating to prevent icing
    • 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—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Separation Of Particles Using Liquids (AREA)
  • Supercharger (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

LA CARCASA HUECA (4) QUE CONSTITUYE LA TOMA DE AIRE DE UN MOTOR A REACCION TIENE UNA SALIDA PARA EL AIRE CALIENTE QUE SE USA PARA EVITAR LA FORMACION DE HIELO SOBRE EL BORDE FRONTAL DE LA CARCASA. LA SALIDA ESTA CONSTITUIDA POR UNA PLURALIDAD DE RANURAS (15) QUE ESTAN DISPUESTAS Y CONFORMADAS DE MANERA TAL QUE GENERAN UN CHORRO DE BAJA PRESION DE AIRE CALIENTE QUE SUFRE UN ALTO GRADO DE MEZCLA CON EL AIRE EXTERNO Y QUE CONSECUENTEMENTE SE ENFRIA DE FORMA QUE NO QUEME LOS PANELES QUE CONSTITUYEN LA PARED EXTERIOR DEL ALOJAMIENTO DEL MOTOR QUE SE ENCUENTRAN INMEDIATAMENTE DEBAJO DE LA CORRIENTE QUE FORMA LA SALIDA DEL AIRE CALIENTE.
ES92830507T 1991-10-03 1992-09-22 Sistema para descargar a baja presion y con un alto grado de dilucion; el fluido caliente de un dispositivo de deshielo a la entrada de aire de un turbo-reactor. Expired - Lifetime ES2107521T3 (es)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ITTO910750A IT1250510B (it) 1991-10-03 1991-10-03 Sistema di scarico a bassa pressione ed alta miscelazione per il fluido di riscaldamento di un dispositivo anti-ghiaccio previsto nella presa d'aria di un motore turbo-getto.

Publications (1)

Publication Number Publication Date
ES2107521T3 true ES2107521T3 (es) 1997-12-01

Family

ID=11409623

Family Applications (1)

Application Number Title Priority Date Filing Date
ES92830507T Expired - Lifetime ES2107521T3 (es) 1991-10-03 1992-09-22 Sistema para descargar a baja presion y con un alto grado de dilucion; el fluido caliente de un dispositivo de deshielo a la entrada de aire de un turbo-reactor.

Country Status (7)

Country Link
EP (1) EP0536089B1 (es)
JP (1) JP3220258B2 (es)
AT (1) ATE154790T1 (es)
DE (1) DE69220548T2 (es)
DK (1) DK0536089T3 (es)
ES (1) ES2107521T3 (es)
IT (1) IT1250510B (es)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2771451B1 (fr) * 1997-11-21 2000-04-14 Aerospatiale Dispositif de protection pour capot d'entree d'air de moteur a reaction, pourvu d'un systeme de degivrage
FR2771776B1 (fr) 1997-12-02 2000-01-28 Aerospatiale Dispositif d'evacuation d'air chaud pour capot d'entree d'air de moteur a reaction, a circuit de degivrage
FR2772341B1 (fr) * 1997-12-12 2000-03-24 Aerospatiale Diffuseur d'air chaud pour capot d'entree d'air de moteur a reaction a circuit de degivrage
US6267328B1 (en) * 1999-10-21 2001-07-31 Rohr, Inc. Hot air injection for swirling rotational anti-icing system
FR2802573B1 (fr) 1999-12-21 2002-02-15 Aerospatiale Matra Airbus Dispositif d'evacuation d'air chaud pour capot d'entree d'air de moteur a reaction, a circuit de degivrage
FR2924409B1 (fr) * 2007-12-03 2010-05-14 Airbus France Nacelle d'aeronef comprenant des moyens d'evacuations d'air chaud
US20120241561A1 (en) * 2011-03-24 2012-09-27 Cox & Company, Inc. Method and apparatus for protecting aircraft and aircraft engines against icing
CN103184935B (zh) * 2011-12-28 2015-06-10 中航商用航空发动机有限责任公司 发动机进气道用热气防冰装置
EP2740905B1 (fr) * 2012-12-07 2020-03-18 Safran Aero Boosters SA Bec de séparation d'une turbomachine axiale, compresseur et turbomachine axiale associés
US9764847B2 (en) * 2013-10-18 2017-09-19 The Boeing Company Anti-icing system for aircraft
US10138811B2 (en) * 2014-03-13 2018-11-27 The Boeing Company Enhanced temperature control anti-ice nozzle
US9764849B2 (en) * 2014-09-18 2017-09-19 The Boeing Company Method of attaching nacelle structure to minimize fatigue loading
US10221765B2 (en) 2016-08-26 2019-03-05 Honeywell International Inc. Anti-icing exhaust system
FR3081926B1 (fr) 2018-05-30 2021-01-15 Safran Aircraft Engines Embouchure d'un conduit de gaz chaud de moteur d'aeronef a travers une paroi du moteur
US11208952B2 (en) * 2018-07-03 2021-12-28 Rohr, Inc. Inlet—NAI exhaust hole definition for reduced D-duct resonance noise and diluted exhaust plume for thermal control
FR3086642A1 (fr) * 2018-09-28 2020-04-03 Airbus Operations Dispositif de reduction voire de suppression du bruit tonal pour systeme de degivrage de groupe propulsif d'aeronef
CN113804394B (zh) * 2021-11-10 2023-03-21 中国空气动力研究与发展中心低速空气动力研究所 一种喷气防冰装置、冰形在线测量系统及方法

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4482114A (en) * 1981-01-26 1984-11-13 The Boeing Company Integrated thermal anti-icing and environmental control system
US4782658A (en) * 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
US5114100A (en) * 1989-12-29 1992-05-19 The Boeing Company Anti-icing system for aircraft

Also Published As

Publication number Publication date
EP0536089A1 (en) 1993-04-07
EP0536089B1 (en) 1997-06-25
IT1250510B (it) 1995-04-08
ITTO910750A0 (it) 1991-10-03
DK0536089T3 (da) 1998-02-02
ITTO910750A1 (it) 1993-04-04
JP3220258B2 (ja) 2001-10-22
DE69220548T2 (de) 1998-02-19
ATE154790T1 (de) 1997-07-15
JPH06221184A (ja) 1994-08-09
DE69220548D1 (de) 1997-07-31

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