FR3051016B1 - Dispositif de degivrage d'un bec de separation de turbomachine aeronautique - Google Patents

Dispositif de degivrage d'un bec de separation de turbomachine aeronautique Download PDF

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Publication number
FR3051016B1
FR3051016B1 FR1654126A FR1654126A FR3051016B1 FR 3051016 B1 FR3051016 B1 FR 3051016B1 FR 1654126 A FR1654126 A FR 1654126A FR 1654126 A FR1654126 A FR 1654126A FR 3051016 B1 FR3051016 B1 FR 3051016B1
Authority
FR
France
Prior art keywords
annular
spout
separation
interior
defrosting
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.)
Active
Application number
FR1654126A
Other languages
English (en)
Other versions
FR3051016A1 (fr
Inventor
Damien Daniel Sylvain LOURIT
Francois Marie Paul Marlin
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.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
SNECMA SAS
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 SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1654126A priority Critical patent/FR3051016B1/fr
Priority to GB1707252.1A priority patent/GB2551889B/en
Priority to US15/590,474 priority patent/US10494997B2/en
Publication of FR3051016A1 publication Critical patent/FR3051016A1/fr
Application granted granted Critical
Publication of FR3051016B1 publication Critical patent/FR3051016B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F02C7/047—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
    • 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
    • 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
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • 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
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/02—De-icing means for engines having icing phenomena
    • 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
    • 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
    • F05D2220/30—Application in turbines
    • 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
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/211—Silica

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)

Abstract

L'invention concerne un dispositif de dégivrage d'un bec de séparation (5) de turbomachine aéronautique (1), comprenant un bec de séparation (5) ayant une paroi annulaire extérieure (12) délimitant l'intérieur du canal d'écoulement du flux secondaire (4) et une paroi annulaire intérieure (10) délimitant une entrée du canal d'écoulement du flux primaire (3), et une virole interne (14) montée à l'amont sur la paroi annulaire intérieure (10) du bec de séparation et sur laquelle sont destinées à être fixées des aubes directrices d'entrée (7), le bec de séparation et la virole interne définissant un volume annulaire (18). Le dispositif comprend en outre un déflecteur annulaire (26) positionné à l'intérieur du volume annulaire séparant ledit volume annulaire en une première cavité annulaire (28), et en une deuxième cavité annulaire (30) définie entre le déflecteur annulaire (26) et la paroi annulaire extérieure (12) du bec de séparation. L'invention vise aussi un module de soufflante comportant un tel dispositif et une turbomachine aéronautique.
FR1654126A 2016-05-09 2016-05-09 Dispositif de degivrage d'un bec de separation de turbomachine aeronautique Active FR3051016B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1654126A FR3051016B1 (fr) 2016-05-09 2016-05-09 Dispositif de degivrage d'un bec de separation de turbomachine aeronautique
GB1707252.1A GB2551889B (en) 2016-05-09 2017-05-05 A device for de-icing a splitter nose of an aviation turbine engine
US15/590,474 US10494997B2 (en) 2016-05-09 2017-05-09 Device for de-icing a splitter nose of an aviation turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1654126 2016-05-09
FR1654126A FR3051016B1 (fr) 2016-05-09 2016-05-09 Dispositif de degivrage d'un bec de separation de turbomachine aeronautique

Publications (2)

Publication Number Publication Date
FR3051016A1 FR3051016A1 (fr) 2017-11-10
FR3051016B1 true FR3051016B1 (fr) 2020-03-13

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
FR1654126A Active FR3051016B1 (fr) 2016-05-09 2016-05-09 Dispositif de degivrage d'un bec de separation de turbomachine aeronautique

Country Status (3)

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US (1) US10494997B2 (fr)
FR (1) FR3051016B1 (fr)
GB (1) GB2551889B (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3047042B1 (fr) * 2016-01-22 2018-02-16 Safran Aircraft Engines Dispositif de degivrage d'un bec de separation et d'aubes directrices d'entree d'une turbomachine aeronautique
CN108138582B (zh) * 2015-07-30 2020-11-17 赛峰飞机发动机公司 用于涡轮发动机叶片的防结冰系统
BE1023531B1 (fr) * 2015-10-15 2017-04-25 Safran Aero Boosters S.A. Dispositif degivrant de bec de separation de compresseur de turbomachine axiale
US20180229850A1 (en) * 2017-02-15 2018-08-16 Pratt & Whitney Canada Corp. Anti-icing system for gas turbine engine
GB201705734D0 (en) * 2017-04-10 2017-05-24 Rolls Royce Plc Flow splitter
US11053848B2 (en) * 2018-01-24 2021-07-06 General Electric Company Additively manufactured booster splitter with integral heating passageways
FR3095230B1 (fr) * 2019-04-16 2021-03-19 Safran Aircraft Engines Dispositif de degivrage
FR3095229B1 (fr) * 2019-04-19 2021-04-23 Safran Aircraft Engines Ensemble pour flux primaire de turbomachine aéronautique, turbomachine munie de celui-ci
US11326519B2 (en) * 2020-02-25 2022-05-10 General Electric Company Frame for a heat engine
FR3111393B1 (fr) * 2020-06-12 2022-07-22 Safran Aircraft Engines Turbomachine comprenant un organe de séparation d’un flux d’air amovible
FR3115070B1 (fr) * 2020-10-08 2022-09-02 Safran Nacelles Entrée d’air supersonique d’un ensemble propulsif d’aéronef comprenant un dispositif de dégivrage des bras de support et procédé de dégivrage
US11725525B2 (en) * 2022-01-19 2023-08-15 Rolls-Royce North American Technologies Inc. Engine section stator vane assembly with band stiffness features for turbine engines

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4860534A (en) * 1988-08-24 1989-08-29 General Motors Corporation Inlet particle separator with anti-icing means
US5976997A (en) * 1996-11-12 1999-11-02 Rohr, Inc. Lightweight fire protection arrangement for aircraft gas turbine jet engine and method
US6561760B2 (en) * 2001-08-17 2003-05-13 General Electric Company Booster compressor deicer
US8205426B2 (en) * 2006-07-31 2012-06-26 General Electric Company Method and apparatus for operating gas turbine engines
EP2505789B1 (fr) * 2011-03-30 2016-12-28 Safran Aero Boosters SA Séparateur de flux gazeux avec dispositif de dégivrage par pont thermique
EP2821597B1 (fr) * 2013-07-05 2016-02-10 Techspace Aero S.A. Bec de séparation avec tôle formant une surface de guidage du flux et un canal de dégivrage

Also Published As

Publication number Publication date
US20170321604A1 (en) 2017-11-09
US10494997B2 (en) 2019-12-03
GB201707252D0 (en) 2017-06-21
GB2551889A (en) 2018-01-03
FR3051016A1 (fr) 2017-11-10
GB2551889B (en) 2021-03-31

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