FR3048727B1 - Conduit d'entree d'air pour une turbomachine d'aeronef - Google Patents

Conduit d'entree d'air pour une turbomachine d'aeronef Download PDF

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Publication number
FR3048727B1
FR3048727B1 FR1652089A FR1652089A FR3048727B1 FR 3048727 B1 FR3048727 B1 FR 3048727B1 FR 1652089 A FR1652089 A FR 1652089A FR 1652089 A FR1652089 A FR 1652089A FR 3048727 B1 FR3048727 B1 FR 3048727B1
Authority
FR
France
Prior art keywords
air inlet
inlet duct
aircraft turbomachine
turbomachine
aircraft
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
FR1652089A
Other languages
English (en)
Other versions
FR3048727A1 (fr
Inventor
Romeo Brogna
Jean-Claude Ferrier Romain
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 FR1652089A priority Critical patent/FR3048727B1/fr
Priority to GB1703904.1A priority patent/GB2550028B/en
Priority to US15/455,532 priority patent/US10415470B2/en
Publication of FR3048727A1 publication Critical patent/FR3048727A1/fr
Application granted granted Critical
Publication of FR3048727B1 publication Critical patent/FR3048727B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • 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
    • 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
    • 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
    • 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
    • F02K3/072—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 counter-rotating, e.g. fan rotors
    • 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
    • F05D2220/325—Application in turbines in gas turbines to drive unshrouded, high solidity propeller
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

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)
FR1652089A 2016-03-14 2016-03-14 Conduit d'entree d'air pour une turbomachine d'aeronef Active FR3048727B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1652089A FR3048727B1 (fr) 2016-03-14 2016-03-14 Conduit d'entree d'air pour une turbomachine d'aeronef
GB1703904.1A GB2550028B (en) 2016-03-14 2017-03-10 Air inlet duct for an aircraft turbine engine
US15/455,532 US10415470B2 (en) 2016-03-14 2017-03-10 Air inlet duct for an aircraft turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1652089A FR3048727B1 (fr) 2016-03-14 2016-03-14 Conduit d'entree d'air pour une turbomachine d'aeronef
FR1652089 2016-03-14

Publications (2)

Publication Number Publication Date
FR3048727A1 FR3048727A1 (fr) 2017-09-15
FR3048727B1 true FR3048727B1 (fr) 2018-03-02

Family

ID=55863061

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1652089A Active FR3048727B1 (fr) 2016-03-14 2016-03-14 Conduit d'entree d'air pour une turbomachine d'aeronef

Country Status (3)

Country Link
US (1) US10415470B2 (fr)
FR (1) FR3048727B1 (fr)
GB (1) GB2550028B (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020033010A2 (fr) 2018-03-16 2020-02-13 Joby Aero Inc. Système de réduction de traînée d'aéronef, système de moteur électrique à refroidissement interne et aéronef les utilisant
US11125158B2 (en) 2018-09-17 2021-09-21 Honeywell International Inc. Ported shroud system for turboprop inlets

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4608819A (en) * 1983-12-27 1986-09-02 General Electric Company Gas turbine engine component cooling system
US4989807A (en) * 1988-04-07 1991-02-05 Grumman Aerospace Corporation S-shaped jet engine inlet diffuser
US5447283A (en) * 1994-02-02 1995-09-05 Grumman Aerospace Corporation Blown boundary layer control system for a jet aircraft
US6655632B1 (en) * 2002-08-27 2003-12-02 General Electric Company System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine
GB0418196D0 (en) * 2004-08-14 2004-09-15 Rolls Royce Plc Boundary layer control arrangement
US7678165B2 (en) * 2006-12-28 2010-03-16 General Electric Company Particle separator using boundary layer control
US8082726B2 (en) * 2007-06-26 2011-12-27 United Technologies Corporation Tangential anti-swirl air supply
FR2970302B1 (fr) * 2011-01-11 2015-07-17 Snecma Turboreacteur a double flux
US8820084B2 (en) * 2011-06-28 2014-09-02 Siemens Aktiengesellschaft Apparatus for controlling a boundary layer in a diffusing flow path of a power generating machine
GB201121889D0 (en) * 2011-12-20 2012-02-01 Rolls Royce Plc Active flow control intake for a gas turbine engine
GB201406952D0 (en) * 2014-04-17 2014-06-04 Rolls Royce Plc Open rotor propulsion engine
US9789954B2 (en) * 2014-04-25 2017-10-17 Rohr, Inc. Method of controlling boundary layer flow
FR3023322B1 (fr) * 2014-07-03 2019-09-06 Safran Aircraft Engines Manche d'entree d'air pour turbomachine

Also Published As

Publication number Publication date
GB2550028A (en) 2017-11-08
US10415470B2 (en) 2019-09-17
GB201703904D0 (en) 2017-04-26
GB2550028B (en) 2020-09-09
US20170260903A1 (en) 2017-09-14
FR3048727A1 (fr) 2017-09-15

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