FR3107307B1 - Système de récupération de chaleur pour système propulsif - Google Patents

Système de récupération de chaleur pour système propulsif Download PDF

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Publication number
FR3107307B1
FR3107307B1 FR2001417A FR2001417A FR3107307B1 FR 3107307 B1 FR3107307 B1 FR 3107307B1 FR 2001417 A FR2001417 A FR 2001417A FR 2001417 A FR2001417 A FR 2001417A FR 3107307 B1 FR3107307 B1 FR 3107307B1
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FR
France
Prior art keywords
heat recovery
propulsion system
propulsion
recovery system
heat
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
FR2001417A
Other languages
English (en)
Other versions
FR3107307A1 (fr
Inventor
William Henri Joseph Riera
Panagiotis Giannakakis
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 SA
Original Assignee
Safran SA
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 SA filed Critical Safran SA
Priority to FR2001417A priority Critical patent/FR3107307B1/fr
Publication of FR3107307A1 publication Critical patent/FR3107307A1/fr
Application granted granted Critical
Publication of FR3107307B1 publication Critical patent/FR3107307B1/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
    • 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
    • F02K3/062—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 aft fan
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/16—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like specially adapted for mounting power plant
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/20—Aircraft characterised by the type or position of power plants of jet type within, or attached to, fuselages
    • 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
    • B64D41/00—Power installations for auxiliary purposes
    • 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
    • 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
    • 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
    • F05D2220/60—Application making use of surplus or waste energy
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • 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)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

Système de récupération de chaleur pour système propulsif Système propulsif (20) comprenant au moins une turbomachine (24A, 24B), au moins une soufflante (22A, 22B) configurée pour être traversée par du gaz de combustion qui s’échappe de la turbomachine, et au moins un système de récupération (49) comprenant une machine thermique (50) configurée pour récupérer, en amont de la soufflante (22A, 22B), de la chaleur du gaz de combustion qui s’échappe de la turbomachine (24A, 24B). Aéronef comprenant un tel système propulsif (20). Figure pour l’abrégé : Fig. 4
FR2001417A 2020-02-13 2020-02-13 Système de récupération de chaleur pour système propulsif Active FR3107307B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2001417A FR3107307B1 (fr) 2020-02-13 2020-02-13 Système de récupération de chaleur pour système propulsif

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2001417A FR3107307B1 (fr) 2020-02-13 2020-02-13 Système de récupération de chaleur pour système propulsif
FR2001417 2020-02-13

Publications (2)

Publication Number Publication Date
FR3107307A1 FR3107307A1 (fr) 2021-08-20
FR3107307B1 true FR3107307B1 (fr) 2022-03-04

Family

ID=70228292

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2001417A Active FR3107307B1 (fr) 2020-02-13 2020-02-13 Système de récupération de chaleur pour système propulsif

Country Status (1)

Country Link
FR (1) FR3107307B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3128247A1 (fr) 2021-10-15 2023-04-21 Safran Système propulsif avec refroidissement du flux primaire

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1557817A (en) * 1977-08-25 1979-12-12 Penny Turbines Ltd Noel Gas turbine ducted fan engines having expansion to sub atmospheric pressure
US9765624B2 (en) * 2012-10-10 2017-09-19 Snecma Propeller comprising a counterweight system provided with an air discharge channel
FR3037106B1 (fr) 2015-06-02 2017-06-02 Snecma Turbomachine d’aeronef
US20170292447A1 (en) * 2016-04-08 2017-10-12 Hamilton Sundstrand Corporation Hybrid electric aircraft with rankine cycle heat recovery system
FR3052743B1 (fr) * 2016-06-20 2018-07-06 Airbus Operations Ensemble pour aeronef comprenant des moteurs a propulsion par ingestion de la couche limite

Also Published As

Publication number Publication date
FR3107307A1 (fr) 2021-08-20

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