FR3036736B1 - AIRCRAFT TURBOMACHINE - Google Patents

AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3036736B1
FR3036736B1 FR1554685A FR1554685A FR3036736B1 FR 3036736 B1 FR3036736 B1 FR 3036736B1 FR 1554685 A FR1554685 A FR 1554685A FR 1554685 A FR1554685 A FR 1554685A FR 3036736 B1 FR3036736 B1 FR 3036736B1
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FR
France
Prior art keywords
flow
gas
engine
outlet
fluid
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
FR1554685A
Other languages
French (fr)
Other versions
FR3036736A1 (en
Inventor
Tewfik Boudebiza
Nicolas Aussedat
Gilles Alain Charier
Lambert Olivier Marie Demoulin
Nicolas Claude Parmentier
Pierre-Alain Jean Philippe Reigner
Baptiste Jean-Marie Renault
Nicolas Jerome Jean Tantot
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
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1554685A priority Critical patent/FR3036736B1/en
Publication of FR3036736A1 publication Critical patent/FR3036736A1/en
Application granted granted Critical
Publication of FR3036736B1 publication Critical patent/FR3036736B1/en
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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/007—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid combination of cycles
    • 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
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
    • F02C1/10—Closed cycles
    • 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
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • 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
    • F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low 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
    • F05D2220/00—Application
    • F05D2220/60—Application making use of surplus or waste energy
    • F05D2220/62—Application making use of surplus or waste energy with energy recovery 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
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

Turbomachine (10) d'aéronef, comportant un moteur (12), au moins une première conduite (30) d'entrée d'un premier flux de gaz dans ledit moteur, et au moins une seconde conduite (34) de sortie d'un second flux de gaz dudit moteur, ledit second flux étant destiné à être plus chaud que ledit premier flux, la turbomachine comprenant en outre des moyens de génération d'énergie électrique, caractérisée en ce que lesdits moyens de génération comprennent un premier échangeur de chaleur (50) situé dans ou sur la seconde conduite et comportant un circuit de vaporisation, dont une entrée de fluide est reliée à un système comportant au moins une pompe (48) et un réservoir de fluide (46) et dont une sortie de fluide est reliée à une entrée de fluide d'une turbine (44) entraînant un rotor, lui-même relié à un générateur électrique, et un second échangeur de chaleur (42) situé dans ou sur la première conduite et comportant un circuit de condensation, dont une entrée de gaz est reliée à une sortie de gaz de la turbine et une sortie de liquide est reliée audit système.Aircraft turbomachine (10), comprising an engine (12), at least a first conduit (30) for entering a first flow of gas into said engine, and at least one second conduit (34) for exiting a second flow of gas from said engine, said second flow being intended to be hotter than said first flow, the turbomachine further comprising means for generating electrical energy, characterized in that said means for generating comprise a first heat exchanger (50) located in or on the second pipe and comprising a vaporization circuit, one fluid inlet of which is connected to a system comprising at least one pump (48) and one fluid reservoir (46) and one fluid outlet of which is connected to a fluid inlet of a turbine (44) driving a rotor, itself connected to an electric generator, and a second heat exchanger (42) located in or on the first pipe and comprising a condensation circuit, of which a gas inlet is connected to an outlet of gas turbine and a liquid outlet is connected to said system.

FR1554685A 2015-05-26 2015-05-26 AIRCRAFT TURBOMACHINE Active FR3036736B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1554685A FR3036736B1 (en) 2015-05-26 2015-05-26 AIRCRAFT TURBOMACHINE

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1554685A FR3036736B1 (en) 2015-05-26 2015-05-26 AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3036736A1 FR3036736A1 (en) 2016-12-02
FR3036736B1 true FR3036736B1 (en) 2021-05-28

Family

ID=53496875

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1554685A Active FR3036736B1 (en) 2015-05-26 2015-05-26 AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3036736B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100083632A1 (en) * 2008-10-08 2010-04-08 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Hybrid propulsive engine including at least one independently rotatable compressor rotor
US20140190162A1 (en) * 2009-10-27 2014-07-10 Flysteam, Llc Heat Recovery System for a Gas Turbine Engine
FR2978728B1 (en) * 2011-08-03 2014-07-04 Eads Europ Aeronautic Defence AIRCRAFT PROPULSION ARCHITECTURE INTEGRATING AN ENERGY RECOVERY SYSTEM
FR3007790B1 (en) * 2013-06-28 2018-10-19 Airbus Operations AIRCRAFT TURBOPROPOWER UNIT COMPRISING A CIRCUIT FOR RECOVERING AND CONVERTING THERMAL ENERGY

Also Published As

Publication number Publication date
FR3036736A1 (en) 2016-12-02

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