FR3102803B1 - HVAC Chamber Synchronized Split Aircraft Engine - Google Patents

HVAC Chamber Synchronized Split Aircraft Engine Download PDF

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Publication number
FR3102803B1
FR3102803B1 FR1912009A FR1912009A FR3102803B1 FR 3102803 B1 FR3102803 B1 FR 3102803B1 FR 1912009 A FR1912009 A FR 1912009A FR 1912009 A FR1912009 A FR 1912009A FR 3102803 B1 FR3102803 B1 FR 3102803B1
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France
Prior art keywords
several
phase
splitting
chambers
valves
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FR1912009A
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French (fr)
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FR3102803A1 (en
Inventor
Bernard Macarez
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Individual
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Individual
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Priority to FR1912009A priority Critical patent/FR3102803B1/en
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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
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/12—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
    • 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

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Characterised By The Charging Evacuation (AREA)

Abstract

Un moteur (M) d’aéronef (AE) à combustion à volume constant, comportant plusieurs modules (A), agencé pour permettre un fractionnement synchronisé des phases (i) d’admission, de combustion, de détente, de balayage et/ou de refroidissement, et de purge, d’un fluide compressible à l’aide d’un procédé de contrôle de valves réalisé au cours d’un cycle thermodynamique, ledit moteur (M) comportant  plusieurs chambres de combustion (2),plusieurs vannes (3) situées à l’entrée,plusieurs vannes (4) (5)(6) situées en sortie des chambres (2),plusieurs carters (7)(8)(19) situés entre la sortie des chambres et les étages turbines (15)(16), plusieurs conduits (18), lesdites chambres (2) caractérisées en ce qu’au cours d’une phase (i) choisie, les ouvertures et les fermetures des vannes (3)(4)(5)(6), sont contrôlées pour fractionner en plusieurs fractions (j)  le déroulement d’une phase (i) afin de transférer vers les carters (7) (8) (19) (20) plusieurs fractions de masse dmi (30) égales à la masse transvasée au cours de la durée dtj (32) du fractionnement (j) choisi. Un procédé de fractionnement synchronisé des phases (i) permettant : de gérer le nombre de tubes (m)(22) d’un même groupe (B) pour que le début de la phase (i) d’une chambre (2) débute dès que la phase (i) d’un autre chambre (2) de ce même groupe (B) se termine.Appelée « synchronisation » des chambres (2) du groupe (B).au cours d’une phase (i),de décaler des durées de fractionnement dt i (32) (33),les instants de début de cycle des groupes (B) dans un module (A), appelé fractionnement (j) des phases (i),de telle sorte que les gaz sortant des vannes (4) (5) alimentent respectivement les carters (7) et (8) via les conduits (18) avec des pressions et températures moyennes distinctes HP (10) et BP (11) pour 2 fractionnements seulement.Le « fractionnement synchronisé » permettant d’obtenir à l’entrée des étages turbines (15) et (16) des fréquences d’ondes fj (34) (35) élevées (1000Hz) , augmentant les rendements turbines et les valeurs de pression et de températures à l’entrée des turbines. Figure à publier avec l’abrégé : [Fig 3]An aircraft engine (AE) with constant volume combustion, comprising several modules (A), arranged to allow a synchronized splitting of the phases (i) of intake, combustion, expansion, scavenging and/or cooling, and purging, a compressible fluid using a valve control method carried out during a thermodynamic cycle, said engine (M) comprising several combustion chambers (2), several valves ( 3) located at the inlet, several valves (4) (5) (6) located at the outlet of the chambers (2), several casings (7) (8) (19) located between the outlet of the chambers and the turbine stages ( 15)(16), several ducts (18), said chambers (2) characterized in that during a chosen phase (i), the openings and closings of the valves (3)(4)(5)( 6), are controlled to split into several fractions (j) the progress of a phase (i) in order to transfer to the casings (7) (8) (19) (20) several mass fractions dmi (30) equal to the mass tr ansvasée during the duration dtj (32) of the fractionation (j) chosen. A method of synchronized splitting of phases (i) allowing: to manage the number of tubes (m)(22) of the same group (B) so that the beginning of phase (i) of a chamber (2) begins as soon as the phase (i) of another room (2) of this same group (B) ends. Called "synchronization" of the rooms (2) of the group (B). during a phase (i), to shift the splitting times dt i (32) (33), the cycle start times of the groups (B) in a module (A), called splitting (j) of the phases (i), so that the gases coming out of the valves (4) (5) respectively feed the casings (7) and (8) via the conduits (18) with distinct average pressures and temperatures HP (10) and LP (11) for 2 fractionations only. synchronized" making it possible to obtain high (1000Hz) fj (34) (35) wave frequencies at the input of the turbine stages (15) and (16), increasing the turbine yields and the pressure and temperature values at turbine inlet . Figure to be published with abstract: [Fig 3]

FR1912009A 2019-10-30 2019-10-30 HVAC Chamber Synchronized Split Aircraft Engine Active FR3102803B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1912009A FR3102803B1 (en) 2019-10-30 2019-10-30 HVAC Chamber Synchronized Split Aircraft Engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1912009A FR3102803B1 (en) 2019-10-30 2019-10-30 HVAC Chamber Synchronized Split Aircraft Engine
FR1912009 2019-10-30

Publications (2)

Publication Number Publication Date
FR3102803A1 FR3102803A1 (en) 2021-05-07
FR3102803B1 true FR3102803B1 (en) 2022-07-15

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Family Applications (1)

Application Number Title Priority Date Filing Date
FR1912009A Active FR3102803B1 (en) 2019-10-30 2019-10-30 HVAC Chamber Synchronized Split Aircraft Engine

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FR (1) FR3102803B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1988456A (en) * 1930-03-24 1935-01-22 Milo Ab Gas turbine system
US2750735A (en) * 1951-12-24 1956-06-19 Schilling Estate Company Apparatus for the generation of driving gases by explosion and process for operating the same
FR2829528B1 (en) 2001-09-07 2004-02-27 Bernard Gilbert Macarez PULSOMOTOR-IMPULSE TURBOMOTOR-GAS TURBINE WITH IMPULSE COMBUSTION CHAMBER AND JET EXPANSION
US7228683B2 (en) * 2004-07-21 2007-06-12 General Electric Company Methods and apparatus for generating gas turbine engine thrust using a pulse detonator

Also Published As

Publication number Publication date
FR3102803A1 (en) 2021-05-07

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