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1. WO2010086091 - JET ENGINE, IN PARTICULAR A JET ENGINE FOR AN AIRCRAFT

Publication Number WO/2010/086091
Publication Date 05.08.2010
International Application No. PCT/EP2010/000195
International Filing Date 15.01.2010
IPC
F01D 17/14 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
17Regulating or controlling by varying flow
10Final actuators
12arranged in stator parts
14varying effective cross-sectional area of nozzles or guide conduits
F02C 5/12 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
5Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
12the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
F02K 9/40 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
08using solid propellants
32Constructional parts; Details
40Cooling arrangements
F02K 7/02 2006.01
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
7Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
02the jet being intermittent, i.e. pulse jet
CPC
F01D 17/14
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
17Regulating or controlling by varying flow
10Final actuators
12arranged in stator parts
14varying effective cross-sectional area of nozzles or guide conduits
F02C 5/12
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
5Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
12the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
F02K 7/067
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
7Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
02the jet being intermittent, i.e. pulse-jet
06with combustion chambers having valves
067having aerodynamic valves
F02K 9/40
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
9Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
08using solid propellants
32Constructional parts; Details
40Cooling arrangements
Applicants
  • AGUILAR, Michel [FR]/[FR]
Inventors
  • AGUILAR, Michel
Agents
  • JUNCA, Eric
Priority Data
090033027.01.2009FR
090394212.08.2009FR
Publication Language French (FR)
Filing Language French (FR)
Designated States
Title
(EN) JET ENGINE, IN PARTICULAR A JET ENGINE FOR AN AIRCRAFT
(FR) REACTEUR NOTAMMENT UN REACTEUR POUR AERONEF
Abstract
(EN)
The invention relates to a jet engine (1), in particular an aircraft jet engine, including at least one combustion chamber (3). The combustion chamber (3) is connected to at least one compressed gas intake (4) and to at least one burnt gas outlet (5). Said burnt gas outlet(s) (5) include an exhaust valve. The exhaust valve includes two rotary parts (7), referred to as rotary exhaust parts, the rotary exhaust parts (7) including curved walls (8) and intermediate walls (9) connecting the curved walls (8), and rotating in a coordinated, continuous fashion such that said valve is in a closed position in order to block the exhaust gas during at least one combustion step, and in an open position in order to define a space (10) through which the exhaust gas flows out from the combustion chamber (3) during at least one expansion step.
(FR)
L'invention concerne un réacteur (1), notamment un réacteur d'aéronef, comprenant au moins une chambre de combustion (3). La chambre de combustion (3) est reliée à au moins une arrivée (4) de gaz comprimés et à au moins une sortie (5) des gaz brûlés. Ladite ou lesdites sorties (5) des gaz brûlés comprend une valve d'éjection. La valve d'éjection comprend deux pièces rotatives (7), dites pièces rotatives d'éjection, les pièces rotatives d'éjection (7) comprenant des parois courbes (8) et des parois intermédiaires (9) reliant les parois courbes (8), et étant en rotation en rotation coordonnée et continue de façon à être dans une position fermée afin de s'opposer à une éjection de gaz, lors d'au moins une étape de combustion, et dans une position ouverte afin de définir un espace (10) au travers duquel les gaz sont éjectés de la chambre de combustion (3) lors d'au moins une étape de détente.
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