Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D17/00—Regulating or controlling by varying flow
  • F01D17/10—Final actuators
  • F01D17/12—Final actuators arranged in stator parts
  • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K7/00—Plants 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
  • F02K7/02—Plants 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 the jet being intermittent, i.e. pulse-jet
  • F02K7/06—Plants 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 the jet being intermittent, i.e. pulse-jet with combustion chambers having valves
  • F02K7/067—Plants 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 the jet being intermittent, i.e. pulse-jet with combustion chambers having valves having aerodynamic valves
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
  • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
  • F02K9/32—Constructional parts; Details not otherwise provided for
  • F02K9/40—Cooling arrangements

Definitions

• the best known constant-volume combustion reactor is the "wave rotor".
• the "wave rotor” operates according to the principle of the barrel. It consists of several speakers arranged around the axis of a cylinder.
• the cylinder turns between two immobile ends called flanges. Each of its ends includes ports controlling the flow of gas including the compressor and the turbine. During rotation of the cylinder, the enclosures are thus cyclically connected to the compressor and the turbine.
• the enclosure In a first phase of the cycle, the enclosure is connected only to the compressor. The chamber then fills with compressed gas and fuel. This phase is followed by a phase during which the chamber is closed, opposing the flow of gas to the compressor or the turbine. A combustion is then carried out in the enclosure. This combustion is therefore at constant volume. Finally, the enclosure is connected to the turbine. The gases resulting from the combustion are then ejected towards the turbine.
• Humphrey's constant volume reactors in which the volume of the combustion chamber is kept constant by valves.
• the document FR2829528 describes such a reactor which comprises several combustion chambers closed periodically by butterfly valves.
• the valves partly reduce the gas leakage but, because of the alternation of the closing and opening cycles, they are subjected to repeated shocks which, under the conditions of high temperatures, of the order of 2000.degree. C, cause rapid wear.
• current constant volume combustion reactors present a risk of significant wear of surfaces subjected to pressure and temperature fluctuations.
• the invention aims to provide a reactor which does not have the aforementioned drawbacks of the prior art.
• the invention aims in particular to provide a reactor with high performance and adapted to operate under conditions of large pressure fluctuations and high temperature.
• the invention relates to a reactor, in particular an aircraft reactor, comprising at least one chamber, called combustion chamber, adapted to perform combustion during at least one stage, called combustion, and being connected.
• at least one gas inlet called compressed gas inlet
• at least one outlet called the exhaust gas outlet, by which the gases are ejected from the combustion chamber during at least one said step of said expansion
• said exhaust gas outlet including a valve, said ejection valve,
• the ejection valve comprises two rotating parts, called rotary ejection parts, the rotary ejection parts comprising curved walls and intermediate walls connecting the curved walls and being in coordinated and continuous rotation so as to to be :
• closed position In an angular position, called closed position, in which a curved wall of a rotating part ejection is substantially in contact with the other piece of curved wall in order to oppose a significant ejection of gas combustion chamber, during at least one combustion step, and
• an open position in which one of the intermediate walls of a rotary ejection piece is situated facing one wall of the other rotary ejection part in order to define an open space between the two walls through which the gases are ejected from the combustion chamber during at least one expansion step.
• the combustion chamber is closed through Vaive ejection during combustion spruced up.
• the combustion is carried out at constant volume according to the Humphrey cycle, and a higher energy efficiency is obtained than that of the usual turbomachines.
• the closure of the combustion chamber by the rotary ejection parts prevents gas leaks when they are in the closed position.
• the rotational movement of the rotating parts is fluid and progressive which eliminates shocks and / or strong pressure fluctuations, especially between the combustion and expansion stages and therefore avoids premature wear of the reactor.
• one of the intermediate walls of a rotary ejection piece is located facing one of the intermediate walls of the other rotary ejection piece.
• the rotary ejection parts are advantageously in direct rotation relative to the direction of the ejection of the gases of the combustion chamber, so as to accompany the movement of gases during their ejection and to reduce the turbulence phenomena.
• the ejection pieces may also be arranged to rotate counter to the direction of gas ejection from the combustion chamber.
• This arrangement requires the addition of so-called secondary nozzles positioned symmetrically with respect to the main nozzle through which the gases of the combustion chamber are ejected. This arrangement offers the advantage of a better filling of the fresh gases and a more complete ejection of the flue gases, as well as a significant reduction of the mechanical powers necessary for the rotation of the ejection parts.
• the rotating parts are symmetrical with respect to the axis of the combustion chamber.
• the curved walls of a rotating part have the same radius of curvature as the curved walls of the other rotary part.
• the intermediate walls of the rotating parts are convex.
• the open space through which the gases are ejected from the combustion chamber will have a shape close to that of the divergent nozzle to obtain an optimal gas ejection speed.
• the compressed gas inlet comprises a valve, called an injection valve, adapted to oppose the flow of gases between the compressed gas inlet and the combustion chamber when at least one combustion step.
• a valve called an injection valve
• the injection valve comprises two rotating parts, called rotary injection parts, similar in structure to the rotary ejection parts, and - being rotationally coordinated so as to be:
• a closed position in which a curved wall of a rotary injection part is substantially in contact with a curved wall of the other part, in order to oppose a significant flow of gases between the arrival of compressed gases and the combustion chamber, during at least one combustion step, and
• the rotary injection and ejection parts are adapted to be in fixed open position during several successive combustion-expansion stages and then in coordinated and continuous rotation so as to alternate several successive combustion-expansion cycles. during which they are in the closed position in the combustion phase and then in the open position in the expansion phase.
• the reactor When the ejection and injection valves are in the fixed open position, the reactor operates as a conventional constant pressure combustion turbine engine. This mode of operation is continuous in contrast to the constant-volume combustion that has been drawn.
• a continuous mode of operation is sometimes preferable. These are in particular the take-off and landing phases.
• the reactor according to the invention can allow continuous operation at constant pressure during takeoff followed by pulsed operation at constant volume during the cruise phase.
• the rotary injection and ejection parts are adapted to be in coordinated and continuous rotation so as to alternate several successive combustion-expansion cycles during which they are in the closed position in the combustion phase. then in the open position in the expansion phase and then in the open position for several successive stages of combustion - relaxation.
• the reactor according to the invention allows operation pulsed at constant volume during the cruise phase followed by continuous operation at constant pressure during landing.
• each combustion chamber comprises at least one fuel supply and at least one means ignition adapted to ignite a mixture of fuel and compressed gases.
• the reactor comprises several ignition means each located at different distances from the arrival of compressed gas, said ignition means being actuated in a delayed manner.
• the flue gases from the first expansion combustion will compress the unburned gases, called fresh gases, and increase their pressure beyond the initial injection pressure due to the initial compression of the compressed gases. Once a certain amount of fresh gas pressure is reached, a second ignition is triggered. The final pressure of the flue gas will be higher than that reached by flue gases from fresh compressed gases that would have undergone a single ignition. In addition, this configuration makes it possible to tend towards a sufficient pressure of fresh gas so that they ignite spontaneously according to the phenomenon of detonation.
• the rotary ejection parts are located in chambers, each chamber having at least one opening allowing the flow of gas between the outside of said chamber and the exhaust gas outlet when the rotating parts of ejection are in the closed position.
• the rotary ejection parts comprise a passage passing through them from one side to the other and adapted to allow fluid to circulate through said parts. The circulation of fluid through the parts ensures their cooling.
• the fluid flowing through the rotary ejection parts is compressed gas which comes from the arrival of compressed gases.
• the compressed gas supplying the combustion chamber is then preheated by the heat of the rotary ejection parts.
• part of the thermal energy emitted by the gases from the output of the flue gases is used to heat the compressed gases upstream of the combustion chamber.
• FIG. 1 is a sectional view of an embodiment of the reactor
• FIG. 2 a sectional view of an embodiment of the reactor during the filling step
• FIG. 3 is a sectional view of the reactor
• FIG. 4 is a sectional view of an embodiment of the reactor at the end of the combustion step
• FIG. 5 is a sectional view of FIG.
• Figure 6 is a perspective view of a rotating part
• Figure 7 is a sectional view of a rotating part.
• Figure 8 is a partial sectional view of the reactor at the outlet of the flue gases
• Figure 9 is a diagram of the yields of different thermodynamic cycles as a function of the compression ratio of the inlet gas.
• FIGS. 1 to 5 show a reactor 1 according to the invention comprising a combustion chamber 3.
• the combustion chamber 3 is supplied with compressed gas by a compressed gas inlet 4.
• the compressed gas is generated by a compressor.
• the compressed gas is compressed air at a pressure of between 2 and 4 bar.
• the combustion chamber 3 is adapted to achieve combustion.
• the combustion chamber 3 comprises at least one fuel supply 15 and at least one ignition means 16 for igniting a mixture of fuel and compressed gas.
• the combustion chamber 3 comprises several ignition means 16 each located at different distances from the raring of compressed gases. 16 can be preferably and conventionally a controlled electric ignition.
• the combustion chamber 3 may also comprise a flame tube 19 whose purpose is to keep the gases burned at a very high temperature out of contact with the walls of the combustion chamber 3.
• the combustion chamber 3 may also include dilution and embossing orifices 20 for directing a portion of the compressed air called "primary air" between the hot gases and the walls of the combustion chamber 3, and thus of contain the hot gases out of contact with the walls.
• the combustion chamber 3 is connected to an outlet 5 of the flue gases through which the gases can be ejected from the combustion chamber.
• This outlet 5 is equipped with an ejection valve 6.
• the ejection valve 6 consists of two rotary ejection parts 7, preferably symmetrical with respect to the axis of the combustion chamber 3.
• the rotary ejection pieces 7 comprise substantially curved walls 8 and intermediate walls 9 connecting the curved walls 8.
• the rotary ejection parts 7 comprise two curved walls 8 and two intermediate walls 9.
• Figure 6 illustrates a rotating part.
• the rotating part is drawn from a cylinder.
• Curved walls 8 follow the geometry of this cylinder and therefore have the same radius of curvature.
• the intermediate walls 9 are convex and have a radius of curvature greater than the radius of the initial cylinder.
• the rotating parts comprise a passage passing through them from one side to the other and adapted to allow a circulation of fluid, in particular a cooling fluid, through said parts.
• the passage is of helical shape, the axis of the helicoid being the axis of rotation of the parts so as to accelerate the circulation of the cooling fluid. through the rotating part.
• the compressed gas inlet 4 comprises an injection valve 11.
• the injection valve 11 is of a structure similar to the ejection valve 6, ie it consists of two rotating parts, called rotary rotating parts. Injection 12, these rotating injection parts 12 themselves being of a similar structure to the rotary ejection parts 7. Indeed, they comprise curved walls and intermediate walls connecting the curved walls.
• these rotary injection parts 12 are symmetrical with respect to the axis of the combustion chamber 3 and comprise two curved walls and two convex intermediate walls and having a radius of curvature greater than that of curved walls.
• the rotary ejection 7 and injection 12 parts are preferably located in chambers 17.
• An opening 18 is provided at the chambers 17 of the rotary ejection pieces 7. This opening 18 connects the outside to the interior of the chamber 17.
• Figure 2 shows the reactor 1 during the filling step.
• the combustion chamber 3 is supplied with compressed gas.
• the injection valve 11 is in the open position.
• the rotary injection parts 12 are then in an angular position, called an open position, in which an intermediate wall 14 of a rotary injection part is located facing an intermediate wall 14 a wall of the other rotary injection part in order to define a space through which the compressed gases feed the combustion chamber 3 during at least one filling step.
• the ejection valve 6 is also in the open position.
• the rotary ejection pieces 7 are then in an angular position in which one of the intermediate walls 9 of a rotary ejection piece 7 is situated opposite an intermediate wall of a wall of the other rotary ejection piece 7 to define an open space 10 between the two walls through which the gases are ejected from the combustion chamber 3.
• the combustion chamber 3 is thus filled with fresh 21 compressed, i in case of i compressed air, driving ies gas remaining in the combustion chamber 3.
• the rotating ejection parts 7 are rotated around their central axis . This movement is preferably carried out in the direction of ejection of the gases from the combustion chamber 3 in order to reduce the turbulence phenomena.
• the rotary ejection pieces 7 which were in an open position in which two of their intermediate walls 9 were facing each other during the filling step, as illustrated in FIG. 2, will undergo a rotational movement.
• This rotational movement is coordinated and continuous so that a curved wall 8 of a rotary ejection piece 7 comes into contact with a curved wall 8 of the other part.
• the curved walls 8 oppose their contact with the ejection of gas from the combustion chamber 3.
• the rotary ejection pieces 7 are then in a closed position, as shown in FIGS. 3 and 4.
• the clearance is defined to oppose a significant flow of gases through the outlet 5 of the flue gases, in particular due to the phenomenon of aerodynamic blockage.
• the pressure of the burnt gases in the space 10 becomes lower than the external atmospheric pressure thus creating a negative thrust.
• the opening 18 connects the outside and the outlet of the burnt gases at the beginning of the combustion phase shown in FIG. 8. Thanks to this opening 18, the equilibrium pressure is restored.
• the rotating injection parts 12 which were in an open position in which two of their intermediate walls were facing each other during the filling step, like this was shown in Figure 2, will also undergo a rotational movement. This movement is preferably in the direction of the injection of the gases of the combustion chamber 3 in order to reduce the turbulence phenomena.
• This rotational movement is coordinated and continuous so that a curved wall of a rotating injection part 12 comes into contact with a curved wall of the other part.
• the curved walls are opposed by their contact with the flow of gases between the inlet 4 of the compressed gases and the combustion chamber 3.
• the rotary injection parts 12 are then in a closed position, as shown in FIGS. Figures 3 and 4. Just as for rotary ejection parts 7, there is a slight clearance between the two curved walls to avoid the risk of shock and wear on these walls.
• the injection and ejection valves are thus in the closed position. They respectively oppose the flow of gas between the inlet 4 of compressed gas and the combustion chamber 3 and the ejection of the gases from the combustion chamber 3, thus keeping the combustion chamber 3 at a constant volume.
• the combustion step is then performed. This step is illustrated in FIGS. 3 and 4. As illustrated in FIG. 9, Humphrey's constant volume combustion has a much better energy efficiency than Joule-Brayton cycle constant pressure combustion.
• the combustion chamber 3 is supplied with fuel via a fuel supply 15.
• the compressed gas-fuel mixture is ignited by ignition means 16.
• the flue gases 22 from the first expanding combustion will compress the unburned gases, so-called fresh gases, and increase their pressure beyond the initial injection pressure. Once a certain amount of fresh gas pressure is reached, a second ignition is triggered. The final pressure of the flue gas will be higher than that reached by flue gases from fresh compressed gases that would have undergone a single ignition.
• the intermediate walls 9 being of convex shape, when the rotary ejection pieces 7 are in the open position, the space 10 through which the gases are ejected from the combustion chamber is of a shape similar to that of the diverging portion of a nozzle.
• the injection valve 11 remains in the closed position during the expansion step.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Physics & Mathematics (AREA)
• Fluid Mechanics (AREA)
• Fluidized-Bed Combustion And Resonant Combustion (AREA)
• Combustion Methods Of Internal-Combustion Engines (AREA)
• Exhaust Silencers (AREA)

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• 2009
  • 2009-08-12 FR FR0903942A patent/FR2945316B1/fr not_active Expired - Fee Related
• 2010
  • 2010-01-15 WO PCT/EP2010/000195 patent/WO2010086091A1/fr not_active Ceased
  • 2010-01-15 CA CA2748891A patent/CA2748891A1/fr not_active Abandoned
  • 2010-01-15 EP EP10700712A patent/EP2391802A1/fr not_active Withdrawn
  • 2010-01-15 BR BRPI1007499A patent/BRPI1007499A2/pt not_active IP Right Cessation
  • 2010-01-15 US US13/142,673 patent/US8925296B2/en not_active Expired - Fee Related

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