RU2706870C1 - Air-jet detonation engine on solid fuel and method of its operation - Google Patents

Air-jet detonation engine on solid fuel and method of its operation Download PDF

Info

Publication number
RU2706870C1
RU2706870C1 RU2019105113A RU2019105113A RU2706870C1 RU 2706870 C1 RU2706870 C1 RU 2706870C1 RU 2019105113 A RU2019105113 A RU 2019105113A RU 2019105113 A RU2019105113 A RU 2019105113A RU 2706870 C1 RU2706870 C1 RU 2706870C1
Authority
RU
Russia
Prior art keywords
combustion chamber
reactor
pyrolysis
pyrolyzer
solid fuel
Prior art date
Application number
RU2019105113A
Other languages
Russian (ru)
Inventor
Сергей Михайлович Фролов
Виктор Серафимович Аксёнов
Игорь Олегович Шамшин
Сергей Александрович Набатников
Константин Алексеевич Авдеев
Надежда Сергеевна Шулакова
Original Assignee
Общество с ограниченной ответственностью "Новые физические принципы"
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 Общество с ограниченной ответственностью "Новые физические принципы" filed Critical Общество с ограниченной ответственностью "Новые физические принципы"
Priority to RU2019105113A priority Critical patent/RU2706870C1/en
Application granted granted Critical
Publication of RU2706870C1 publication Critical patent/RU2706870C1/en

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K7/00Plants 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
    • F02K7/10Plants 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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines

Abstract

FIELD: aviation.
SUBSTANCE: invention relates to power plants of aircraft for various purposes operating on solid fuel (for example, synthetic polymer). Method of detonation combustion of pyrolysis gases in combustion chamber of air-jet engine, at that jet reactor throttling involves blowdown of pyrolyser reactor with granulated solid fuel by high-temperature or low-temperature gases from gas generator. Combustion of pyrolysis gases mixture with air in combustion chamber takes place in detonation wave, providing heat flow to pyrolysis reactor from combustion chamber, sufficient to achieve required rate of pyrolysis gases formation in this or that operating mode, and sufficient for reliable cooling of combustion chamber design elements due to endothermic pyrolysis of granular solid fuel. Method is realized in a device in which the pyrolyser reactor is separated from the annular combustion chamber by a wall made from a material with high heat conductivity. Inside the pyrolysis reactor there is a heat exchange frame made of material with high heat conductivity and in thermal contact with the wall separating the pyrolysis reactor from the annular combustion chamber. Granulated solid fuel in pyrolyser reactor is in thermal contact both with wall separating reactor-pyrolyser from annular combustion chamber, and with elements of heat exchange frame.
EFFECT: invention enables to obtain pyrolysis products with phase and chemical composition required for self-sustained detonation combustion and reliable cooling of combustion chamber design elements.
3 cl, 1 dwg

Description

The invention relates to power plants of aircraft for various purposes (unmanned aerial vehicles, flying targets, etc.), operating on solid fuel (for example, synthetic polymer).

The main problem facing the creation of practical solid-propellant air-jet engines is the need to ensure rapid gasification (pyrolysis) of solid fuel and subsequent rapid and complete combustion of the formed fuel-air mixture in flight conditions at high speeds, as well as reliable cooling engine design. For example, during the pyrolysis of a synthetic polymer, as a rule, gaseous and condensed pyrolysis products are formed: non-condensable pyrolysis gases, condensable pyrolysis gases (liquid fraction) and coke residue, and the pyrolysis process itself is a complex set of simultaneously sequential and parallel, usually endothermic transformations. The reactions occurring during pyrolysis are divided into primary reactions with a polymer chain breaking and with the formation of a free radical and a double bond, and secondary reactions in which primary decomposition products interact with each other. Chromatomass spectrometric analysis of the liquid fraction of the pyrolysis products shows that the main products are unsaturated branched hydrocarbons (alkenes and dienes) C 8 -C 28 formed as a result of primary reactions. Their content in the liquid fraction can be up to 80%. In addition, groups of compounds formed as a result of secondary cyclization and condensation reactions are identified: o dienes, cycloalkenes, alkylbenzenes and polycyclic aromatic hydrocarbons. Therefore, to solve this problem, it is proposed to use detonation combustion (continuous-detonation, longitudinally pulsating or pulse-detonation) pyrolysis gases, which provides high heat stress of the working process and relatively low sensitivity to the type of fuel used (see Frolov S.M., Zvegintsev V. I., Ivanov V.S., Aksenov V.S., Shamshin I.O., Vnuchkov D.A., Nalyvaychenko D.G., Berlin A.A., Fomin V.M., Shiplyuk A.N., Yakovlev NN Model of a detonation ramjet engine: tests in a wind tunnel at a flow of an air stream with a Mach number of 5.7 and a temperature of 1500 K. braking combustion and explosion, 2018, Volume 11, №1, pp. 54-62).

State of the art

The known method and device proposed in the patent RU 2565131 C1, F02K 7/10 (2006.1), F02K 9/64 (2006.1), 10.20.2015. The method of operation of the device includes accelerating by means of the starting stage to the specified speed and altitude parameters, incomplete braking of the air flow in the air intake, low-temperature gasification of solid fuel in the gas generator, high-temperature decomposition of gasification products in the cooling path, mixing of air and decomposition products, ignition and burning of the mixture in the afterburner , expansion of combustion products in the nozzle. The device comprises an air intake, a gas generator with a charge of solid fuel in a separate housing, a afterburner and a nozzle. The disadvantages of the method and device include the external location of the gas generator, which requires an additional heat source to maintain the temperature regime of the gas generator.

A device is known, proposed in patent RU 2439358 C2, F02K 7/18 (2006.1), 01/10/2012. The device is a ramjet engine on a metal powder fuel - contains an engine start system, a fuel supply system including a fuel tank with a metal powder fuel and a perforated piston, a combustion chamber. A gas generator is installed in the engine casing, which enables the start-up of the powder metal fuel supply system. The combustion chamber consists of a pre-chamber, an igniter and a final fuel combustion chamber. The prechamber and afterburner have air ducts. In the prechamber, the air flow ensures the completeness of gasification of the suspension with a coefficient of excess air from 0.15 to 0.3. The disadvantages of the method and device include the need for continuous operation of the gas generator, ensuring the formation of powder suspension and its displacement in the prechamber, which requires a significant supply of fuel and an oxidizing agent for the gas generator to work in the case of a long flight.

A device is known, proposed in patent RU 2627310 C1, F02K 7/10 (2006.1), 08/07/2017. The device is a ramjet engine with an open type gas generator and an adjustable solid fuel flow rate; it contains an air intake, a system for supplying solid fuel to the combustion chamber, a gas generator, a combustion chamber, and a profiled nozzle mounted at the outlet of the combustion chamber. The gas generator is made in the form of a drum with through longitudinal channels in which solid fuel charges are placed with the possibility of their movement into the combustion chamber. In this case, the drum is connected to an annular perforated lattice, the openings of which direct the air flow to the surface of solid fuel charges. The main disadvantage of the device is the use of a pneumomechanical or hydromechanical device for supplying solid fuel, which complicates the design and, as a result, reduces its reliability.

A device is known, proposed in patent RU 2315193 C1, F02K 7/18 (2006.1), 01/20/2008. The device is a ramjet engine with a heat and mass distribution distributed along the length of the device; it contains an air intake, a gas generator with fuel, a combustion chamber with a fuel block, and an output nozzle. In the combustion chamber, fuel-carrying sections connected to the control unit with nozzles are installed for the flow of fuel jets from the internal cavities of the sections into the internal space of the combustion chamber. In each fuel-carrying section, the nozzles are distributed around the perimeter of the combustion chamber, and their axes are directed at an angle from 90 ° to 0 ° to the axis of the combustion chamber. Different fuel-carrying sections contain fuel charges that differ in chemical composition and state of aggregation. One or more fuel-carrying sections are installed in the tapering (subsonic) part of the engine output nozzle. The main disadvantage of the device is the complexity of the design, which reduces its reliability.

Closest to the proposed invention by technical essence are a ramjet solid-fuel jet engine and a method of engine operation, proposed in the article "Tests of solid fuel ramjet with measuring traction characteristics in aerodynamic installations" / D.A. Vnuchkov, V.I. Zvegintsev, D.G. Nalyvaichenko, V.I. Smolyaga, A.V. Stepanov // Thermophysics and Aeromechanics, 2018, No. 4, pp. 629-635.

The prototype method of the functioning of the prototype device includes accelerating the prototype device through the starting stage to the specified speed and altitude parameters, organizing the combustion of the fuel mixture with the oxidizing agent in the gas generator, pyrolysis of solid fuel, mixing air with pyrolysis gas, including gases from the gas generator, ignition and combustion of mixtures in the combustion chamber and expansion of the combustion products in the nozzle to create reactive thrust.

The prototype device contains a supersonic air intake, a combustion chamber with a central body with a built-in gas generator, equipped with a pyrolysis reactor, a gas manifold and a belt of radial openings for supplying gases from the gas generator to the combustion chamber with a central body, and a jet nozzle. The disadvantages of the prototype device include: (1) the need to have on board the aircraft the amount of fuel and oxidizer that is required for continuous operation of the gas generator, providing heat for the endothermic process of pyrolysis of solid fuel in the pyrolyzer reactor; (2) the pyrolysis of solid fuel in a pyrolysis reactor occurs only due to the heat from gases from the gas generator; (3) The pyrolysis gases entering the combustion chamber are always diluted with the gases from the gas generator.

Disclosure of invention

The objective of the invention is the creation of a method for organizing detonation combustion of pyrolysis gases in the combustion chamber of an aircraft engine, which will provide (1) the production of pyrolysis products with the phase and chemical composition required for self-sustaining detonation combustion and (2) reliable cooling of the structural elements of the combustion chamber.

The objective of the invention is to provide a device for implementing a method for organizing detonation combustion of pyrolysis gases in a combustion chamber of an air-jet engine, which will provide (1) the production of pyrolysis products with the phase and chemical composition required for self-sustaining detonation combustion and (2) reliable cooling of the structural elements of the combustion chamber .

The solution to this problem is achieved by the proposed:

- a method comprising flushing a solid fuel pyrolyzer reactor with gases from a gas generator, pyrolyzing solid fuel in a pyrolysis reactor to form pyrolysis gases, supplying pyrolysis gases from the pyrolysis reactor to the combustion chamber and mixing them with atmospheric air entering the combustion chamber, with subsequent combustion of the formed combustible mixture in the combustion chamber and the expiration of combustion products from the combustion chamber into the atmosphere in the form of a jet stream creating a jet propulsion in which solid fuel is granulated The injection of a solid fuel pyrolyzer reactor from the gas generator is used only for throttling reactive thrust by transferring the pyrolyzer reactor to one or another operating mode with the required rate of pyrolysis gas formation, and if one or another operating mode of the pyrolyzer reactor is violated, to restore it, moreover, the required rate of formation of pyrolysis gases in the pyrolyzer reactor in the operating mode is ensured by the flow of heat into the pyrolyzer reactor from the combustion chamber in thermal contact f with a pyrolyzer reactor, and the mixture of pyrolysis gases with air in the combustion chamber is burned in a detonation wave, which provides a heat flux into the pyrolyzer reactor from the combustion chamber, sufficient to achieve the required rate of pyrolysis gas formation in the pyrolyzer reactor at one or another working mode, as well as sufficient for reliable cooling of the structural elements of the combustion chamber due to the endothermic pyrolysis of granular solid fuel.

- a device containing a supersonic air intake, a combustion chamber with a central body with an integrated gas generator equipped with a pyrolysis reactor, a gas manifold and a belt of radial openings for supplying gases to the combustion chamber with a central body, and a jet nozzle in which a pyrolyzer reactor is integrated in the central the body and installed between the gas generator and the gas collector is filled with granular solid fuel, and the pyrolyzer reactor and gas generator communicate with each other through an expanding channel, and a ctor pyrolyzer and a gas collector through a perforated baffle, the pyrolyzer reactor being separated from the annular combustion chamber by a wall made of a material with high thermal conductivity, and is adjacent to the region of the annular combustion chamber where heat is generated in the detonation wave mainly and inside the reactor the pyrolyzer is located heat exchange frame made of a material with high thermal conductivity and is in thermal contact with the wall separating the pyrolyzer reactor from the annular combustion chamber, and gr the annulled solid fuel in the pyrolyzer reactor is in thermal contact with both the wall separating the pyrolyzer reactor from the annular combustion chamber and the elements of the heat exchange frame, and the annular combustion chamber is equipped with a knock initiator having any known construction.

The heat exchange frame can be made in the form of an assembly of transverse perforated disks and longitudinal rods in thermal contact with each other and with the wall separating the pyrolyzer reactor from the annular combustion chamber.

The gas generator may be of any known design that provides the generation of both low-temperature and high-temperature gases in the temperature range required for throttling the thrust of the proposed device.

Brief Description of the Drawings

In FIG. 1 shows a diagram of a device for an air-reactive detonation engine based on solid fuel with detonation combustion of a mixture of pyrolysis gases with air: 1 - an annular combustion chamber, 2 - a central body, 3 - a housing, 4 - a supersonic air intake, 5 - a jet nozzle, 6 - a reactor pyrolyzer, 7 - gas generator, 8 - gas manifold, 9 - radial hole belt, 10 - expanding channel, 11 - perforated partition, 12 - wall, 13 - heat transfer frame, 14 - transverse perforated disk, 15 - longitudinal rod, GTT - granular solid then livo, PG - pyrolysis gases ID -initsiator detonation ET - detonation wave, A - an annular region of the combustion chamber (1), wherein the heat dissipation occurs mainly in a detonation wave.

The implementation of the invention

In FIG. 1 is a diagram of the proposed device with detonation combustion of a mixture of pyrolysis gases of solid fuel with air.

The main element of the device is an annular combustion chamber (1), formed by the central body (2) and the housing (3), equipped with a knock initiator (ID). A supersonic air intake (4) is connected to the input section of the annular combustion chamber (1). A jet nozzle (5) is connected to the output section of the annular combustion chamber (1). A pyrolyzer reactor (6) with granular solid fuel (GTT), a gas generator (7) and a gas manifold (8) equipped with a belt of radial openings (9) for supplying gas to the annular combustion chamber (1) are built into the central body (2). The pyrolyzer reactor (6) is installed between the gas generator (7) and the gas manifold (8). The pyrolyzer reactor (6) and the gas generator (7) communicate with each other through an expanding channel (10). The pyrolyzer reactor (6) and the gas manifold (8) communicate with each other through a perforated partition (11). The pyrolyzer reactor (6) is separated from the annular combustion chamber (1) by a wall (12) made of a material with high thermal conductivity, and borders on the region (A) of the annular combustion chamber (1), where mainly heat is generated in the detonation wave (LW) ) Inside the pyrolyzer reactor (6) there is a heat exchange frame (13) made of a material with high thermal conductivity and in thermal contact with the wall (12) separating the pyrolyzer reactor (6) from the annular combustion chamber (1). Granular solid fuel (GTT) in the pyrolyzer reactor (6) is in thermal contact with both the wall (12) separating the pyrolyzer reactor (6) from the annular combustion chamber (1) and with the elements of the heat exchange frame (13).

The heat exchange frame (13) can be made in the form of an assembly of transverse perforated disks (14) and longitudinal rods (15) that are in thermal contact with each other and with the wall (12) separating the pyrolyzer reactor (6) from the annular combustion chamber (one).

The gas generator (7) may have any known design that provides the generation of both low-temperature and high-temperature gases in the temperature range required for throttling the thrust of the proposed device.

The proposed device operates as follows.

The device (Fig. 1) accelerates to the required supersonic flight speed by any known method, so that atmospheric air passes through a supersonic air intake (4), an annular combustion chamber (1) and leaves the device through a jet nozzle (5). The device is started by turning on the gas generator (7), which generates a high-temperature gas stream. Gases from the gas generator (7) are sent to the pyrolyzer reactor (6) filled with granular solid fuel through an expanding channel (10) connecting the gas generator (7) and the pyrolyzer reactor (6). The expanding channel (10) ensures uniform gas flow from the gas generator (7) at the inlet to the pyrolyzer reactor (6). Passing through granular solid fuel, the gases from the gas generator (7) uniformly heat the solid fuel and enter through the perforated baffle (11) first into the gas manifold (8) and then into the annular combustion chamber (1) through the belt of radial openings (9) for supplying gases into the annular combustion chamber (1), where they are mixed with air and flow from the annular combustion chamber (1) into the atmosphere through a jet nozzle (5). The perforated partition (11) is designed to separate non-condensable pyrolysis gases from the coke residue and the liquid fraction of condensed pyrolysis gases generated during the pyrolysis of granular solid fuel. The belt of radial openings (9) for supplying gases to the annular combustion chamber (1) provides a quick and uniform mixing of gases with air. The heating of granular solid fuel with gases from the gas generator (7) leads to the pyrolysis of solid fuel with the release of pyrolysis gases that enter the annular combustion chamber (1) together with the gases from the gas generator (7), mix with air and flow out of the annular combustion chamber (1) into the atmosphere through a jet nozzle (5). The gas generator (7) operates until the rate of pyrolysis gas formation reaches the value required for a particular operating mode of the pyrolysis reactor (6). The operating mode of the pyrolyzer reactor (6) is determined by the average temperature of the walls of the pyrolyzer reactor (6) and the elements of the heat exchange frame (13). Upon reaching the desired value of the rate of formation of pyrolysis gases in the pyrolysis reactor (6), the gas generator (7) is turned off and in the annular combustion chamber (1) self-sustaining detonation combustion of the mixture of pyrolysis gases with air is initiated. The initiation of detonation combustion and the detonation combustion itself is carried out in accordance with the principle set forth in patent WO 2014/129920 A1, Device for burning fuel in a continuous detonation wave, F23R 7/00 (2006.01), published on 08/28/2014 (authors Frolov S.M. , Frolov F.S.). Self-sustaining detonation combustion of a mixture of pyrolysis gases with air in the annular combustion chamber (1) is accompanied by significant heat generation and provides acceleration of the combustion products towards the jet nozzle (5) and the creation of reactive thrust, and also leads to heating of the wall (12) separating the annular combustion chamber (1) from the pyrolyzer reactor (6), which is built into the central body (2) of the device and borders on the region (A) of the annular combustion chamber (1), where heat is mainly generated in the detonation wave. Due to the fact that the temperature of the combustion products in the region (A) of the annular combustion chamber (1) significantly exceeds the average temperature of the wall (12) of the pyrolyzer reactor (6) and the elements of the heat transfer frame (13), from the annular combustion chamber (1) to the reactor the pyrolyzer (6) receives a heat flux sufficient to ensure the rate of formation of pyrolysis gases in the pyrolyzer reactor (6) required for a particular operating mode of the pyrolysis reactor (6). One or another operating mode of the pyrolysis reactor (6) corresponds to a certain flow rate of pyrolysis gases through an annular combustion chamber (1) and a certain amount of reactive thrust developed by the proposed device, i.e. changing the operating mode of the pyrolyzer reactor (6) provides throttling of the thrust of the proposed device.

To increase reactive thrust, you can use the short-term inclusion of the gas generator (7) with the supply of high-temperature gases, which will lead to an increase in the average temperature of the wall (12) of the pyrolyzer reactor (6) and elements of the heat exchange frame (13) and, therefore, to increase the rate of formation of pyrolysis gases in the pyrolyzer reactor (6) and to increase the consumption of pyrolysis gases through the annular combustion chamber (1).

To reduce reactive thrust, you can use the short-term inclusion of the gas generator (7) with the supply of low-temperature gases, which will lead to a decrease in the average wall temperature (12) of the pyrolyzer reactor (6) and elements of the heat exchange frame (13) and, therefore, to a decrease in the rate of formation of pyrolysis gases in the pyrolyzer reactor (6) and to reduce the consumption of pyrolysis gases through the annular combustion chamber (1).

We give an example implementation of the device embodiment of the invention.

In our article (Frolov SM, Aksenov VS, Ivanov VS, Shamshin IO Continuous detonation combustion of ternary "hydrogen-liquid propane-air" mixture in annular combustor. International Journal of Hydrogen Energy, 2017, Vol. 42, No.26, pp 16808-16820) presents experimental studies of the continuous detonation combustion of an air mixture of liquefied petroleum gas of the PBA-propane-butane automobile type in an annular combustion chamber with an outer wall with a diameter of 406 mm and an annular gap width of 25 mm. At a fuel and air flow rate of 0.1-0.5 kg / s and 5-12 kg / s, respectively, the detonation combustion regime with one rotating detonation wave was recorded in the experiments, i.e. The process of continuous detonation combustion was implemented.

In order to prove that automobile propane-butane can be replaced by pyrolysis gases of solid fuels, we conducted experiments to study the detonation ability of pyrolysis gases of granular secondary polypropylene. The pyrolyzer reactor was designed, manufactured and tested to produce pyrolysis gases of granular secondary polypropylene at a wall temperature of the pyrolyzer reactor from 650 to 800 ° C. It is shown that the operating mode of the pyrolyzer reactor is completely determined by the average wall temperature of the pyrolyzer reactor. Chromatographic analysis of the products showed that they mainly consist of propylene, isobutene, ethane, methane, ethylene and propane. Experiments have been carried out to study the transition of combustion to detonation in air mixtures of pyrolysis gases of polypropylene. It was shown that in mixtures with air, somewhat enriched in fuel (with an air excess coefficient of 0.73≤α≤0.90), at normal pressure and an increased initial temperature (60-90 ° C), polypropylene pyrolysis products have a detonation ability close to the detonation ability of liquefied petroleum gas of the PBA brand — automobile propane-butane — in a stoichiometric mixture with air under normal conditions: the distance and time required for the transition of combustion to detonation in such mixtures are almost the same.

Thus, the proposed method for organizing detonation combustion of pyrolysis gases of granular solid fuel in the combustion chamber of an aircraft jet engine and a device for its implementation provide pyrolysis gases with the phase and chemical composition required for self-sustaining detonation combustion, as well as reliable cooling of the structural elements of the combustion chamber.

Claims (3)

1. The method of organizing detonation combustion of pyrolysis gases in the combustion chamber of an air-jet engine, including purging the pyrolyzer reactor with gases from the gas generator, pyrolysis of solid fuel in the pyrolyzer reactor with the formation of pyrolysis gases, feeding pyrolysis gases from the pyrolysis reactor to the combustion chamber and mixing them with atmospheric air entering the combustion chamber, followed by combustion of the formed combustible mixture in the combustion chamber and the expiration of combustion products from the combustion chamber into the atmosphere in the form of reactive th jet generating jet thrust, characterized in that the solid fuel is granulated, the purge reactor-pyrolyzer with solid fuel gases from the gas generator is used only to throttle the jet thrust by transferring the reactor-pyrolyzer to a particular operating mode with the required rate of formation of pyrolysis gases, and in case of violation of one or another operating mode of the pyrolyzer reactor, for its recovery, and the required rate of pyrolysis gas formation in the pyrolyzer reactor in the operating mode is due to the heat flux into the pyrolyzer reactor from the combustion chamber in thermal contact with the pyrolysis reactor, and the mixture of pyrolysis gases with air in the combustion chamber is burned in a detonation wave, which provides a sufficient heat flux to the pyrolyzer reactor from the combustion chamber to achieve the required rate of formation of pyrolysis gases in the pyrolyzer reactor at one or another operating mode, as well as sufficient for reliable cooling of the structural elements of the combustion chamber due to the endothermic pyrolysis of the granule solid fuel.
2. A solid propellant air-jet detonation engine containing a supersonic air intake, a combustion chamber with a central body with an integrated gas generator equipped with a pyrolysis reactor, a gas manifold and a belt of radial openings for supplying gases to the combustion chamber with a central body, and a jet nozzle, characterized the fact that the pyrolyzer reactor built into the central body and installed between the gas generator and the gas collector is filled with granular solid fuel, and the pyrolyzer reactor and gas the heatsink communicate with each other through an expanding channel, and the pyrolyzer reactor and gas collector communicate through a perforated baffle, the pyrolyzer reactor being separated from the annular combustion chamber by a wall made of a material with high thermal conductivity, and borders on that region of the annular combustion chamber, where mainly, heat is generated in the detonation wave, and inside the pyrolyzer reactor there is a heat exchange frame made of a material with high thermal conductivity and in thermal contact with the wall separating the pyrolyzer reactor from the annular combustion chamber, and the granular solid fuel in the pyrolysis reactor is in thermal contact with both the wall separating the pyrolyzer reactor from the annular combustion chamber and the elements of the heat exchange frame, and the annular combustion chamber is equipped with a knock initiator.
3. The device according to p. 2, characterized in that the heat exchange frame can be made in the form of an assembly of transverse perforated disks and longitudinal rods in thermal contact with each other and with the wall separating the pyrolyzer reactor from the annular combustion chamber.
RU2019105113A 2019-02-25 2019-02-25 Air-jet detonation engine on solid fuel and method of its operation RU2706870C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2019105113A RU2706870C1 (en) 2019-02-25 2019-02-25 Air-jet detonation engine on solid fuel and method of its operation

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2019105113A RU2706870C1 (en) 2019-02-25 2019-02-25 Air-jet detonation engine on solid fuel and method of its operation

Publications (1)

Publication Number Publication Date
RU2706870C1 true RU2706870C1 (en) 2019-11-21

Family

ID=68652934

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2019105113A RU2706870C1 (en) 2019-02-25 2019-02-25 Air-jet detonation engine on solid fuel and method of its operation

Country Status (1)

Country Link
RU (1) RU2706870C1 (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2142058C1 (en) * 1997-11-18 1999-11-27 Ермишин Александр Викторович Detonation combustion pulse-jet engine
RU2157909C1 (en) * 1999-05-26 2000-10-20 Центральный институт авиационного моторостроения им. П.И. Баранова Supersonic pulse detonating ramjet engine and method of its functioning
RU2315193C1 (en) * 2006-04-14 2008-01-20 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Ramjet engine with lengthwise heat-mass distribution
RU2439358C2 (en) * 2009-11-05 2012-01-10 Открытое акционерное общество "Корпорация "Тактическое ракетное вооружение" Air ramjet engine operating on powder metal fluid
WO2014129920A1 (en) * 2013-02-19 2014-08-28 Некоммерческое Партнерство По Научной, Образовательной И Инновационной Деятельности "Центр Импульсного Детонационного Горения" Device for fuel combustion in a continuous detonation wave
RU2565131C1 (en) * 2014-07-14 2015-10-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Ramjet engine running on solid propellant and method of its operation

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2142058C1 (en) * 1997-11-18 1999-11-27 Ермишин Александр Викторович Detonation combustion pulse-jet engine
RU2157909C1 (en) * 1999-05-26 2000-10-20 Центральный институт авиационного моторостроения им. П.И. Баранова Supersonic pulse detonating ramjet engine and method of its functioning
RU2315193C1 (en) * 2006-04-14 2008-01-20 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Ramjet engine with lengthwise heat-mass distribution
RU2439358C2 (en) * 2009-11-05 2012-01-10 Открытое акционерное общество "Корпорация "Тактическое ракетное вооружение" Air ramjet engine operating on powder metal fluid
WO2014129920A1 (en) * 2013-02-19 2014-08-28 Некоммерческое Партнерство По Научной, Образовательной И Инновационной Деятельности "Центр Импульсного Детонационного Горения" Device for fuel combustion in a continuous detonation wave
RU2565131C1 (en) * 2014-07-14 2015-10-20 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" Ramjet engine running on solid propellant and method of its operation

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
W 2014/129920 A1, 28.04.2014. *

Similar Documents

Publication Publication Date Title
Lu et al. Rotating detonation wave propulsion: experimental challenges, modeling, and engine concepts
US9163584B2 (en) System, method and apparatus for lean combustion with plasma from an electrical arc
Eidelman et al. Pulsed detonation engine experimental and theoretical review
EP1445465B1 (en) Combination of core engine with ramjet engine incorporating swirl augmented combustion
US6668542B2 (en) Pulse detonation bypass engine propulsion pod
US6062018A (en) Pulse detonation electrical power generation apparatus with water injection
US1828784A (en) Pressure fluid generator
Altman et al. Overview and history of hybrid rocket propulsion
US2926613A (en) Composite rocket-ram jet fuel
US2635420A (en) Jet propulsion engine with auxiliary pulse jet engine
US7690192B2 (en) Compact, high performance swirl combustion rocket engine
US2655786A (en) Method of operating jet engines with fuel reforming
US6662550B2 (en) Method and apparatus for improving the efficiency of pulsed detonation engines
CN104632467B (en) Rocket thrust chamber provided with acoustic cavity and applied to supersonic airliner and supply system thereof
US6644015B2 (en) Turbojet with precompressor injected oxidizer
US7669406B2 (en) Compact, low pressure-drop shock-driven combustor and rocket booster, pulse detonation based supersonic propulsion system employing the same
US6983586B2 (en) Two-stage pulse detonation system
George et al. Fuel regression rate in hydroxyl-terminated-polybutadiene/gaseous-oxygen hybrid rocket motors
CA1290178C (en) Armament system
Yu et al. Investigation of kerosene combustion characteristics with pilot hydrogen in model supersonic combustors
US20100251692A1 (en) Methods of combining a series of more efficient aircraft engines into a unit, or modular units
US8539752B2 (en) Integrated deflagration-to-detonation obstacles and cooling fluid flow
US5353588A (en) Rotary valve multiple combustor pulse detonation engine
US8650856B2 (en) Fluidic deflagration-to-detonation initiation obstacles
Wang Thermophysics characterization of kerosene combustion