KR20240001832A - High performance bipropellant engine - Google Patents

Abstract

A dual propellant engine according to embodiments includes a fuel injector assembly on one side of which is provided on the propellant body and supplies fuel; a mixing chamber disposed on the other side of the fuel injector assembly, where the fuel and the oxidizer are mixed; a catalytic igniter disposed around the mixing chamber; a combustion chamber disposed on an opposite side of the mixing chamber from the propellant body; and a nozzle disposed on the opposite side of the combustion chamber from the propellant body, wherein the oxidant introduced into the catalyst igniter may be supplied to the mixing chamber after passing through the catalyst.

Description

High-performance binary propellant engine {HIGH PERFORMANCE BIPROPELLANT ENGINE}

The present invention relates to a high-performance binary propellant engine.

Hydrogen peroxide oxidizer has been widely used since the early days of rocket development. Representatively, it was used as a propellant for the gas generator of the V-2 rocket, and was also used as a propellant for the thruster attitude control system of the U.S. Mercury program.

Hydrogen peroxide is split into oxygen and water molecules by a catalyst and releases heat. Due to this exothermic reaction, oxygen gas and water vapor can be generated at about 1000 K in the case of 90 wt.% hydrogen peroxide. Using this property, it can be used as a propellant for a single propellant thruster. Alternatively, ignition can be caused by spraying kerosene or an ignitable substance into the high-temperature oxygen and water vapor mixed gas, which is a decomposition product of hydrogen peroxide. The combustion product produced in this way can be a gas of much higher temperature than the existing decomposition product of hydrogen peroxide. Additional performance improvements can be expected. An engine that injects a substance such as hydrogen peroxide, which acts as an oxidizing agent, and a substance that acts as a fuel, are called dual-propellant engines.

For example, the advantages of hydrogen peroxide binary propellant engines are: Hydrogen peroxide exists as a liquid at room temperature, so it does not need to be handled in cryogenic environments like liquid oxygen, and it can be stored for a relatively long time stored in a propellant tank. Additionally, due to the low toxicity of hydrogen peroxide, less protective equipment is required when handling it compared to hydrazine. It has a density 1.4 times higher than that of water, allowing the propellant tank to be designed with a smaller volume. The decomposition product of hydrogen peroxide is a high-temperature mixed gas of oxygen and water vapor, so it can be used as a variety of fuels. If the fuel is chosen well, it is environmentally friendly because the only emissions are water and carbon dioxide.

Several studies on binary propellant engines are being conducted using the characteristics of oxidizing agents such as hydrogen peroxide.

U.S. Registration No. 2010-0252686 A1 discloses a method and device enabling a rocket engine pump to be driven by an internal combustion engine.

The above-mentioned background technology is possessed or acquired by the inventor in the process of deriving the disclosure of the present application, and cannot necessarily be said to be known technology disclosed to the general public before the present application.

The purpose of one embodiment is to provide a dual propellant engine that can achieve high performance while dramatically reducing the pressure drop inside the catalytic igniter of the dual propellant engine.

The purpose of one embodiment is to provide a dual propellant engine that can simultaneously improve the performance and durability of a catalytic igniter that decomposes an oxidizing agent.

The purpose of one embodiment is to provide a dual propellant engine that can significantly increase the area perpendicular to the flow direction of the catalytic igniter, secure the necessary internal volume of the catalytic igniter, and lower the pressure drop inside the catalytic igniter.

A dual propellant engine according to embodiments includes a fuel injector assembly on one side of which is provided on the propellant body and supplies fuel; a mixing chamber disposed on the other side of the fuel injector assembly, where the fuel and the oxidizer are mixed; a catalytic igniter disposed around the mixing chamber; a combustion chamber disposed on an opposite side of the mixing chamber from the propellant body; and a nozzle disposed on the opposite side of the combustion chamber from the propellant body, wherein the oxidant introduced into the catalyst igniter may be supplied to the mixing chamber after passing through the catalyst.

According to one side, the catalytic igniter includes a housing provided in an annular shape; and a catalyst provided inside the housing to decompose the supplied oxidant, wherein the inside of the housing surrounds the mixing chamber, and the oxidizing agent that has passed through the catalyst passes through the inside of the housing and flows into the mixing chamber. It can be.

According to one side, the catalytic igniter may further include a membrane cooling unit and an oxidizing agent injector unit, wherein the membrane cooling unit includes an inner inlet provided on one side of the housing adjacent to the propellant body and into which an oxidizing agent is injected; and an inner flow path provided along the inside of the housing, through which some or all of the oxidizing agent flows from the inner inlet. The inner flow path may cool the inside of the housing.

According to one side, the film cooling unit may further include a liquid film forming part connected to an end of the inner passage and spraying a portion of the oxidant to a portion of the combustion chamber, and through the liquid film forming part, the combustion chamber. A liquid film may be formed on part of the liquid film, and the combustion chamber may be cooled through the liquid film.

According to one side, the oxidizing agent injector unit includes an outer flow path connected to an end of the inner flow path to guide another part of the oxidizing agent to the outside of the housing; and an external injector that sprays some of the oxidant introduced from the external passage onto the catalyst, wherein the oxidant reacts with the catalyst and decomposes through the external injector, and the decomposition product flows into the mixing chamber. You can.

According to one side, the catalytic igniter may further include a regenerative cooling unit, wherein the regenerative cooling unit includes an external inlet provided outside the combustion chamber and injecting an oxidizing agent; and a regenerative cooling passage extending from the outer inlet to the catalytic igniter along a portion of the combustion chamber, wherein the regenerative cooling passage passes a portion of the oxidant introduced from the outer inlet to the combustion chamber and the nozzle. Part or all of it can be cooled.

According to one side, the catalytic igniter may further include a film cooling unit, and the film cooling unit is provided between the combustion chamber and the housing, and is connected to an end of the regenerative cooling passage to inject a portion of the oxidant into a portion of the combustion chamber. It may further include a liquid film forming unit, and a liquid film can be formed on a part of the combustion chamber through the liquid film forming unit, and the combustion chamber can be additionally cooled through the liquid film. According to one side, the regeneration The cooling passage may extend along the inside of the housing and cool the inside of the housing.

According to one side, the regenerative cooling unit includes: a distribution passage provided inside the housing and connected to the regenerative cooling passage to guide another part of the oxidizing agent to the outside of the housing; and an injector that injects some of the oxidant introduced from the distribution passage onto the catalyst, wherein the oxidant reacts with the catalyst and decomposes through the injector, and the decomposition product may flow into the mixing chamber. .

According to one side, the distribution passage may include a primary distribution passage connected to an end of the regenerative cooling passage to guide another portion of the oxidant to the outside of the housing.

According to one side, the distribution passage may further include a secondary distribution passage that guides the oxidant from the primary distribution passage to the injector and distributes it evenly.

The dual propellant engine according to one embodiment can achieve high performance while dramatically reducing the pressure drop inside the catalytic igniter of the oxidizer and dye dual propellant engine.

The dual propellant engine according to one embodiment can simultaneously pursue improvements in the performance and durability of the catalytic igniter that decomposes the oxidizer.

The dual propellant engine according to one embodiment can significantly increase the area perpendicular to the flow direction of the catalytic igniter, secure the necessary internal volume of the catalytic igniter, and lower the pressure drop inside the catalytic igniter.

Figure 1 shows an exploded view of a binary propellant engine according to the first embodiment.
Figure 2 shows a cross-sectional view of a binary propellant engine according to the first embodiment.
Figure 3 shows a cross-sectional view of a fuel injector assembly of a binary propellant engine according to the first embodiment.
Figure 4 shows a cross-sectional view of a catalytic igniter of a binary propellant engine according to the first embodiment.
Figure 5 shows a cross-sectional view of the combustion chamber and nozzle of the binary propellant engine according to the first embodiment.
Figure 6 shows an exploded view of the binary propellant engine according to the second embodiment.
Figure 7 shows a cross-sectional view of a binary propellant engine according to the second embodiment.
Figure 8 shows a cross-sectional view of a fuel injector assembly of a binary propellant engine according to a second embodiment.
Figure 9 shows a cross-sectional view of a catalytic igniter of a binary propellant engine according to a second embodiment.
Figure 10 shows a cross-sectional view of the combustion chamber and nozzle of the binary propellant engine according to the second embodiment.

Hereinafter, embodiments will be described in detail with reference to the attached drawings. However, since various changes can be made to the embodiments, the scope of the patent application is not limited or limited by these embodiments. It should be understood that all changes, equivalents, or substitutes for the embodiments are included in the scope of rights.

The terms used in the examples are for descriptive purposes only and should not be construed as limiting. Singular expressions include plural expressions unless the context clearly dictates otherwise. In this specification, terms such as “comprise” or “have” are intended to designate the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, but are not intended to indicate the presence of one or more other features. It should be understood that this does not exclude in advance the possibility of the existence or addition of elements, numbers, steps, operations, components, parts, or combinations thereof.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as generally understood by a person of ordinary skill in the technical field to which the embodiments belong. Terms defined in commonly used dictionaries should be interpreted as having a meaning consistent with the meaning in the context of the related technology, and unless explicitly defined in the present application, should not be interpreted in an ideal or excessively formal sense. No.

In addition, when describing with reference to the accompanying drawings, identical components will be assigned the same reference numerals regardless of the reference numerals, and overlapping descriptions thereof will be omitted. In describing the embodiments, if it is determined that detailed descriptions of related known technologies may unnecessarily obscure the gist of the embodiments, the detailed descriptions are omitted.

Additionally, in describing the components of the embodiment, terms such as first, second, A, B, (a), and (b) may be used. These terms are only used to distinguish the component from other components, and the nature, sequence, or order of the component is not limited by the term. When a component is described as being "connected," "coupled," or "connected" to another component, that component may be directly connected or connected to that other component, but there is no need for another component between each component. It should be understood that may be “connected,” “combined,” or “connected.”

Components included in one embodiment and components including common functions will be described using the same names in other embodiments. Unless stated to the contrary, the description given in one embodiment may be applied to other embodiments, and detailed description will be omitted to the extent of overlap.

Below, with reference to the attached drawings, embodiments of the present invention will be described in detail so that those skilled in the art can easily implement the present invention. However, the present invention may be implemented in many different forms and is not limited to the embodiments described herein. In order to clearly explain the present invention in the drawings, parts unrelated to the description are omitted.

The dual propellant engines 10 and 20 according to embodiments may be composed of an oxidizer and a fuel dual propellant engine. For example, the oxidizer may be hydrogen peroxide, a mixture containing hydrogen peroxide, or nitrous oxide. Depending on the cooling method of the combustion chamber and the catalytic igniter, it is divided into a first embodiment and a second embodiment and will be described later. At this time, embodiments that can be realized are not limited to these described embodiments. Hereinafter, the dual propellant engines 10 and 20 according to embodiments will be described in detail with reference to the drawings.

Figure 1 shows an exploded view of the binary propellant engine 10 according to the first embodiment. Figure 2 shows a cross-sectional view of a binary propellant engine 10 according to the first embodiment. Figure 3 shows a cross-sectional view of the fuel injector assembly 1100 of the binary propellant engine 10 according to the first embodiment. Figure 4 shows a cross-sectional view of the catalytic igniter 1200 of the binary propellant engine 10 according to the first embodiment. Figure 5 shows a cross-sectional view of the combustion chamber 1400 and the nozzle 1500 of the binary propellant engine 10 according to the first embodiment.

Referring to FIG. 1, the binary propellant engine 10 according to the first embodiment has a fuel injector assembly 1100 on one side provided on the propellant body and supplies fuel, and a fuel injector assembly 1100 on the other side of the fuel injector assembly 1100. A mixing chamber 1300 in which fuel and oxidizer are mixed, a catalytic igniter 1200 disposed around the mixing chamber 1300, a combustion chamber 1400 disposed on the opposite side of the mixing chamber 1300 from the propellant body, and a propellant body. It may include a nozzle 1500 disposed on the opposite side of the combustion chamber 1400.

Referring to FIG. 3, the fuel injector assembly 1100 of the binary propellant engine 10 according to the first embodiment includes a fuel inlet 1110 for injecting fuel, and a fuel injector 1120 for injecting the injected fuel into the combustion chamber. ) may include.

Referring to FIGS. 2 and 4, the catalytic igniter 1200 of the binary propellant engine 10 according to the first embodiment includes a housing 1210 provided in an annular shape, and provided inside the housing 1210, It may include a catalyst 1220 that decomposes the supplied oxidant. The catalyst 1220 can decompose the supplied oxidant, for example, hydrogen peroxide, and the inside of the housing 12110 can serve to fix the catalyst and prevent it from leaking. The oxidizing agent introduced into the catalytic igniter 1200 may pass through the catalyst 1220 and then be supplied to the mixing chamber 1300. More specifically, the inside of the housing 1211 surrounds the mixing chamber 1300, and the catalyst 1220 ) may pass through the inside of the housing (1211) and flow into the mixing chamber (1300).

The catalytic igniter 1200 of the binary propellant engine 10 according to the first embodiment may include a membrane cooling unit 1230 and an oxidant injector unit 1240, and the membrane cooling unit 1230 is located in a housing adjacent to the propellant body. An inner inlet 1231 provided on one side of 1210 and into which the oxidizing agent is injected, and an inner flow path 1232 provided along the inner side of the housing 1211 through which some or all of the oxidizing agent flows from the inner inlet 1231. It is connected to the end of the flow path 1232 and leads to a liquid film forming portion 1233 that injects some of the oxidant into a portion of the combustion chamber 1400. The oxidant injector unit 1240 is connected to the end of the inner flow path 1232, and the outer flow path 1241 guides another part of the oxidant to the outside of the housing 1210, and catalyzes some of the oxidant introduced from the outer flow path 1241. It may include an external sprayer 1242 that sprays on 1220.

Some or all of the oxidizing agent injected into the inner injection port 1231 may be distributed to the inner passage 1232, and the inner passage 1232 may cool the inside of the housing 1211 through the injected oxidizing agent. Through this, the inner flow path 1231 can reduce the thermal load generated due to the flame inside the catalytic igniter 1200.

The liquid film forming unit 1233 can cool the combustion chamber 1400 by using some of the oxidizing agent that has escaped the inner flow passage 1231. A liquid film is formed on a portion of the combustion chamber 1400 through the liquid film forming unit 1233, and the combustion chamber 1400 can be cooled through the liquid film.

The oxidizing agent not used for film cooling is uniformly distributed to the external injector 1242 through the external flow path 1241, and the external injector 1242 can inject the oxidizing agent on the catalyst 1220. Through this, the oxidant reacts with the catalyst 1220 and is decomposed, and the decomposition products can flow into the mixing chamber 1300.

Combustion and decomposition products of the oxidizer are mixed in the mixing chamber 1300, and then the oxidizer and fuel are burned in the combustion chamber 1400, so that the combustion products can be accelerated to supersonic speed in the nozzle 1500.

Hereinafter, the operating principle of the binary propellant engine 10 according to the first embodiment will be described in detail.

Referring to Figures 2 and 3, the binary propellant engine 10 according to the first embodiment can receive fuel injected from the outside through the fuel injection port 1110. The fuel injector 1120 may inject fuel supplied through the fuel injection port 1110 into the mixing chamber 1300.

Referring to Figures 2 and 4, the operating principles of the film cooling unit 1230 and the oxidizing agent injector unit 1240 of the catalytic igniter 1200 are as follows. The oxidizing agent may be supplied from the outside through the inner inlet 1231. The inner inlet 1231 can be machined to fit the size of inch or metric pipe.

The oxidizing agent supplied from the inner inlet 1231 can be uniformly distributed in the inner flow path 1232 located inside the housing 1211. The inner passage 1232 may have a ring shape surrounding the inner side of the housing 1211, and its cross-section may be polygonal or circular.

The reason why the inner flow passage 1232 must exist is as follows. In the space at the central axis of the catalytic igniter 1200, for example, hydrogen peroxide decomposition products and fuel injected from the fuel injector 1120 may meet to cause a combustion reaction. At this time, since a high temperature flame of 2500 K or more is generated, the inside of the housing 1211 must not only prevent loss of the catalyst 1220 but also be able to withstand high temperature flames. Therefore, the inside of the housing 1211 can be cooled using the oxidizing agent flowing in the inside flow path 1232, and through this, the robustness of the inside of the housing 1211 can be maintained.

Some of the oxidant exiting the inner passage 1232 may be injected along the wall of the combustion chamber 1400 through the liquid film forming portion 1233. Combustion products of oxidizer and fuel may pass through the combustion chamber 1400. This combustion product is a high-temperature gas mixture, and in order to prevent problems that may damage the wall of the combustion chamber 1400, a portion of the oxidant flow rate is sprayed along the wall of the combustion chamber 1400 through the liquid film forming portion 1233, A kind of liquid film may form. This liquid film can protect the wall of the combustion chamber 1400 by absorbing and evaporating the high heat of combustion products.

The liquid film forming unit 1233 can spray the coolant or oxidant onto the wall of the combustion chamber 1400 as uniformly and thinly as possible. The liquid film forming portion 1233 may be composed of multiple orifices with the same diameter. Alternatively, the liquid film forming unit 1233 may spray an oxidizing agent in the form of a sheet to form a liquid film on the wall of the combustion chamber 1400. The liquid film forming unit 1233 may or may not be included in the catalytic igniter 1200.

The outer flow path 1241 of the oxidant injector unit 1240 can supply hydrogen peroxide that is not injected from the liquid film forming unit 1233 to the external injector 1242 as uniformly as possible. The outer flow path 1241 may be in the form of a ring or may be multiple flow paths leading to the orifice of the individual outer sprayer 1242.

The external injector 1242 can uniformly inject the oxidizing agent to the catalyst 1220, and for this purpose, it can be configured as a showerhead type injector by processing a number of mutually symmetrical orifices.

Referring to Figures 2 and 5, the operating principles of the combustion chamber 1400 and the nozzle 1500 are as follows. The fuel and oxidizer supplied from the fuel injector assembly 1100 and the catalytic igniter 1200 may meet in the combustion chamber 1400 to cause a combustion reaction. For sufficient combustion, the combustion chamber 1400 may be designed with sufficient volume and length. Combustion products supplied from the combustion chamber 1400 may be accelerated to supersonic speed in the nozzle 1500. Thrust can be generated by spraying this accelerated gas. The principle and shape of the nozzle 1500 may follow general compressible fluid dynamics and are not limited as described in the drawings.

Figure 6 shows an exploded view of the dual propellant engine 20 according to the second embodiment. Figure 7 shows a cross-sectional view of the binary propellant engine 20 according to the second embodiment. Figure 8 shows a cross-sectional view of the fuel injector assembly 2100 of the binary propellant engine 20 according to the second embodiment. Figure 9 shows a cross-sectional view of the catalytic igniter 2200 of the binary propellant engine 20 according to the second embodiment. Figure 10 shows a cross-sectional view of the combustion chamber 2400 and the nozzle 2500 of the binary propellant engine 20 according to the second embodiment.

Referring to FIG. 6, the binary propellant engine 20 according to the second embodiment includes a fuel injector assembly 2100, a mixing chamber 2300, a catalytic igniter 2200, a combustion chamber 2400, and a nozzle 2500. It can be included. Referring to FIG. 7, the fuel injector assembly 2100 of the binary propellant engine 20 according to the second embodiment may include a fuel inlet 2110 and a fuel injector 2120. Referring to FIGS. 7 and 9 , the catalytic igniter 2200 of the binary propellant engine 20 according to the second embodiment may include a housing 2210 and a catalyst 2220.

The catalytic igniter 2200 of the binary propellant engine 20 according to the second embodiment may include a regenerative cooling unit 2230. The regenerative cooling unit 2230 is provided outside the combustion chamber 2400 and has an outer inlet 2231 for injecting an oxidizing agent, and a regenerative cooling unit extending from the outer inlet 2231 along a part of the combustion chamber 2400 to the catalytic igniter 2200. May include Euros (2232).

The regenerative cooling passage 2232 can cool part or all of the combustion chamber 2400 and the nozzle 2500 through part or all of the oxidant introduced from the external inlet 2231. Additionally, the regenerative cooling passage 2232 may extend along the inside of the housing 2211 and cool the inside of the housing 2211.

The regenerative cooling unit 2230 is provided inside the housing 2210 and is connected to the regenerative cooling passage 2232, and includes distribution passages 2233 and 2234 that guide some or all of the oxidant to the outside of the housing. , It may further include an injector 2235 that injects some or all of the oxidant introduced from 2234) onto the catalyst 2220.

The oxidant reacts with the catalyst 2220 and is decomposed through the injector 2235, and the decomposition product may flow into the mixing chamber 2300.

The distribution passages 2233 and 2234 are connected to the end of the regenerative cooling passage 2232 and lead another part of the oxidant to the outside of the housing 2210, and the primary distribution passage 2233 It may include a secondary distribution passage 2234 that guides the oxidant from the injector 2235 and distributes it evenly.

Hereinafter, the operating principle of the binary propellant engine 20 according to the second embodiment will be described in detail.

7 and 8, the operating principle of the fuel injector assembly 2100 is as follows. Fuel injected into the fuel injection port 2110 may be supplied to the fuel injector 2120. The fuel injector 2120 may inject the fuel supplied from the fuel inlet 2110 into the catalytic igniter 2200 and the mixing chamber 2300.

Referring to Figures 7 and 9, the operating principle of the catalytic igniter 2200 is as follows. The oxidizing agent may be injected from the outside of the combustion chamber 2400, for example, through an external injection port 2231 provided on the nozzle 2500. The outer inlet 2231 can be provided to match the size of inch or metric pipe. The injected oxidant may be supplied to the catalytic igniter 2200 through a regenerative cooling oil duct 2232 extending from the outer injection port 2231 and formed on the combustion chamber 2400 side.

The regenerative cooling passage 2232 formed on the side of the catalytic igniter 2200 may be formed by extending from the regenerative cooling flow path 2232 formed on the side of the combustion chamber 2400, and may be formed in the central axis space of the catalytic igniter 2230, for example, mixing. It may serve to protect the inside of the housing 2211 from the high temperature of the flame generated in the seal 2300. In the central axis space of the catalytic igniter 2200, combustion may occur when fuel and decomposition products of an oxidant, such as hydrogen peroxide, meet. At this time, since a high temperature flame of, for example, 2500 K or more is generated, the inside of the housing 2211 needs to be cooled. In order to perform cooling, the regenerative cooling passage 2232 formed on the catalytic igniter 2200 side can cool the inside of the housing 2211 by receiving an oxidizing agent from the regenerative cooling oil passage 2232 formed on the combustion chamber 2400 side. there is. Afterwards, the oxidizing agent may be delivered to the primary distribution passage 2233. The cross-section of the regenerative cooling passage 2232 formed on the side of the combustion chamber 2400 and the catalytic igniter 2200 may be circular or polygonal.

The role of the primary distribution passage 2233 is to uniformly distribute the oxidant supplied from the regenerative cooling passage 2232 formed on the catalytic igniter 2200 side to the secondary distribution passage 2234. The primary distribution passage 2233 may have a ring shape surrounding the inside of the housing 2211.

The secondary distribution passage 2234 can uniformly distribute the oxidant supplied from the primary distribution passage 2233 to the injector 2235. The secondary distribution passage 2234 may be ring-shaped or may be an individual passage leading to the injector 2235.

The injector 2235 can uniformly inject an oxidizing agent, such as hydrogen peroxide, into the catalyst 2220. For this purpose, a plurality of mutually symmetrical orifices may be processed to provide a showerhead type injector.

Referring to Figures 7 and 10, regenerative cooling may be performed on the combustion chamber 2400 and the nozzle 2500 to protect them from the high temperature of combustion products. The regenerative cooling passage 2232 formed on the combustion chamber 2400 side can cool the combustion chamber 2400 and the nozzle 2500 using the oxidizing agent supplied from the external inlet 2231. The regenerative cooling passage 2232 on the combustion chamber 2400 side may be composed of multiple passages, and its cross section may be circular or polygonal.

The binary propellant engine (not shown) according to the third embodiment can simultaneously perform film cooling and regenerative cooling. The binary propellant engine according to the third embodiment may include a fuel injector assembly, a mixing chamber, a catalytic igniter, a combustion chamber, and a nozzle, and the catalytic igniter may include a housing and a catalyst.

The catalytic ignitor of the dual propellant engine according to the third embodiment may further include a film cooling injector unit, an oxidant injector unit, and a regenerative cooling unit.

The regenerative cooling unit includes an outer inlet provided outside the combustion chamber and injecting the oxidizing agent, a regenerative cooling passage extending from the outer inlet to the catalytic igniter along part or all of the combustion chamber, and a regenerative cooling passage provided inside the housing and connected to the regenerative cooling passage to inject the oxidizing agent. A film cooling unit that injects another portion into a portion of the combustion chamber, a distribution passage provided inside the housing and connected to the regenerative cooling passage to guide some of the oxidant to the outside of the housing, and a portion of the oxidant flowing in from the distribution passage or the distribution passage. An injector that injects all of the oxidant onto the catalyst, a primary distribution channel that is connected to the end of the regenerative cooling channel and guides another part of the oxidant to the outside of the housing, and an injector that guides the oxidant from the primary distribution channel to the injector and distributes it evenly. , may include a secondary distribution channel. The regenerative cooling passage can cool part or all of the combustion chamber and nozzle through some or all of the oxidant introduced from the external inlet, and the regenerative cooling passage extends along the inside of the housing and can cool the inside of the housing. Through the injector, the oxidant reacts with the catalyst and is decomposed, and the decomposition products may flow into the mixing chamber.

The fuel inlets 1110 and 2110 of the dual propellant engines 10 and 20 according to embodiments may be provided to match the size of inch or metric pipes. The fuel injectors 1120 and 2120 may inject fuel into the mixing chambers 1300 and 2300 so that the fuel can be mixed with the oxidant decomposition products. The fuel injectors 1120 and 2120 may be in the form of a shower head, coaxial or impingement type, spray type, pintle injector, etc. to uniformly inject fuel. Fuel that can be used in the dual propellant engines 10 and 20 according to embodiments may be a hydrocarbon liquid or gas or a hydrocarbon mixture.

A catalyst (1220, 2220) may be filled inside the catalytic igniter (1200, 2200). The catalysts 1220 and 2220 may be devices that decompose an oxidizing agent, such as hydrogen peroxide, into high-temperature oxygen and water vapor. The catalyst 1220 may be provided by applying a catalytically active material that reacts violently with an oxidizing agent to a catalyst support that reacts or does not react with an oxidizing agent. At this time, the catalyst support may or may not be the same material as the catalytically active material. The catalyst 1220 may be in the form of pellets, grains, metal sheets, metal foams, or monoliths.

The inside of the housing (1211, 2211) can fix the catalysts (1220, 2220) so that they are not lost by the flow of high-temperature oxygen and water vapor mixed gas, which is a decomposition product of oxidizing agent, for example, hydrogen peroxide. . The surface of the housing interior (1211, 2211) may have a structure that allows oxidizing agent decomposition products to pass through. This structure may be a large number of circular holes, polygonal holes, or a radial structure, or it may be a lattice structure.

The dual propellant engines (10, 20) according to the embodiments can simultaneously pursue improvements in the performance and durability of the catalytic ignitors (1200, 2200) that decompose the oxidizing agent by using the annular-shaped catalytic ignitors (1200, 2200). . By arranging the catalytic igniter (1200, 2200) in an annular shape, the area perpendicular to the flow direction of the catalytic igniter (1200, 2200) can be significantly increased. Since the mass flow, which is the mass flowing per unit area, and the pressure drop inside the catalytic igniter are proportional, in order to maintain a high oxidant decomposition rate through the binary propellant engine (10, 20) according to the embodiments, the necessary catalytic igniter (1200, 2200) ) As the internal volume is secured, the pressure drop inside the catalytic igniter (1200, 2200) can be lowered. Through this, the problem of low durability due to high pressure drop inside the catalytic igniter (1200, 2200) can be solved.

Binary propellant rockets using hydrogen peroxide can be divided into those in which a catalytic ignitor is used and those in which it is not used. When a catalytic igniter is used, there is no contact ignition property that ignites when hydrogen peroxide and fuel come into contact. When a catalytic igniter is not used, there is a case where the fuel used is a contact ignition type fuel that ignites when it comes into contact with hydrogen peroxide. This is the case.

When a catalytic igniter is used, most or all of the supplied hydrogen peroxide flow rate may be input into the catalytic igniter, and only a portion of the supplied hydrogen peroxide may be input into the catalytic igniter. When most or all of the hydrogen peroxide is input into the catalytic igniter, ignition of the fuel is rapid and certain because the composition of the oxidant that meets the fuel is a high-temperature oxygen and water vapor mixed gas, which is a decomposition product of hydrogen peroxide. However, since the hydrogen peroxide flow rate that the catalytic igniter must handle is large, it is necessary to ensure the durability of the catalytic igniter. If only a partial flow rate of hydrogen peroxide is input to the catalytic igniter, there is a high possibility that there will be no problem with the life of the catalytic igniter because the flow rate flowing to the catalytic igniter is small. However, since liquid hydrogen peroxide and fuel meet inside the combustion chamber, the ignition sequence must be designed well. Only then can reliable ignition be performed.

Inside the catalytic igniter, the catalyst and hydrogen peroxide come into contact, and hydrogen peroxide decomposes into water and oxygen. At this time, when 90 wt.% hydrogen peroxide is used, the adiabatic decomposition temperature is about 1000 K, and when 95 wt.% is used, it is about 1100 K. When the decomposition of the introduced hydrogen peroxide is completed, the gas inside the hydrogen peroxide injector becomes a mixture of high temperature oxygen and water vapor of over 1000 K. When these gases flow between catalysts, a high pressure drop occurs. This pressure drop generates a large compressive load on the catalyst filled in the catalytic igniter and destroys the catalyst. If the binary propellant thruster is operated continuously and repeatedly, the amount of catalyst damaged increases due to the pressure drop inside the catalytic igniter. As the number of damaged catalysts increases, the performance of the catalytic igniter decreases, and if the amount of catalyst damage exceeds a critical point, the flow resistance becomes very large and the flow of hydrogen peroxide may stop. In this case, the catalytic igniter itself may not do its job.

The pressure drop that occurs inside the catalytic igniter is caused by several factors. Among them, the factors resulting from the shape of the catalytic igniter are the mass flux and the length of the catalytic igniter. The relationship between the internal pressure drop and mass of the catalytic igniter and the length of the catalytic igniter is as follows.

(ΔP is pressure drop, G is mass flux, L is catalytic igniter length)

Therefore, in order to reduce the pressure drop of the catalytic igniter, the mass flux must be reduced or the length of the catalytic igniter must be reduced. The dual propellant engines 10 and 20 according to the embodiments can be secured with a significantly increased area perpendicular to the flow direction of the catalytic igniters 1200 and 2200 by applying annular-shaped catalytic igniters 1200 and 2200. As a result, the mass flux can be significantly reduced compared to the constant volume of the catalytic igniter (1200, 2200), and the pressure drop inside the catalytic igniter (1200, 2200) can be significantly reduced. In addition, as the mass flux is reduced, the increased length of the catalytic igniter (1200, 2200) can be secured, and the charging volume of the catalyst (1220, 2220) can be increased, so that the performance of decomposing oxidizing agents, such as hydrogen peroxide, can also be sufficiently secured.

Through the dual propellant engines 10 and 20 according to the embodiments, an engine type that can achieve high performance while dramatically reducing the pressure drop inside the catalytic igniter of an oxidizing dual propellant engine such as hydrogen peroxide can be proposed.

Through the binary propellant engine (10, 20) according to the embodiments, a cooling method that can be used with the annular-shaped catalytic igniter (1200, 2200) can also be proposed.

Through the dual propellant engines 10 and 20 according to the embodiments, the problem of not ensuring the long life of the catalytic igniter because the pressure drop within the catalytic igniter 1200 and 2200 is very large, such as about 10 bar, can be prevented.

Through the dual propellant engines 10 and 20 according to the embodiments, the performance of the catalytic igniters 1200 and 2200 is also reduced due to change in the catalyst to lower the pressure drop of the catalytic igniters 1200 and 2200, and thus the dual propellant engine 10 and 20 The problem of reduced performance of the propellant engine itself can be prevented.

Although the embodiments have been described with limited drawings as described above, those skilled in the art can apply various technical modifications and variations based on the above. For example, the described techniques are performed in a different order than the described method, and/or components of the described system, structure, device, circuit, etc. are combined or combined in a different form than the described method, or other components are used. Alternatively, appropriate results may be achieved even if substituted or substituted by an equivalent.

Therefore, other implementations, other embodiments, and equivalents of the claims also fall within the scope of the following claims.

10: Bipropellant engine according to the first embodiment
1100: Fuel injector assembly
1110: fuel inlet
1120: fuel injector
1200: Catalytic igniter
1210: housing
1211: Inside housing
1220: catalyst
1230: Membrane cooling unit
1231: Inner injection port
1232: Internal flow passage
1233: Liquid film forming part
1240: Oxidizing agent spray unit
1241: External flow path
1242: Outward sprayer
1300: Mixing room
1400: combustion chamber
1500: nozzle
20: Bipropellant engine according to the second embodiment
2100: Fuel injector assembly
2110: fuel inlet
2120: fuel injector
2200: Catalytic Igniter
2210: housing
2211: Inside housing
2220: catalyst
2230: Regenerative cooling unit
2231: External inlet
2232: Regenerative cooling channel
2233: 1st distribution channel
2234: 2nd distribution channel
2235: sprayer
2300: Mixing room
2400: combustion chamber
2500: nozzle

Claims (11)

A fuel injector assembly on one side provided on the propellant body and supplying fuel;
a mixing chamber disposed on the other side of the fuel injector assembly, where the fuel and oxidizer are mixed;
a catalytic igniter disposed around the mixing chamber;
a combustion chamber disposed on an opposite side of the mixing chamber from the propellant body; and
a nozzle disposed on an opposite side of the combustion chamber from the propellant body;
Including,
The oxidant introduced into the catalyst igniter passes through the catalyst and is then supplied to the mixing chamber.
Bipropellant engine.
According to paragraph 1,
The catalytic igniter,
A housing provided in an annular shape; and
a catalyst provided inside the housing and decomposing the supplied oxidant;
Including,
The inside of the housing surrounds the mixing chamber, and the oxidizing agent that has passed through the catalyst passes through the inside of the housing and flows into the mixing chamber.
Bipropellant engine.
According to paragraph 2,
The catalytic igniter further includes a film cooling unit,
The membrane cooling unit,
an inner inlet provided on one side of the housing adjacent to the propellant body, into which an oxidizing agent is injected; and
an inner flow path provided along the inside of the housing, through which some or all of the oxidizing agent flows from the inner inlet;
Including,
The inner flow path cools the inside of the housing,
Bipropellant engine.
According to paragraph 3,
The membrane cooling unit,
a liquid film forming portion connected to an end of the inner flow path to spray a portion of the oxidant into a portion of the combustion chamber;
It further includes,
A liquid film is formed on a part of the combustion chamber through the liquid film forming unit, and the combustion chamber is cooled through the liquid film.
Bipropellant engine.
According to clause 3,
The catalytic igniter further includes an oxidant injector unit, the oxidant injector unit,
an outer passage connected to an end of the inner passage to guide another portion of the oxidizing agent to the outside of the housing; and
an external injector that injects some of the oxidant introduced from the external passage onto the catalyst;
It further includes,
Through the external injector, the oxidant reacts with the catalyst and is decomposed, and the decomposition product flows into the mixing chamber.
Bipropellant engine.
According to paragraph 2,
The catalytic igniter further includes a regenerative cooling unit,
The regenerative cooling unit,
An outer injection port provided outside the combustion chamber and injecting an oxidizing agent; and
a regenerative cooling flow path extending from the outer inlet to the catalytic igniter along part or all of the combustion chamber;
Including,
The regenerative cooling passage cools part or all of the combustion chamber and the nozzle through some or all of the oxidant introduced from the external inlet,
Bipropellant engine.
According to clause 6,
The regenerative cooling passage extends along the inside of the housing and cools the inside of the housing.
Bipropellant engine.
According to clause 6,
The regenerative cooling unit,
a distribution passage provided inside the housing and connected to the regenerative cooling passage to guide some or all of the oxidizing agent to the outside of the housing; and
an injector that injects some or all of the oxidant introduced from the distribution passage onto the catalyst;
It further includes,
Through the injector, the oxidant reacts with the catalyst and is decomposed, and the decomposition product flows into the mixing chamber.
Bipropellant engine.
According to clause 8,
The distribution flow path is,
a primary distribution passage connected to an end of the regenerative cooling passage to guide another portion of the oxidant to the outside of the housing;
Including,
Bipropellant engine.
According to clause 9,
The distribution flow path is,
a secondary distribution channel that guides the oxidant from the primary distribution channel to the sprayer and distributes it evenly;
Including,
Bipropellant engine.
According to paragraph 2,
The catalytic igniter further includes a regenerative cooling unit,
The regenerative cooling unit,
An outer injection port provided outside the combustion chamber and injecting an oxidizing agent; and
a regenerative cooling flow path extending from the outer inlet to the catalytic igniter along part or all of the combustion chamber;
Including,
The catalytic igniter further includes a film cooling unit,
The membrane cooling unit,
a liquid film forming portion provided on one side of the housing adjacent to the propellant body and connected to an end of the regenerative cooling passage to spray another portion of the oxidant into a portion of the combustion chamber;
Including,
The catalytic igniter,
a distribution passage provided inside the housing and connected to the regenerative cooling passage to guide some or all of the oxidizing agent to the outside of the housing;
an injector that injects some or all of the oxidant introduced from the distribution passage onto the catalyst;
a primary distribution passage connected to an end of the regenerative cooling passage to guide another portion of the oxidant to the outside of the housing; and
a secondary distribution channel that guides the oxidant from the primary distribution channel to the sprayer and distributes it evenly;
It further includes,
The regenerative cooling passage cools part or all of the combustion chamber and the nozzle through some or all of the oxidant introduced from the external inlet,
The regenerative cooling passage extends along the inside of the housing and cools the inside of the housing,
Through the injector, the oxidant reacts with the catalyst and is decomposed, and the decomposition product flows into the mixing chamber,
A liquid film is formed on a part of the combustion chamber through the liquid film forming unit, and the combustion chamber is cooled through the liquid film.
Bipropellant engine.

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