JP2015040489A - Two-stage combustion two-component thruster - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a two-stage combustion two-component thruster capable of reducing the size of a combustion chamber and improving combustion efficiency.SOLUTION: In a sub combustion chamber 7, liquid fuel and liquid oxidizer are supplied, and a part of the fuel is converted to primary combustion gas whereas a remainder of the liquid fuel is converted to unreacted fuel gas. In a main combustion chamber 11, the unreacted fuel gas is supplied from the sub combustion chamber 7, gas oxidizer is supplied from an evaporated oxidizer channel 9, and secondary combustion gas is generated. The evaporated oxidizer channel 9 flows oxidizer into the main combustion chamber 11 in a gaseous state by heat of the main combustion chamber 11. The evaporated oxidizer channel 9 is formed in a wall surface of an inner wall surface forming element 27 forming an inner wall surface of the main combustion chamber 11.

Description

  The present invention relates to a two-component thruster that generates a combustion gas by mixing a liquid oxidant and a liquid fuel and reacting them with each other, and obtains thrust by ejecting the combustion gas.

  The thruster is mounted on, for example, an artificial satellite and adjusts the orbit and attitude of the artificial satellite by generating thrust.

  FIG. 1 shows a schematic configuration of a two-component thruster. As shown in FIG. 1, the two-component thruster 30 includes a fuel supply mechanism 31, an oxidant supply mechanism 33, a combustion chamber 35, and a nozzle 37. In the example of FIG. 1, the fuel supply mechanism 31 and the oxidant supply mechanism 33 respectively inject the liquid fuel and the liquid oxidant into the combustion chamber 35 so as to collide with each other. As a result, the liquid fuel and the liquid oxidant are atomized, and the mixing of both is promoted. The mixed liquid fuel and liquid oxidant react with each other. As a result, combustion gas is generated from the liquid fuel and the liquid oxidant. The combustion gas is injected from the nozzle 37, thereby obtaining thrust. As the liquid fuel, for example, hydrazine is used, and as the liquid oxidant, for example, dinitrogen tetroxide is used. Such a two-component thruster is disclosed in, for example, Patent Documents 1 and 2 below.

  In the two-component thruster, since the combustion gas reaches 3000K, the combustion chamber 35 is provided with a cooling means. The cooling means is often a combination of film cooling and radiation cooling.

  Film cooling is performed by injecting a part of the fuel to the inner wall surface of the combustion chamber 35 by the fuel supply mechanism 31 as indicated by an arrow A in FIG. That is, the fuel injected onto the inner wall surface of the combustion chamber 35 flows along the inner wall surface as shown by the arrow B in FIG. 1, thereby causing a gap between the inner wall surface and the combustion gas or flame in the combustion chamber 35. A cooling layer is formed. This cooling layer suppresses heat transfer from the combustion gas in the combustion chamber 35 to the inner wall of the combustion chamber 35.

  Radiation cooling is performed by radiating heat transmitted to the inner wall of the combustion chamber 35 through the cooling layer. This radiation is made from the outer surface of the structure forming the combustion chamber 35 to the outside.

JP 2009-085159 A Special table 2012-533701 gazette

  However, conventionally, it has been necessary to lengthen the combustion chamber as follows. In the case of FIG. 1, as described above, the liquid fuel and the liquid oxidant are each atomized by being injected into the combustion chamber 35 and colliding with each other. Thereby, mixing and reaction of the liquid fuel and the liquid oxidant are promoted, and combustion gas is generated from the liquid fuel and the liquid oxidant. In this process, combustion gas is generated. Therefore, in order to sufficiently burn the fuel by performing such a process, it is necessary to lengthen the combustion chamber in the gas flow direction.

  In addition, when the combustion chamber is long, the combustion efficiency decreases as follows. If the combustion chamber is long, the amount of fuel for forming a cooling layer on the inner wall of the combustion chamber increases. The fuel that forms the cooling layer is unlikely to contribute to combustion. Therefore, when the fuel for the cooling layer increases, the combustion efficiency decreases.

  SUMMARY OF THE INVENTION An object of the present invention is to provide a two-stage combustion type two-liquid thruster that can shorten the combustion chamber and increase the combustion efficiency.

In order to achieve the above object, according to the present invention, a combustion gas is generated by reacting a liquid oxidant and a liquid fuel, and a thrust is obtained by ejecting the combustion gas to the outside. A liquid thruster,
A secondary combustion chamber to which liquid fuel and liquid oxidant are supplied;
A fuel supply structure for supplying liquid fuel to the auxiliary combustion chamber;
An oxidant supply structure for supplying a liquid oxidant to the sub-combustion chamber,
In the auxiliary combustion chamber, the liquid oxidant generates primary combustion gas by reacting with a part of the liquid fuel, and the remaining liquid fuel is converted into unreacted fuel gas by the heat of the primary combustion gas,
A main combustion chamber to which primary combustion gas and unreacted fuel gas are supplied from the auxiliary combustion chamber;
An evaporating oxidant flow path for supplying an oxidant to the main combustion chamber,
In the main combustion chamber, a secondary combustion gas is generated from the unreacted fuel gas and the oxidant from the evaporated oxidant flow path, and this combustion gas is ejected to the outside.
The evaporating oxidant flow path receives the oxidant from the outside and evaporates it by the heat of the main combustion chamber, thereby allowing the oxidant to flow into the main combustion chamber in a gas state,
A two-stage combustion type two-liquid thruster is provided in which the evaporating oxidant flow path is formed in the wall surface of the main combustion chamber.

  A configuration example of the present invention will be described below.

The evaporating oxidant flow channel flows the oxidant from the downstream side of the main combustion chamber to the upstream side within the wall surface of the main combustion chamber, and causes the oxidant to flow into the main combustion chamber on the upstream side of the main combustion chamber,
In the main combustion chamber, on the upstream side, the unreacted fuel gas is mixed with the gas oxidant from the evaporating oxidant flow path, and thereby the secondary combustion gas generated by reacting with each other is sent to the outside on the downstream side. Erupted.

The cross-sectional area of the main combustion chamber is smaller in the downstream portion of the main combustion chamber as it moves downstream.
The evaporating oxidant flow path extends from the downstream end portion to the upstream end portion of the main combustion chamber, so that the oxidant from the outside is upstream from the downstream end portion of the main combustion chamber within the wall surface of the main combustion chamber. Flow to the end.

  The evaporating oxidant flow path extends along the inner wall surface of the main combustion chamber while being positioned in the vicinity of the inner wall surface of the main combustion chamber.

  According to the present invention described above, the evaporating oxidant flow path causes the oxidant to flow into the main combustion chamber in the state of gas by the heat of the main combustion chamber, so that the process of gasifying the liquid oxidant in the main combustion chamber can be omitted. . Therefore, the main combustion chamber can be shortened.

  Also, in the auxiliary combustion chamber, primary combustion gas and unreacted fuel gas are generated from liquid fuel and liquid oxidant, and this unreacted fuel gas is mixed with gas oxidant from the evaporative oxidant flow path in the main combustion chamber. To do. In this way, the unreacted fuel gas and the oxidant that has already been gasified are mixed and burned, so that the combustion is performed quickly. As a result, high combustion efficiency can be obtained.

  Furthermore, since the oxidant from the oxidant tank is supplied to the evaporated oxidant flow path in the inner wall surface forming body of the main combustion chamber, the inner wall surface forming body can be cooled by the oxidant from the oxidant tank. Therefore, since the above-mentioned cooling layer can be eliminated or reduced, fuel that does not easily contribute to combustion can be eliminated or reduced. As a result, higher combustion efficiency can be obtained.

The structure of the conventional thruster is shown. 1 shows a configuration of a two-stage combustion type two-liquid thruster according to an embodiment of the present invention. (A) is the IIIA-IIIA sectional view taken on the line of FIG. 2, (B) is the IIIB-IIIB sectional view taken on the line of FIG.

  A preferred embodiment of the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

  FIG. 2 shows a configuration of a two-stage combustion type two-liquid thruster 10 according to an embodiment of the present invention. The two-component thruster 10 generates a combustion gas by mixing a liquid oxidant and a liquid fuel and reacting them with each other, and obtains thrust by ejecting the combustion gas to the outside. As shown in FIG. 2, the two-stage combustion type two-liquid thruster 10 includes a fuel supply structure 3, an oxidant supply structure 5, a sub-combustion chamber 7, an evaporated oxidant flow path 9, a main combustion chamber 11, and the like. Is provided.

  The fuel supply structure 3 supplies liquid fuel (that is, liquid fuel) to the auxiliary combustion chamber 7. In the present embodiment, the fuel supply structure 3 is a fuel flow path that receives liquid fuel from the fuel supply source 1 (in the example of FIG. 2, the fuel tank 1). In the example of FIG. 2, the fuel flow path 3 receives liquid fuel from the fuel tank 1 through the fuel pipe 2. The fuel tank 1 accumulates liquid fuel (for example, hydrazine). The gas phase portion of the fuel tank 1 communicates with a gas tank (not shown) filled with a pressurized gas (for example, helium gas). The fuel pipe 2 is provided with a shutoff valve 13. When the shut-off valve 13 is opened, liquid fuel flows into the fuel pipe 2 by the pressurized gas phase portion in the fuel tank 1. The fuel pipe 2 introduces the liquid fuel received from the fuel tank 1 in this way into the fuel flow path 3 through another shutoff valve 15 (propellant valve) opened after the shutoff valve 13 is opened. In the example of FIG. 2, the fuel flow path 3 is formed in the solid interior of the end surface forming body 17 that forms the upstream end surface 7 a of the auxiliary combustion chamber 7 (that is, in the wall surface of the auxiliary combustion chamber 7). The fuel flow path 3 allows liquid fuel to flow into the auxiliary combustion chamber 7. Preferably, the fuel flow path 3 is provided with a fuel nozzle hole 3 a for injecting liquid fuel into the auxiliary combustion chamber 7.

  The oxidant supply structure 5 supplies a liquid oxidant (that is, a liquid state oxidant) to the auxiliary combustion chamber 7. The oxidant supply structure 5 receives the liquid oxidant from the oxidant supply source 4 (the oxidant tank 4 in the example of FIG. 2). In the example of FIG. 2, the oxidant supply structure 5 is a liquid oxidant flow path that receives the liquid oxidant from the oxidant tank 4 through the first oxidant pipe 6. The oxidant tank 4 accumulates a liquid oxidant (for example, dinitrogen tetroxide). The gas phase portion of the oxidant tank 4 communicates with a gas tank (not shown) filled with a pressurized gas (for example, helium gas). The first oxidizer pipe 6 is provided with a shut-off valve 19. When the shut-off valve 19 is opened, the liquid oxidant flows into the first oxidant pipe 6 by the pressurized gas phase portion in the oxidant tank 4. The first oxidant pipe 6 passes the liquid oxidant received from the oxidant tank 4 in this way through another shutoff valve 21 (propellant valve) opened after the shutoff valve 19 is opened. Introduce to 5. In the example of FIG. 2, the liquid oxidant flow path 5 is formed in a solid interior (that is, in the wall surface of the sub-combustion chamber 7) in the end surface forming body 17 of the sub-combustion chamber 7. The liquid oxidant flow path 5 allows the liquid oxidant to flow into the auxiliary combustion chamber 7. Preferably, the liquid oxidant flow path 5 is provided with an oxidant nozzle hole 5 a for injecting the liquid oxidant into the sub-combustion chamber 7.

  Preferably, the liquid oxidant flow path 5 (oxidant nozzle hole 5a in the example of FIG. 2) is injected from the fuel flow path 3 (fuel nozzle hole 3a in the example of FIG. 2) into the auxiliary combustion chamber 7. A liquid oxidant is injected into the auxiliary combustion chamber 7 toward the liquid fuel. Thereby, the liquid oxidant collides with the liquid fuel, the liquid fuel and the liquid oxidant are atomized, and the mixing of both is promoted. Note that when the liquid fuel (for example, hydrazine) is mixed with the liquid oxidant, it reacts with the liquid oxidant (for example, dinitrogen tetroxide) and burns.

  In the auxiliary combustion chamber 7, as described above, the liquid fuel and the liquid oxidant are supplied, so that the liquid oxidant reacts with a part of the liquid fuel to generate the primary combustion gas, and the primary combustion gas. The remaining liquid fuel is converted into unreacted fuel gas by the heat of The primary combustion gas and the unreacted fuel gas generated in the auxiliary combustion chamber 7 flow into the main combustion chamber 11. In the example of FIG. 2, the primary combustion gas and the unreacted fuel gas flow from the auxiliary combustion chamber 7 to the main combustion chamber 11 through the communication path 23. The communication passage 23 has an opening formed in the downstream end surface 7 b in the sub-combustion chamber 7 and an opening formed in the upstream end surface 11 a in the main combustion chamber 11. The auxiliary combustion chamber 7 has, for example, a cylindrical shape, and the inner peripheral surface of the auxiliary combustion chamber 7 is formed by the auxiliary combustion chamber forming body 25. The temperature of the auxiliary combustion chamber 7 becomes, for example, 800 ° C. to 900 ° C. due to the generation of the primary combustion gas. In the example of FIG. 2, the communication path 23 is formed in the solid interior of an inner wall surface forming body 27 described later.

  Liquid oxidation supplied from the liquid oxidant flow path 5 to the sub-combustion chamber 7 during the same unit time with respect to the amount (mass) of liquid fuel supplied from the fuel flow path 3 to the sub-combustion chamber 7 during unit time. The ratio of the amount (mass) of the agent is preferably 0.1 or more and maintained at 0.2 or less. Appropriate control can be performed to obtain such a ratio.

  In the present embodiment, the upstream side of the auxiliary combustion chamber 7 is the upstream side (the left side in FIG. 2) in the direction parallel to the central axis of the cylindrical auxiliary combustion chamber 7 (the direction along the central axis). The downstream side of the auxiliary combustion chamber 7 means the downstream side (the right side in FIG. 2) in the direction parallel to the central axis of the auxiliary combustion chamber 7.

  The evaporating oxidant channel 9 supplies a gas oxidant (that is, an oxidant in a gas state) to the main combustion chamber 11. The evaporating oxidant flow path 9 receives the oxidant from the outside (that is, the oxidant supply source 4) and evaporates the heat by the heat of the main combustion chamber 11, thereby allowing the oxidant to flow into the main combustion chamber 11 in a gas state. . In the example of FIG. 2, the evaporating oxidant channel 9 receives the oxidant from the oxidant tank 4 through the first oxidant tube 6, the liquid oxidant channel 5, and the second oxidant tube 8. The second oxidant pipe 8 communicates the liquid oxidant flow path 5 and the evaporated oxidant flow path 9.

  In the main combustion chamber 11, a secondary combustion gas is generated from the unreacted fuel gas from the sub-combustion chamber 7 and the oxidant in a gas state from the evaporated oxidant flow path 9, and this secondary combustion gas is Together with the primary combustion gas, it is injected outside through the nozzle 29 of the two-component thruster 10. As a result, a device (for example, an artificial satellite) on which the two-component thruster 10 is mounted obtains thrust. In the example of FIG. 2, the nozzle 29 is integrated with the inner wall surface forming body 27, but may be formed separately from the inner wall surface forming body 27 and then coupled to the inner wall surface forming body 27.

  Preferably, the evaporating oxidant flow path 9 is located downstream of the main combustion chamber 11 in the solid interior of the inner wall surface forming body 27 that forms the inner wall surface of the main combustion chamber 11 (that is, in the wall surface of the main combustion chamber 11). The oxidant is caused to flow from the upstream side to the upstream side, and the oxidant is caused to flow into the main combustion chamber 11 on the upstream side of the main combustion chamber 11. In the main combustion chamber 11, on the upstream side, the unreacted fuel gas is mixed with the gas oxidant from the evaporating oxidant channel 9, and flows downstream while reacting with the gas oxidant. Therefore, in the main combustion chamber 11, the downstream temperature is higher than the upstream temperature.

  In the present embodiment, the upstream side of the main combustion chamber 11 means the upstream side (left side in FIG. 2) in the direction parallel to the central axis of the main combustion chamber 11, and the downstream side of the main combustion chamber 11 Means the downstream side (the right side in FIG. 2) in the direction parallel to the central axis of the main combustion chamber 11. Here, in the present embodiment, the main combustion chamber 11 has a circular cross section by a plane orthogonal to the central axis at each position in a direction parallel to the central axis.

  In the present embodiment, as shown in FIG. 2, the cross-sectional area of the main combustion chamber 11 becomes smaller in the downstream portion of the main combustion chamber 11 as it moves downstream. The temperature of the main combustion chamber 11 is highest at the downstream end of the main combustion chamber 11 (position Pd indicated by a broken line in FIG. 2). Therefore, the evaporating oxidant channel 9 extends from the downstream end portion to the upstream end portion of the main combustion chamber 11 along the inner wall surface, while being positioned in the vicinity of the inner wall surface of the main combustion chamber 11. In the example of FIG. 2, the evaporating oxidant flow path 9 extends from the downstream end portion of the main combustion chamber 11 to the opening 11 a 1 of the upstream end surface 11 a of the main combustion chamber 11, and the gas oxidant is sent from this opening to the main combustion chamber 11. Let it flow.

  Preferably, the evaporating oxidant flow path 9 is provided with an oxidant nozzle hole 9 a for injecting a gas oxidant into the main combustion chamber 11. In the example of FIG. 2, the oxidant nozzle hole 9a has the above-described opening 11a1. In this case, more preferably, the oxidant nozzle hole 9 a injects the gas oxidant in the main combustion chamber 11 toward the unreacted fuel gas from the sub-combustion chamber 7. This causes the gas oxidant to collide with the unreacted fuel gas. In this case, for example, as shown in FIG. 2, the communication passage 23 described above extends in a direction parallel to the central axis of the main combustion chamber 11, and in this direction, unreacted fuel gas flows into the main combustion chamber 11 to oxidize. The agent nozzle hole 9 a injects the gas oxidant into the main combustion chamber 11 toward the central axis of the main combustion chamber 11 in a direction inclined from a direction parallel to the central axis.

  FIG. 3 shows the configuration of the evaporating oxidant flow path 9 of FIG. 2 according to the present embodiment. 3A is a cross-sectional view taken along the line IIIA-IIIA in FIG. 2, and FIG. 3B is a cross-sectional view taken along the line IIIB-IIIB in FIG. In FIG. 3, the evaporating oxidant channel 9 extends from the opening on the outer surface of the inner wall surface forming body 27 in the radial direction of the main combustion chamber 11 to a position near the inner wall surface of the main combustion chamber 11. Branched into a plurality of branch channels 9b, and these branch channels 9b are located in the vicinity of the inner wall surface of the main combustion chamber 11 and extend along the inner wall surface to the plurality of oxidant nozzle holes 9a. Yes. However, the evaporating oxidant channel 9 may have other shapes.

  The end surface forming body 17, the sub-combustion chamber forming body 25, and the inner wall surface forming body 27 described above may be formed separately and then combined with each other or may be integrally formed from the beginning.

  In the two-stage combustion type two-liquid thruster 10 according to the embodiment of the present invention described above, the following effects (A) to (H) are obtained.

(A) The evaporating oxidant channel 9 causes the oxidant to flow into the main combustion chamber 11 in the state of gas by the heat of the main combustion chamber 11, so that the process of gasifying the liquid oxidant in the main combustion chamber 11 is omitted. it can. Therefore, the main combustion chamber 11 can be shortened.

(B) In the auxiliary combustion chamber 7, primary combustion gas and unreacted fuel gas are generated from the liquid fuel and liquid oxidant, and this unreacted fuel gas is gas from the evaporated oxidant flow path 9 in the main combustion chamber 11. Mix with oxidizing agent. In this way, the unreacted fuel gas and the oxidant that has already been gasified are mixed and burned, so that the combustion is performed quickly. As a result, high combustion efficiency can be obtained.

(C) From the oxidant tank 4 in which the liquid oxidant is accumulated, the oxidant is introduced into the evaporated oxidant flow path 9 formed in the wall surface of the main combustion chamber 11. Therefore, since the inner wall surface forming body 27 can be cooled by this oxidizing agent, film cooling of the main combustion chamber 11 can be eliminated or reduced. As a result, higher combustion efficiency can be obtained.

(D) The liquid oxidant flows into the evaporating oxidant flow path 9, and this oxidant evaporates with heat from the main combustion chamber 11 in the evaporating oxidant flow path 9. The cooling effect is further enhanced. That is, the cooling effect of the inner wall surface forming body 27 is enhanced by converting the heat from the main combustion chamber 11 into the vaporization heat of the liquid oxidant. For example, the temperature of the inner wall surface forming body 27 can be suppressed to 1000 ° C. or lower.

(E) Furthermore, the evaporation oxidant flow path 9 makes it possible to use the gasification of the liquid oxidant for increasing the combustion efficiency for cooling the inner wall surface forming body 27.

(F) In the main combustion chamber 11, on the upstream side, the unreacted fuel gas is mixed with the gas oxidant from the evaporation oxidant flow path 9, and flows downstream while reacting with the gas oxidant. Therefore, in the main combustion chamber 11, the downstream temperature is higher than the upstream temperature. Therefore, in the present embodiment, in the wall surface of the main combustion chamber 11, the oxidant flows from the downstream side to the upstream side of the main combustion chamber 11, and the oxidant flows into the main combustion chamber 11 on the upstream side of the main combustion chamber 11. By doing so, the downstream part of the relatively high temperature inner wall surface forming body 27 can be cooled by the relatively low temperature oxidizing agent. Thereby, the cooling effect of the inner wall surface forming body 27 by the oxidizing agent is enhanced.

(G) The liquid oxidant from the oxidant tank 4 first flows into the downstream end of the hottest main combustion chamber 11 in the evaporative oxidant flow path 9 and then flows upstream of the main combustion chamber 11. Therefore, the downstream end part of the hottest main combustion chamber 11 can be cooled more effectively.

(H) Since the inner wall surface forming body 27 can be cooled as described above, the inner wall surface forming body 27 forming the main combustion chamber 11 can be made of a general metal material having a heat resistant temperature of 1000 ° C. or less. Therefore, the manufacturing cost of the thruster 10 can be reduced.

  The present invention is not limited to the above-described embodiment, and various changes can be made without departing from the scope of the present invention. For example, any one of the following modification examples 1 to 3 may be adopted, or any two or all of the modification examples 1 to 3 may be employed in combination. In this case, the other points are the same as described above.

(Modification 1)
The fuel supply structure 3 is not limited to the above-described fuel flow path as long as it receives liquid fuel from a fuel supply source and supplies the liquid fuel to the sub-combustion chamber 7, and may be another structure. .

(Modification 2)
The oxidant supply structure 5 is not limited to the above-described liquid oxidant flow path as long as it receives liquid oxidant from an oxidant supply source and supplies the liquid oxidant to the auxiliary combustion chamber 7. It may be a structure.

(Modification 3)
The second oxidant pipe 8 may branch from the first oxidant pipe 6 and extend to the evaporating oxidant flow path 9, or may extend from the oxidant tank 4 to the evaporating oxidant flow path 9. Good. In the latter case, the first oxidant pipe 6 and the second oxidant pipe 8 may extend from two different oxidant tanks, respectively.

1 Fuel supply source (fuel tank)
2 Fuel pipe 3 Fuel supply structure (fuel flow path)
3a Fuel nozzle hole 4 Oxidant supply source (oxidant tank)
5 Oxidant supply structure (liquid oxidant flow path)
5a Oxidant nozzle hole 6 First oxidant pipe 7 Subcombustion chamber 7a Upstream end face 7b Downstream end face 8 Second oxidant pipe 9 Evaporating oxidant flow path 9a Oxidant nozzle hole 9b Branch flow path 10 Two-component thruster 11 Main combustion chamber 11a Upstream end face 11a1 Opening 13, 15 Shut-off valve 17 End face forming body 19, 21 Shut-off valve 23 Communication path 25 Sub-combustion chamber forming body 27 Inner wall surface forming body 29 Nozzle

Claims (3)

A two-stage combustion type two-liquid thruster that generates a combustion gas by reacting a liquid oxidant and a liquid fuel and obtains thrust by ejecting the combustion gas to the outside,
A secondary combustion chamber to which liquid fuel and liquid oxidant are supplied;
A fuel supply structure for supplying liquid fuel to the auxiliary combustion chamber;
An oxidant supply structure for supplying a liquid oxidant to the sub-combustion chamber,
In the auxiliary combustion chamber, the liquid oxidant generates primary combustion gas by reacting with a part of the liquid fuel, and the remaining liquid fuel is converted into unreacted fuel gas by the heat of the primary combustion gas,
A main combustion chamber to which primary combustion gas and unreacted fuel gas are supplied from the auxiliary combustion chamber;
An evaporating oxidant flow path for supplying an oxidant to the main combustion chamber,
In the main combustion chamber, a secondary combustion gas is generated from the unreacted fuel gas and the oxidant from the evaporated oxidant flow path, and this combustion gas is ejected to the outside.
The evaporated oxidant flow path receives the oxidant from the outside, and flows the oxidant evaporated by the heat of the main combustion chamber into the main combustion chamber in a gas state.
A two-stage combustion type two-liquid thruster, wherein the evaporating oxidant flow path is formed in the wall surface of the main combustion chamber. The evaporating oxidant flow channel flows the oxidant from the downstream side of the main combustion chamber to the upstream side within the wall surface of the main combustion chamber, and causes the oxidant to flow into the main combustion chamber on the upstream side of the main combustion chamber,
In the main combustion chamber, on the upstream side, the unreacted fuel gas is mixed with the gas oxidant from the evaporating oxidant flow path, and thereby the secondary combustion gas generated by reacting with each other is sent to the outside on the downstream side. The two-stage combustion type two-liquid thruster according to claim 1, wherein the two-stage combustion type thruster is ejected. The cross-sectional area of the main combustion chamber is smaller in the downstream portion of the main combustion chamber as it moves downstream.
The evaporating oxidant flow path extends from the downstream end portion to the upstream end portion of the main combustion chamber, so that the oxidant from the outside is upstream from the downstream end portion of the main combustion chamber within the wall surface of the main combustion chamber. The two-stage combustion type two-liquid thruster according to claim 2, wherein the two-stage thruster is flowed to an end portion.

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