JP2007120333A - Injection pipe of combustor for rocket and combustor for rocket - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a combustor for a rocket capable of improving combustion efficiency, and capable of improving specific impulse, by forming a finer droplet. <P>SOLUTION: This injection pipe 11 of the combustor for the rocket has an inner cylinder 13 and an outer cylinder 15 having the axis C in common, and injects a liquid oxidizing agent LOx from the inside of the inner cylinder 13, and injects fuel gas GH2 from between the inner cylinder 13 and the outer cylinder 15, and is characterized by arranging a diffusion part 23 between the inner cylinder 13 and the outer cylinder 15 for turning the flowing direction of the fuel gas GH2 outward by a predetermined angle to the axis C. <P>COPYRIGHT: (C)2007,JPO&INPIT

Description

  The present invention relates to a rocket combustor.

Generally, a rocket combustor includes a combustion chamber and a nozzle, and the combustion chamber includes an injector for injecting fuel and an oxidant and an injected fuel gas (for example, hydrogen gas ( GH2)) and a liquid oxidant (for example, liquid oxygen (LOx)) are known to be provided with a combustion chamber (for example, see Non-Patent Document 1).
In the rocket combustor described above, the fuel gas and the liquid oxidant are injected in a coaxial jet state, and the liquid oxidant is atomized, evaporated, and burned with the fuel gas.

In recent years, due to the demand for higher efficiency of rocket combustors, improvement in specific thrust has been demanded of rocket combustors.
In order to increase the specific thrust of the rocket combustor, the improvement of the combustion efficiency in the rocket combustor is the most important factor, and in order to improve the combustion efficiency, the average particle size of the atomized liquid oxidant is increased. It is known that it is important to reduce the size and make the particle size distribution uniform.
For this reason, various techniques for promoting atomization of a liquid oxidizer in a rocket combustor have been proposed (see, for example, Patent Document 1).
JP 2002-266703 A (2nd page, FIG. 5 etc.) Harrje, D.H. J. et al. , And Reardon, F .; H. , Liquid Properant Rocket Instability, NASA SP-194, 1972, p157

In the above-mentioned Patent Document 1, a coaxial element (injector) that includes an inner cylinder and an outer cylinder, injects liquid oxygen from the inside of the inner cylinder, and injects hydrogen gas from between the inner cylinder and the outer cylinder. And what provided the some convex part which protrudes in the radial direction center side is disclosed by the inner periphery of the front-end | tip part of an inner cylinder.
According to the above-described coaxial element, the horseshoe vortex that swirls along the root of the convex portion is generated by collision of liquid oxygen with the convex portion provided on the inner peripheral surface of the distal end portion of the inner cylinder. Mixing of liquid oxygen and hydrogen gas could be promoted by the horseshoe vortex generated in such liquid oxygen.

In general, liquid oxygen including the coaxial element described in Patent Document 1 is ejected from the inner cylinder in the form of a liquid column, and the hydrogen gas flowing around the liquid column collides with the surface of the liquid column, thereby being separated from the surface of the liquid column as a droplet. (Atomized).
However, the method of tearing liquid oxygen with hydrogen gas has a problem in that there is a limit to the fineness of the particle diameter of the liquid oxygen droplets obtained.

  The present invention has been made to solve the above problems, and provides a rocket combustor capable of improving combustion efficiency and specific thrust by forming finer droplets. The purpose is to do.

In order to achieve the above object, the present invention provides the following means.
An injection tube of a rocket combustor according to the present invention has an inner cylinder and an outer cylinder sharing a central axis, injects a liquid oxidant from the inside of the inner cylinder, and between the inner cylinder and the outer cylinder. A rocket combustor injection pipe for injecting fuel gas from the inner cylinder and between the inner cylinder and the outer cylinder, diffusion with the fuel gas flow direction directed outward by a predetermined angle with respect to the central axis A portion is provided.

  According to the present invention, since the flow direction of the fuel gas is directed outward by a predetermined angle with respect to the central axis by the diffusion portion, the fuel gas flows along the surface of the liquid oxidant ejected in a liquid column form from the inner cylinder. Flowing. Therefore, the fuel gas does not collide with the liquid column surface of the liquid oxidant, and the wave generated on the liquid column surface of the liquid oxidant can be sufficiently developed. As a result, droplets having a small particle diameter are torn off from the developed wave, and fine liquid oxidant droplets can be formed. The droplets torn from this developed wave are smaller than the particle size of the droplets torn off by the fuel gas.

That is, the liquid oxidant injected from the inner cylinder flows so as to increase in cross-sectional area as the distance from the injection tube increases. On the other hand, the fuel gas spreads away from the central axis as it moves away from the injection pipe by the diffusion portion. The spread angles of the flow of the liquid oxidant and the fuel gas are substantially the same.
Therefore, the fuel gas flows in a direction along the boundary surface of the flowing liquid oxidant while spreading, and does not collide with the liquid oxidant. Further, the droplets torn off from the surface of the liquid oxidant are immediately diffused by the fuel gas flowing in the vicinity of the boundary surface.
In addition, it is thought that the wave which generate | occur | produces on the liquid column surface of a liquid oxidizer originates in unstable factors, such as a density difference of a liquid oxidizer.

In the above invention, the diffusion portion is an inclined surface provided on the outer surface of the inner cylinder,
It is desirable that the inclined surface has an inclination angle of the predetermined angle that inclines outward in the fuel gas injection direction with respect to the central axis.

  According to the present invention, since the inclined surface is provided on the outer surface of the inner cylinder, the fuel gas is ejected from the injection pipe after colliding and being guided by the inclined surface. Therefore, the fuel gas injection direction is directed outward by a predetermined angle with respect to the central axis, and the fuel gas flows along the surface of the liquid oxidant liquid column.

  In the above invention, the diffusion portion is a blade extending in a radial direction between the inner cylinder and the outer cylinder, and the blade imparts a turning force that rotates around the central axis to the fuel gas. It is desirable.

  According to the present invention, since the swirl vanes are provided, the swirl force around the central axis can be applied to the injected fuel gas. Since the swirl flow spreads and flows toward the downstream, the swirl vane adjusts the swirl degree of the fuel gas so that the flow of the fuel gas can be spread outward by a predetermined angle with respect to the central axis.

  In the above invention, the diffusing portion is a wall that seals between the inner cylinder and the outer cylinder, and an injection hole provided in the wall, and the axis of the injection hole is the central axis. On the other hand, it is desirable to incline outward by a predetermined angle toward the fuel injection direction.

  According to the present invention, since the diffusing portion is the wall body and the injection hole, the fuel gas injection direction is directed outward by a predetermined angle with respect to the central axis. That is, the fuel gas flowing between the inner cylinder and the outer cylinder is blocked by the wall body and ejected from the injection hole. Since the axis of the injection hole is inclined outward by a predetermined angle toward the fuel injection direction with respect to the central axis, the injection direction of the fuel gas injected from the injection hole is outward by a predetermined angle with respect to the central axis. Directed to.

  In the above-described invention, an extension portion that extends to the injection side from the end portion of the inner cylinder is provided at the end portion on the injection side of the outer cylinder, and the inner surface of the extension portion is in relation to the central axis. It is desirable that the fuel gas has an inclination angle inclined outward by a predetermined angle toward the fuel gas injection direction.

  According to the present invention, since the extension portion is provided, the jetted fuel gas can be prevented from diffusing outward. Therefore, it is possible to prevent a decrease in the flow rate of the fuel gas in the vicinity of the extension, and it is possible to effectively take in and diffuse the droplets torn from the liquid oxidant into the fuel gas flow.

Since the inner surface of the extension portion has an inclination angle inclined outward by a predetermined angle in the fuel gas injection direction with respect to the central axis, the fuel gas can flow along the surface of the liquid oxidant liquid column. Therefore, the wave generated on the surface of the liquid oxidant liquid column can be sufficiently developed, and fine liquid oxidant droplets can be formed from the developed wave.
On the other hand, for example, if the inner surface is not provided with an inclination angle, the spread of the fuel gas flow is suppressed by the inner surface, and the fuel gas flow collides with the surface of the liquid oxidant liquid column. Then, the wave generated on the surface of the liquid oxidant liquid column cannot be sufficiently developed, and it becomes difficult to form fine liquid oxidant droplets.

  The rocket combustor according to the present invention includes an injector that mixes and injects a liquid oxidant and a fuel gas, a combustion chamber in which the mixture of the liquid oxidant and the fuel gas is combusted, and a nozzle from which the combustion gas is ejected. The rocket combustor according to the present invention is characterized in that the injector is provided in the injector.

  According to the present invention, since the injection tube of the rocket combustor according to the present invention is provided, finer liquid oxidizer droplets can be formed, and combustion efficiency and specific thrust can be improved. Can be planned.

  According to the rocket combustor of the present invention, the diffusion portion directs the flow direction of the fuel gas outward by a predetermined angle with respect to the central axis, thereby sufficiently generating the wave generated on the liquid column surface of the liquid oxidant. Can be developed. Therefore, it is possible to form fine liquid oxidizer droplets from the developed wave, and it is possible to improve the combustion efficiency and the specific thrust.

[First Embodiment]
Hereinafter, a first embodiment of the present invention will be described with reference to FIGS. 1 to 3.
FIG. 1 is a schematic diagram illustrating the configuration of a rocket combustor according to the present embodiment.
As shown in FIG. 1, the rocket combustor 1 is a mixture of hydrogen gas (fuel gas (hereinafter referred to as GH2)) and liquid oxygen (liquid oxidant (hereinafter referred to as LOx)). An injector 3 for injecting into the combustion chamber, a combustion chamber (Combustion Chamber) 5 for forming the combustion chamber, and a nozzle 7 for discharging the combustion gas and generating thrust are provided.

  The injector 3 is schematically configured from an injection surface 9 and a plurality of injection tubes 11 arranged on the injection surface 9. Usually, several hundred injection pipes 11 are arranged so as to extend to the back side (left side in FIG. 1) of the injection surface 9. The injection tube 11 is arranged so as to be substantially uniform in the circumferential direction with respect to the central axis in the thrust direction of the rocket combustor 1 (see Non-Patent Document 1 for details).

FIG. 2 is a schematic diagram illustrating the configuration of the injection pipe in the injector of FIG.
As shown in FIG. 2, the injection tube 11 is generally configured by a cylindrical LOx post (inner cylinder) 13 and a cylindrical sleeve (outer cylinder) 15 adjacent to the outer periphery of the LOx post 13.
The LOx post 13 is provided with an orifice 17 at the LOx inflow side end (left end in FIG. 2). At the approximate center in the longitudinal direction of the LOx post 13, a flange portion 19 extending outward in the radial direction is provided. The outer peripheral surface of the LOx post 13 in the vicinity of the LOx ejection side end (the right end in FIG. 2) has a smaller diameter than the outer peripheral surface of other regions. By forming in this way, the GH2 flow path 21 through which GH2 flows is formed between the sleeve 15 and the sleeve 15.
Further, an inclined surface (diffusion part) 23 whose outer peripheral surface increases in diameter toward the LOx ejection direction is formed at the LOx ejection side end of the LOx post 13. The inclined surface 23 is formed to have an inclination of about 5 ° to 9 ° with respect to the central axis C. More desirably, it is formed so as to have an inclination of about 7 ° with respect to the central axis C.

The sleeve 15 is formed in a substantially cylindrical shape having a shorter length in the central axis C direction than the LOx post 13. An inflow hole 25 to which GH2 is supplied is formed at a substantially center in the longitudinal direction of the sleeve 15 so as to extend in the radial direction.
The left end of the sleeve 15 in FIG. 2 is in contact with the flange portion 19, and the inner surface of the sleeve 15 and the outer surface of the LOx post 13 are in contact with each other in the vicinity of the flange portion 19. By forming in this way, the relative position of the LOx post 13 and the sleeve 15 can be fixed.

As shown in FIG. 1, a baffle hub 27 and a baffle blade 29 that suppress a resonance phenomenon in the combustion chamber are provided on the injection surface 9.
The baffle hub 27 is a cylindrical member that extends from the injection surface 9 toward the nozzle 7 and is disposed so as to share the central axis with the rocket combustor 1. The baffle blade 29 is a plate-like member that extends from the ejection surface 9 toward the nozzle 7 and is disposed so as to extend radially outward from the baffle hub 27.

The combustion chamber 5 is formed in a substantially cylindrical shape. An end portion on the injector 3 side (left end portion in FIG. 1) in the combustion chamber 5 is fixed to the injector 3, and an end portion on the nozzle 7 side (right end portion in FIG. 1) is connected to the nozzle 7.
The nozzle 7 is formed in a substantially conical shape having a larger cross-sectional diameter in the combustion gas injection direction (the right direction in FIG. 1). An end of the nozzle 7 on the injector 3 side (left end in FIG. 1) is connected to the combustion chamber 5.
In addition, a well-known thing can be used as the combustion chamber 5 and the nozzle 7, It does not specifically limit.

Next, the operation of the rocket combustor 1 having the above configuration will be described. First, the outline of the action in the rocket combustor 1 will be described.
In the rocket combustor 1 in the present embodiment, as shown in FIG. 1, LOx and GH2 are injected into the injection pipe 11 of the injector 3, and LOx and GH2 are injected into the combustion chamber 5 through the injection pipe 11. Mixed. The mixture of LOx and GH2 injected into the combustion chamber 5 is ignited by an igniter (not shown), and then the combustion gas generated inside the combustion chamber 5 is throttled by the nozzle 7 and discharged in the direction of exhausting the combustion gas. And thrust is generated.

Next, the effect | action in the injection pipe 11 which is the characterizing part of this embodiment is demonstrated.
In the injection tube 11 in the present embodiment, as shown in FIG. 2, LOx is injected into the LOx post 13 from the inflow side end (left end in FIG. 2) of the LOx post 13. The LOx injected into the LOx post 13 is rectified by the orifice 17 and ejected from the LOx post 13 toward the combustion chamber 5.

  LOx is ejected from the LOx post 13 so as to form a substantially columnar liquid column, and its cross section increases toward the ejection direction (the right direction in FIG. 2). The side surface of the liquid column of LOx has an inclination of about 7 ° with respect to the central axis C. This inclination is not affected by the LOx ejection speed or the like and is almost constant.

FIG. 3 is a diagram showing a liquid column shape of LOx ejected from the LOx post. In this figure, the LOx liquid column is photographed when only LOx is ejected.
The LOx ejected from the LOx post 13 flows in a liquid column shape that spreads downstream as shown in FIG. The side surface of the liquid column of LOx has an inclination of about 7 ° with respect to the central axis C. Further, waves are generated on the surface of the liquid column of LOx due to unstable factors such as a difference in density of LOx. This wave develops toward the downstream, and when the wave develops sufficiently, a droplet with a small particle size is torn off from the wave.

On the other hand, GH2 is injected into the GH2 flow path 21 from the inflow hole 25 of the sleeve 15. The GH 2 injected into the GH 2 flow path 21 collides with the inclined surface 23 and flows along the inclined surface 23. Thereafter, the gas is ejected from the GH2 flow path 21 toward the combustion chamber 5.
Since GH2 flows along the inclined surface 23 and then is injected from the GH2 flow path 21, it flows along the inclined surface 23 after the injection, and in this embodiment, about 5 ° to 9 ° with respect to the central axis C. It becomes a flow with expanse. Therefore, GH2 flows along the LOx liquid column without colliding.

  Waves are generated on the surface of the liquid column of LOx ejected from the ejection tube 11 due to disturbance of the density distribution of LOx. This wave develops toward the downstream of LOx, and the droplet is torn off from the sufficiently developed wave at a predetermined position. The torn droplets are diffused by GH2 flowing around.

According to the above configuration, the flow direction of GH2 is directed outward from about 5 ° to 9 ° with respect to the central axis C by the inclined surface 23. Therefore, GH2 is along the surface of LOx ejected in a liquid column shape. Flowing. Therefore, GH2 does not collide with the surface of the liquid column of LOx, and can sufficiently develop waves generated on the surface of the liquid column of LOx. As a result, a droplet having a small particle diameter can be torn off from the developed wave, and a fine LOx droplet can be formed, and atomization can be promoted.
Thus, since fine droplets can be formed by the injection tube 11, the combustion efficiency of the rocket combustor 1 and the specific thrust can be improved.

  Since the inclined surface 23 is provided on the outer peripheral surface of the LOx post 13, the GH 2 is ejected from the injection pipe 11 after being collided and guided by the inclined surface 23. Therefore, the injection direction of GH2 is directed outward from about 5 ° to 9 ° with respect to the central axis C, and GH2 can flow along the surface of the liquid column of LOx. The wave generated on the surface of the LOx liquid column can be sufficiently developed because GH2 flows along the surface of the LOx liquid column.

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIGS.
The basic configuration of the rocket combustor of this embodiment is the same as that of the first embodiment, but the configuration of the injection tube is different from that of the first embodiment. Therefore, in the present embodiment, only the configuration of the injection pipe will be described using FIGS. 4 and 5, and description of other components such as nozzles will be omitted.
FIG. 4 is a schematic diagram illustrating the configuration of the injection pipe of the rocket combustor according to the present embodiment.
In addition, the same code | symbol is attached | subjected to the component same as 1st Embodiment, and the description is abbreviate | omitted.

  As shown in FIG. 4, the injection pipe 61 in the rocket combustor 51 of the present embodiment includes a cylindrical LOx post (inner cylinder) 63 and a cylindrical sleeve 65 (outer cylinder) adjacent to the outer periphery of the LOx post 63. ).

FIG. 5 is a developed view around the circumference of the LOx post 63 for explaining the configuration of the swirl vanes of FIG.
At the LOx ejection side end of the LOx post 63, a swirl vane (diffusion part) 73 extending outward in the radial direction is provided over the entire circumferential surface. As shown in FIG. 5, the swirl vanes 73 are arranged to be inclined at a predetermined angle with respect to the central axis C.

  The tilt angle of the swirl vane 73 is set so that the angle at which the GH2 flow injected from the injection pipe 61 spreads is about 5 ° to 9 ° with respect to the central axis C. That is, in the swirling flow, since the angle at which the flow spreads changes depending on the degree of swirling of the flow, the angle at which the flow spreads is adjusted by the inclination angle of the swirling blades 73.

Next, the effect | action in the injection pipe 61 which consists of said structure is demonstrated.
The outline of the operation of the rocket combustor 51 is the same as that of the first embodiment, and the description thereof is omitted.
In the injection pipe 61 in this embodiment, LOx is injected into the LOx post 63 from the inflow side end (left end in FIG. 4) of the LOx post 63, as shown in FIG. The LOx injected into the LOx post 63 is rectified by the orifice 17 and ejected from the LOx post 63.

On the other hand, GH2 is injected into the GH2 flow path 21 from the inflow hole 25 of the sleeve 65. GH2 injected into the GH2 flow path 21 flows toward the GH2 ejection side (right side in FIG. 4). A predetermined turning force around the central axis C is given to the GH 2 by the turning blade 73, and the GH 2 is ejected from the GH 2 flow path 21 as a turning flow.
GH2 ejected as a swirl flow becomes a flow that spreads downstream. In the present embodiment, the flow has a spread of about 5 ° to 9 ° with respect to the central axis C. Therefore, GH2 flows along the LOx liquid column without colliding.

According to the above configuration, since the swirl vane 73 is provided in the injection pipe 61, the swirl force around the central axis C can be given to the GH2 flow, and the GH2 flow can be turned into the swirl flow.
The degree of swirling of GH2 can be adjusted by swirling blades 73, so that the flow of GH2 can be widened by about 5 ° to 9 ° with respect to the central axis C. Therefore, the wave generated on the surface of the LOx liquid column can be sufficiently developed because GH2 flows along the surface of the LOx liquid column.

[Third Embodiment]
Next, a third embodiment of the present invention will be described with reference to FIGS.
The basic configuration of the rocket combustor of this embodiment is the same as that of the first embodiment, but the configuration of the injection tube is different from that of the first embodiment. Therefore, in the present embodiment, only the configuration of the injection pipe will be described with reference to FIGS. 6 and 7, and description of other components such as the nozzle will be omitted.
FIG. 6 is a schematic diagram illustrating the configuration of the injection pipe of the rocket combustor according to the present embodiment.
In addition, the same code | symbol is attached | subjected to the component same as 1st Embodiment, and the description is abbreviate | omitted.

  As shown in FIG. 6, the injection tube 111 in the rocket combustor 101 of the present embodiment is roughly configured by a cylindrical LOx post 113 and a cylindrical sleeve 115 adjacent to the outer periphery of the LOx post 113. Yes.

FIG. 7 is a front view for explaining the arrangement of the injection holes in FIG.
A wall body (diffusion part) 123 that closes the GH2 flow path 21 is provided at the GH2 injection side end (right end in FIG. 5) of the injection pipe 111. The wall body 123 is formed with an injection hole (diffusion part) 124 that is inclined in a direction away from the central axis C in the GH2 injection direction (right direction in FIG. 5). The injection hole 124 is formed to have an inclination of about 5 ° to 9 ° with respect to the central axis C. Further, as shown in FIG. 7, the injection holes 124 are arranged at equal intervals on the same circumference with the central axis C as the center.

Next, the effect | action in the injection pipe 111 which consists of said structure is demonstrated.
The outline of the operation of the rocket combustor 101 is the same as that of the first embodiment, and the description thereof is omitted.
In the injection tube 111 in the present embodiment, LOx is injected into the LOx post 113 from the inflow side end (left end in FIG. 4) of the LOx post 113, as shown in FIG. The LOx injected into the LOx post 113 is rectified by the orifice 17 and ejected from the LOx post 113.

On the other hand, GH2 is injected into the GH2 flow path 21 from the inflow hole 25 of the sleeve 115. The GH2 that has flowed through the GH2 flow path 21 toward the GH2 ejection side (the right side in FIG. 5) is ejected from the injection hole 124.
The injection hole 124 has an inclination of about 5 ° to 9 ° with respect to the central axis C, and GH2 flows along the injection hole 124, so that GH2 flows along the LOx liquid column without colliding.

  According to said structure, since the injection pipe 111 is equipped with the wall body 123 and the injection hole 124, the injection direction of GH2 is orient | assigned about 5 to 9 degrees outward with respect to the central axis C. That is, the axis of the injection hole 124 is inclined about 5 ° to 9 ° toward the GH2 injection direction with respect to the central axis C. Therefore, the injection direction of GH2 discharged from the injection hole 124 is also set to the central axis C. On the other hand, it can be directed outward by about 5 ° to 9 °. Therefore, the wave generated on the surface of the LOx liquid column can be sufficiently developed because GH2 flows along the surface of the LOx liquid column.

[Fourth Embodiment]
Next, a fourth embodiment of the present invention will be described with reference to FIG.
The basic configuration of the rocket combustor of this embodiment is the same as that of the first embodiment, but the configuration of the injection tube is different from that of the first embodiment. Therefore, in the present embodiment, only the configuration of the injection pipe will be described using FIG. 8, and description of other components such as nozzles will be omitted.
FIG. 8 is a schematic diagram illustrating the configuration of the injection pipe of the rocket combustor according to the present embodiment.
In addition, the same code | symbol is attached | subjected to the component same as 1st Embodiment, and the description is abbreviate | omitted.
As shown in FIG. 8, the injection pipe 161 in the rocket combustor 151 of the present embodiment includes a cylindrical LOx post 13 and a cylindrical sleeve (outer cylinder) 165 adjacent to the outer periphery of the LOx post 13. It is roughly structured.

The sleeve 165 is formed with a recess (extension portion) 173 in which the GH2 ejection side end (the right end in FIG. 8) extends in the GH2 ejection direction from the LOx post 13. The inner peripheral surface (inner surface) 174 of the recess 173 is formed as an inclined surface that is separated from the central axis C toward the GH2 ejection direction. The inner peripheral surface 174 is formed to have an inclination of about 5 ° to 9 ° with respect to the central axis C.
Further, the length of the recess 173 in the direction of the central axis C is formed to be 1.8D to 1.2D, where D is the opening diameter of the recess 173 at the GH2 ejection side end (right end in FIG. 8). Yes.

Next, the effect | action in the injection pipe 161 which consists of said structure is demonstrated.
The outline of the operation in the rocket combustor 151 is the same as that in the first embodiment, and thus the description thereof is omitted. Moreover, since the effect | action of the inclined surface 23 in the injection pipe 161 is the same as that of 1st Embodiment, the description is abbreviate | omitted.

  In the injection pipe 161 in the present embodiment, LOx is injected into the LOx post 13 from the inflow side end (left end in FIG. 8) of the LOx post 13 as shown in FIG. The LOx injected into the LOx post 13 is rectified by the orifice 17 and ejected from the LOx post 13.

On the other hand, GH2 is injected into the GH2 flow path 21 from the inflow hole 25 of the sleeve 65. GH2 injected into the GH2 flow path 21 flows toward the GH2 ejection side (right side in FIG. 4).
Since GH2 flows along the inclined surface 23 and then is injected from the GH2 flow path 21, it flows along the inclined surface 23 after the injection, and in this embodiment, about 5 ° to 9 ° with respect to the central axis C. It becomes a flow with expanse.
GH2 ejected from the GH2 flow path 21 flows along the inner peripheral surface 174 of the recess 173.

  According to the above configuration, the recess 173 can prevent the ejected GH2 from diffusing outward. Therefore, a decrease in the flow rate of GH2 in the vicinity of the recess 173 can be prevented, and the droplets torn off from the LOx liquid column can be effectively taken into the GH2 flow and diffused.

Since the inner peripheral surface 174 of the recess 173 is an inclined surface inclined outward from about 5 ° to 9 ° with respect to the central axis C, GH2 can flow along the surface of the liquid column of LOx. Therefore, the wave generated on the surface of the liquid column of LOx can be sufficiently developed, and fine liquid oxidant droplets can be formed from the developed wave.
On the other hand, for example, if the inner peripheral surface 174 is not provided with an inclination angle, the spread of the GH2 flow is suppressed by the inner peripheral surface 174, and the GH2 flow collides with the LOx liquid column surface. Then, the wave generated on the surface of the LOx liquid column cannot be sufficiently developed, and it becomes difficult to form fine droplets.

[Fifth Embodiment]
Next, a fifth embodiment of the present invention will be described with reference to FIG.
The basic configuration of the rocket combustor of this embodiment is the same as that of the first embodiment, but the configuration of the injection tube is different from that of the first embodiment. Therefore, in the present embodiment, only the configuration of the injection pipe will be described using FIG. 9, and description of other components such as nozzles will be omitted.
FIG. 9 is a schematic diagram illustrating the configuration of the injection pipe of the rocket combustor according to the present embodiment.
In addition, the same code | symbol is attached | subjected to the component same as 1st Embodiment, and the description is abbreviate | omitted.

As shown in FIG. 9, the injection pipe 211 in the rocket combustor 201 of the present embodiment is roughly configured by a cylindrical LOx post 63 and a cylindrical sleeve 165 adjacent to the outer periphery of the LOx post 63. Yes.
The sleeve 165 is formed with a recess 173 whose GH2 ejection side end (right end in FIG. 9) extends in the GH2 ejection direction from the LOx post 63. The inner peripheral surface 174 of the recess 173 is formed as an inclined surface that is separated from the central axis C toward the GH2 ejection direction.

  In addition, since the action and effect in the injection pipe 211 which consists of said structure are the combination with the effect | action of the above-mentioned 2nd Embodiment and the effect | action of 4th Embodiment, the description is abbreviate | omitted.

[Sixth Embodiment]
Next, a sixth embodiment of the present invention will be described with reference to FIG.
The basic configuration of the rocket combustor of this embodiment is the same as that of the first embodiment, but the configuration of the injection tube is different from that of the first embodiment. Therefore, in this embodiment, only the configuration of the injection pipe will be described with reference to FIG. 10, and description of other components such as the nozzle will be omitted.
FIG. 10 is a schematic diagram illustrating the configuration of the injection pipe of the rocket combustor according to the present embodiment.
In addition, the same code | symbol is attached | subjected to the component same as 3rd and 4th embodiment, and the description is abbreviate | omitted.

As shown in FIG. 10, the injection pipe 261 in the rocket combustor 251 of the present embodiment is roughly configured by a cylindrical LOx post 113 and a cylindrical sleeve 165 adjacent to the outer periphery of the LOx post 113. Yes.
The sleeve 165 is formed with a recess 173 whose GH2 ejection side end (right end in FIG. 10) extends in the GH2 ejection direction from the LOx post 113. The inner peripheral surface 174 of the recess 173 is formed as an inclined surface that is separated from the central axis C toward the GH2 ejection direction.

  In addition, since the action and effect in the injection pipe 261 having the above-described configuration are a combination of the action of the third embodiment and the action of the fourth embodiment, the description thereof is omitted.

It is the schematic explaining the structure of the combustor for rockets concerning the 1st Embodiment of this invention. It is the schematic explaining the structure of the injection pipe in the injector of FIG. It is a figure which shows the liquid column shape of LOx ejected from the LOx post. It is the schematic explaining the structure of the injection pipe of the combustor for rockets concerning the 2nd Embodiment of this invention. It is a figure explaining the structure of the turning blade | wing of FIG. It is the schematic explaining the structure of the injection tube of the combustor for rockets concerning the 3rd Embodiment of this invention. It is a front view explaining arrangement | positioning of the injection hole of FIG. It is the schematic explaining the structure of the injection pipe of the combustor for rockets concerning the 4th Embodiment of this invention. It is the schematic explaining the structure of the injection pipe of the combustor for rockets concerning the 5th Embodiment of this invention. It is the schematic explaining the structure of the injection pipe of the combustor for rockets concerning the 6th Embodiment of this invention.

Explanation of symbols

1, 51, 101, 151, 201, 251 Combustor for rocket 3 Injector 5 Combustion chamber (combustion chamber)
7 Nozzle 11, 61, 111, 161, 211, 261 Injection pipe 13, 63, 113 LOx post (inner cylinder)
15, 65, 115, 165 Sleeve (outer cylinder)
23 Inclined surface (diffusion part)
73 Swirling blade (diffusion part)
123 Wall (diffusion part)
124 injection hole (diffusion part)
173 Recess (extension part)
174 Inner peripheral surface (inner surface)
C Center axis

Claims (6)

It has an inner cylinder and an outer cylinder that share a central axis,
Injecting liquid oxidant from the inside of the inner cylinder,
A rocket combustor injection pipe for injecting fuel gas from between the inner cylinder and the outer cylinder,
A rocket combustor injection, characterized in that a diffusing portion is provided between the inner cylinder and the outer cylinder to direct the flow direction of the fuel gas outward by a predetermined angle with respect to the central axis. tube. The diffusion part is an inclined surface provided on the outer surface of the inner cylinder,
2. The rocket combustor injection pipe according to claim 1, wherein the inclined surface has the predetermined inclination angle inclined outward in the fuel gas injection direction with respect to the central axis. The diffusion part is a blade extending in a radial direction between the inner cylinder and the outer cylinder,
2. The rocket combustor injection pipe according to claim 1, wherein the blade imparts a turning force rotating around the central axis to the fuel gas. 3. The diffusion portion is a wall body that seals between the inner cylinder and the outer cylinder, and an injection hole provided in the wall body,
2. An injection tube for a rocket combustor according to claim 1, wherein the axis of the injection hole is inclined outward by a predetermined angle toward the fuel injection direction with respect to the central axis. At the end of the outer cylinder on the injection side, an extension that extends to the injection side from the end of the inner cylinder is provided,
5. The rocket according to claim 1, wherein an inner surface of the extension portion has an inclination angle inclined outward by a predetermined angle toward the fuel gas injection direction with respect to the central axis. Combustor injection tube. An injector for mixing and injecting liquid oxidant and fuel gas;
A combustion chamber in which the mixture of the liquid oxidant and the fuel gas is combusted;
A rocket combustor having a nozzle from which combustion gas is ejected,
A rocket combustor, wherein the rocket combustor injection pipe according to any one of claims 1 to 5 is provided in the injector.

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