KR100654966B1 - fuel injection face plate of liquid rocket engine for enhancement of the cooling performance - Google Patents

Abstract

The present invention is to provide a fuel injection face plate of a liquid rocket engine with improved cooling performance that can prevent the occurrence of temperature deviation due to local heating.

In the present invention for realizing this, in the fuel injection face plate of the liquid rocket engine which is installed at the inlet of the combustion chamber for injecting the oxidant and the fuel supplied from the oxidant supply pipe and the fuel supply pipe to the combustion chamber, the outlet space of the oxidant supply pipe and the An upper plate disposed between the combustion chambers and dividing the two spaces; A lower plate disposed on the combustion chamber side in parallel with the upper plate to form a space connected to the fuel supply pipe between the upper plate and the upper plate; A partition plate disposed between them to divide the space between the upper plate and the lower plate, the outer edge of which is located inside the upper edge of the upper plate and the lower plate, and the center portion of which is perforated; A plurality of holes formed in the holes drilled at the corresponding multiple positions of the upper plate, the lower plate and the divider plate, and a hollow connecting the outlet of the oxidant supply pipe and the combustion chamber, and a through hole connecting the space between the upper and lower plates and the combustion chamber. Provided are fuel injection face plates of a liquid rocket engine comprising two hollow injectors.

Rocket, engine, propulsion, action, reaction, liquid fuel, liquid oxygen

Description

Fuel injection face plate of liquid rocket engine for enhancement of the cooling performance

1 is a schematic cross-sectional view of a rocket engine for showing an application example of a general fuel injection face plate,

2 is a plan view showing a porous plate conventionally employed as the fuel injection face plate shown in FIG.

3 is a plan view of the 'plate' of the 'collision injector of the liquid rocket engine' of the Republic of Korea Patent Publication No. 2003-0076119,

4 is a partial cross-sectional view of the plate shown in FIG.

5 is a partial cross-sectional view for showing an operating state with respect to the plate shown in FIG.

6 is a partial cross-sectional view of the assembled state for showing the fuel injection face plate configuration of the liquid rocket engine according to the present invention;

FIG. 7 is a partial perspective view of an assembled state for illustrating a fuel injection face plate configuration of the liquid rocket engine shown in FIG. 6;

FIG. 8 is a half cross-sectional view for illustrating a fuel injection face plate operating state of the liquid rocket engine illustrated in FIG. 6.

Explanation of symbols on the main parts of the drawings

1: rocket engine 3: head part

5: fuel supply pipe 7: oxidant supply pipe

10: fuel injection face plate 18: combustion chamber

90: top plate 95: bottom plate

200: partition plate 210: retaining ring

220: injector

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a fuel injection face plate which is used to inject a liquid fuel and an oxidant into a combustion chamber in a liquid rocket engine.

The rocket engine is an engine that uses the reaction of force when it explodes and expels fuel. Because it uses liquid oxygen as an oxidant, it can burn and explode fuel even in the absence of air. Fuel is divided into solid fuel and liquid fuel. Liquid fuel has the advantage of being able to control the supply amount through the valve and the pump, and to stop and resume the combustion of the fuel.

That is, the liquid fuel is stored separately from the liquefied oxygen, and then mixed and combusted. The mixture of the fuel and the oxidant is a porous plate 10 which is a fuel injection face plate at the head 3 of the rocket engine 1 as shown in FIG. ) And the oxidant supply pipe 7 and the fuel supply pipe 5 are connected to a space formed above the engine head by the porous plate 10 (see Fig. 2).

A plurality of through holes 12 are formed in the porous plate 10 as described above, and the ends of the igniter 16 are penetrated so as to be exposed to the combustion chamber 18 at the central position thereof, so that the fuel supply pipe 5 is opened. The fuel flowing through is introduced into the combustion chamber 18 through the plurality of through holes 12 of the porous plate 10, thereby mixing with the oxidant flowing through the oxidant supply pipe 7 in the combustion chamber 18 (see FIG. 2).

As described above, the igniter 16 is ignited in the combustion chamber 18 in which the mixed fuel is present, and the driving force is applied to the rocket according to this action.

By the way, the rocket engine having a conventional general porous plate 10 as described above is ejected only in a predetermined direction in accordance with the direction of the through-hole 12 drilled in the porous plate 10, expecting a uniform fuel mixing it's difficult.

The invention related to an orthogonal radial injector arrangement in a liquid propulsion rocket engine disclosed in Korean Patent Laid-Open Publication No. 2003-0084366 discloses two oxidant injection holes in the lower side and two fuel injections for cooling in both sides. In the liquid rocket engine injector surface in which the ball unit unit injector is installed, the unit injector is installed on the injector surface in the orthogonal radial type which is a mixture of orthogonal and radial forms to uniformly mix the fuel and maintain the combustion surface evenly. Local heating can be prevented.

The 'liquid rocket engine mixer' disclosed in Korean Patent Laid-Open Publication No. 2003-0084366 includes a top plate that forms an oxidant storage unit between a main structure having a fuel supply unit and an oxidant supply unit, and includes a top plate and a predetermined top plate. The lower plate is provided to be spaced apart to form a fuel reservoir, and an upper portion thereof includes a plurality of collision type unit injectors brazed to the upper plate and a lower portion of the lower plate to be brazed to the lower plate. The injection in multiple directions allows the mixing with the uniform oxidant in the combustion chamber.

The 'collision injector of a liquid rocket engine' disclosed in Korean Patent Laid-Open Publication No. 2003-0076119 discloses a central injection path integrally formed with a lower end attached to a plate and penetrating the upper end and the lower end. And an inclined spray path formed only through the lower end portion, and the fuel and the oxidant are uniformly mixed to improve the reliability, and to test each injection component to improve the manufacturability and the hydraulic force of the injection jet. I can understand the characteristics.

That is, as shown in Figs. 3 to 5 relates to a mixer 50 equipped with about 200 impact injectors 60, the injector 60 is a combination of the upper end 70 and the lower end 80 The upper mounting portion 76 has a stepped portion formed on the upper side 72 of the upper end portion 70, and the lower mounting portion 82 having a stepped shape is formed on the lower portion 80 having a larger cross-sectional area than the upper end portion 70. ) Is formed on the lower side surface 84.

The upper mounting portion 76 and the lower mounting portion 82 are fitted to the upper plate 90 and the lower plate 95, respectively, and are coupled to each other, and the central injection path 100 and the side injection paths, through which fluids such as liquids and oxidants are injected, 110) two perforations each.

The central injection path 100 is formed in a straight line from the upper end surface 72 to the lower injection surface 86, the side injection path 110 is a predetermined angle from the lower upper side surface 88 to the injection surface 86 It is formed to be inclined.

The angle formed by the center and the side injection path (100, 110), the fluid injected through the injection path (100, 110) has a first impact point 120 and the secondary impact point 130, the central injection path (100) And the position and angle of the side injection path 110 so that the angle of the first and second collision points (120, 130) is in the range of 45 to 90 degrees.

According to the configuration as described above, the different types of fluids coming out through the central injection path 100 and the side injection path 110 are each mixed with the first collision, and again collided again at the secondary impact point 130 While mixing is made, a more uniform mixture of fluids is possible.

Therefore, the dispersion effect of the fuel and the oxidant in the form of fine particles can be improved independently, and the combustion efficiency can be expected to improve the reliability and performance of the rocket.

However, all conventional fuel injection face plates as described above have not been devised to increase the flow velocity of the fluid. Rather, the flow velocity of the fluid decreases and the pressure increases toward the center of the rocket head, thereby increasing the space of the fuel injection. Not only can not secure uniformity, but this also leads to a problem that leads to a performance degradation of the rocket engine.

In addition, the effect of cooling the fuel injecting plate by the fuel is also reduced, there is another problem that the combustion surface is not evenly maintained, thus causing a temperature deviation due to local heating.

The present invention is to solve the problems associated with the prior art as described above, the object of the present invention is to control the flow rate of the fluid to increase the effect of cooling the fuel injection face plate, to minimize the degree of action of the pressing force The present invention aims to provide a fuel injection face plate of a liquid rocket engine with improved cooling performance, which can secure spatial uniformity of mixed fuel.

That is, the object of the present invention, first, by increasing the flow rate of the fluid does not increase the pressure, it is possible to ensure the spatial uniformity in the injection of the fuel, thereby improving the performance of the rocket engine, Secondly, the liquid rocket engine, which improves the cooling performance which makes it possible to maintain the combustion surface evenly by cooling the fuel injection face plate by fuel and thus prevents the occurrence of temperature deviation due to local heating. It is to provide a fuel injection faceplate.

In order to achieve the above object, the present invention, in the fuel injection face plate of the liquid rocket engine which is installed at the inlet of the combustion chamber for injecting the oxidant and fuel supplied from the oxidant supply pipe and the fuel supply pipe to the combustion chamber, the outlet side of the oxidant supply pipe An upper plate disposed between a space and the combustion chamber to divide both spaces; A lower plate disposed on the combustion chamber side in parallel with the upper plate to form a space connected to the fuel supply pipe between the upper plate and the upper plate; A partition plate disposed between them to divide the space between the upper plate and the lower plate, the outer edge of which is located inward of the upper edge of the upper plate and the lower plate, and the central portion of which is perforated; A plurality of holes formed in the holes drilled at the corresponding multiple positions of the upper plate, the lower plate and the divider plate, and a hollow connecting the outlet of the oxidant supply pipe and the combustion chamber, and a through hole connecting the space between the upper and lower plates and the combustion chamber. Provided are fuel injection face plates of a liquid rocket engine comprising two hollow injectors.

Fixing rings are provided at the lower end portions disposed between the divider plates and the lower plates of the injectors, respectively, to support the divider plate from the lower plate, and the through hole is formed at the upper end portion positioned between the upper plate and the divider plate. The diameter of the upper end is larger than the diameter of the lower end.

In addition, in the present invention, each of the plurality of injectors is formed in a cylindrical shape, the upper and lower sides are opened, the lower end portion is inserted into the corresponding hole of the lower plate under the state that the fixing ring is overlapping and the lower plate and ; The step portion of the divider hole is inserted between the bottom outer portion and the upper end of the fixing ring so that the tip portion of the divider hole is stepped to a larger diameter than the lower portion, and the space between the top plate and the divider plate is spaced between the space inside the injector and An upper end portion formed with a plurality of through holes to communicate with each other; The upper insertion end extends therefrom stepped to a diameter smaller than the upper end so as to be inserted into the hole of the upper plate so that the tip portion of the upper plate hole is fixed under the seated state.

As described above, the fuel injection face plate of the present invention is injected into the combustion chamber while the oxidant and the liquid fuel supplied through the oxidant supply pipe and the fuel supply pipe are mixed by the injector, and the oxidant and the fuel are mixed in the combustion chamber.

In particular, the liquid fuel is circulated from the outer position of the fuel injection face plate to the center position of the fuel injection face plate through the space between the upper plate and the divider plate and the divider plate and the lower plate.

At this time, the liquid fuel flowing into the space between the divider and the lower plate may flow U-turn into the space between the upper plate and the divider at the position of the center of the fuel injection face plate, and the liquid fuel flows at twice the pressure. Depending on the condition, the pressure balance can be adjusted in the direction that can be achieved.

As above, as the liquid fuel flows at a uniform pressure and at a uniform flow rate in the entire space of the fuel injection face plate, the liquid fuel and the oxidant are mixed and injected in a uniform distribution, as well as cooling the fuel injection face plate by the liquid fuel as a whole. It is made uniform at the site.

In addition, it is possible to fundamentally solve the problem of the size and complicated structure of the rocket engine according to the expansion design of the head space to add or subtract the height of the flow path in the radial direction relative to the flow direction of the liquid fuel.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings.

As shown in FIG. 1, which is a schematic cross-sectional view of a rocket engine for showing an application example of a general 'fuel jet plate', the space where the oxidant supply pipe 7 and the fuel supply pipe 5 are connected is a rocket engine 1. It is related to the fuel injection face plate 10 of the liquid rocket engine 1 which becomes the upper part of the head part 3. Hereinafter, the fuel injection face plate of the present invention will be described with reference numeral 10.

6 is a partial cross-sectional view of the assembled state for showing the fuel injection face plate configuration of the liquid rocket engine according to the present invention, Figure 7 is a partial perspective view of the assembled state for showing the fuel injection face plate configuration of the liquid rocket engine according to the present invention. 8 is a half sectional view for showing a fuel injection face plate working state of the liquid rocket engine according to the present invention.

As illustrated, the fuel injection face plate 10 includes an upper plate 90, a lower plate 95, a divider plate 200, and a plurality of injectors 220 and a plurality of fixing rings 210.

The upper plate 90 separates the space to which the oxidant supply pipe 7 (see FIG. 1) is connected to the combustion chamber 18 (see FIG. 1) of the block of the rocket engine 1 (see FIG. 1). 1 is fixed to the upper inner wall of the block, the lower plate 95 is provided to be spaced in parallel with the upper plate 90.

The dividing plate 200 is disposed therebetween so as to divide the space between the upper plate 90 and the lower plate 95, and the outer edge thereof is larger than the outer edge of the upper plate 90 and the lower plate 95. It is located inward, and its central portion is formed in the form of a perforated disc.

Each of the plurality of injectors 220 is provided such that the upper and lower ends are fitted into and fixed in holes formed at corresponding positions of the upper plate 90 and the lower plate 95, and the lower end 224 and the upper end ( 222 and the upper insertion end 226, the upper and lower sides of the cylindrical shape is opened.

That is, the lower end portion 224 is inserted into the corresponding hole of the lower plate 95 in the state in which the fixing ring 210 is overlapped, the lower end portion 224 is larger than such a lower end portion 224 The upper end 222 is extended therefrom so as to step in diameter.

The upper end portion 222 as described above is the tip portion of the hole of the partition plate 200 is inserted between the lower outer portion and the upper end of the fixing ring 210 is fixed, the upper plate 90 and the partition plate ( A plurality of through holes 228a and 228b are formed such that the space between the 200 is in communication with the space inside the injector 220.

On the other hand, the upper insertion end 226 is inserted into the hole of the upper plate 90 so that the tip portion of the hole of the upper plate 90 is fixed to a smaller diameter than the upper end portion 222 so as to be fixed under the seated state. Extends from. In addition, the upper insertion end 226 is hollow (not shown) is formed on the side. The hollow connects the outlet of the oxidant supply pipe and the combustion chamber.

In addition, the plurality of fixing rings 210 are provided in a state overlapping with the injector 220 so as to support the partition plate 200 from the lower plate 95 at each of the plurality of injectors 220. do.

As described above, the fuel injection face plate 10 of the present invention injects the oxidant and the liquid fuel supplied through the oxidant supply pipe 7 and the fuel supply pipe 5 into the combustion chamber 18 while being mixed by the injector 220. .

In particular, the liquid fuel supplied through the fuel supply pipe 5 is the top plate 90, the partition plate 200 and the partition plate 200 from the outer position (section 'a' in Fig. 8) of the fuel injection face plate 10. It is distributed to the central position of the fuel injection face plate 10 through the space between the lower plate 95, at this time, the split plate 200 and the lower plate in the position ('b' section of FIG. 8) in the center of the fuel injection face plate 10 The liquid fuel that flowed into the space between the 95 and the U-turn into the space between the upper plate 90 and the partition plate 200 may flow twice, and the flow of the liquid fuel is pressure depending on the pressure state at each site. It is adjusted in the direction in which equilibrium can be achieved.

As described above, as the liquid fuel flows at a uniform pressure and at a uniform flow rate in the entire space of the fuel injection face plate 10, the liquid fuel and the oxidant are mixed and injected in a uniform distribution, as well as the fuel injection face plate by the liquid fuel. Cooling of the (10) is made uniform throughout the entire area, and the rocket engine (1) according to the expansion design of the space of the head (3) to add or subtract the height of the flow path in the radial direction relative to the flow direction of the liquid fuel The problem of size and complicated structure can be solved.

The present invention as described above provides the effect that, by increasing the flow rate of the first fluid and not increasing the pressure, it is possible to ensure spatial uniformity in the injection of the fuel.

Second, the present invention can improve the performance of the rocket engine due to the uniform distribution and injection of liquid fuel, and thirdly, to maintain the combustion surface evenly by producing the effect of cooling the fuel injection face plate by the fuel. Provide a useful effect.

The present invention ultimately provides the effect of preventing the occurrence of a temperature deviation due to local heating, and also in the expansion design of the head space to add or subtract the radial flow path height relative to the flow direction of the liquid fuel. Another effect is that it can solve the problem of the size and complex structure of the following rocket engine.

The present invention described as described above is merely a preferred embodiment, and the scope of the present invention is not limited to the above, but may be appropriately changed within the scope of the same idea.

Claims (2)

In the fuel injection face plate of the liquid rocket engine which is installed at the inlet of the combustion chamber for injecting the oxidant and fuel supplied from the oxidant supply pipe and the fuel supply pipe into the combustion chamber, An upper plate disposed between the outlet side space of the oxidant supply pipe and the combustion chamber to divide both spaces; A lower plate disposed on the combustion chamber side in parallel with the upper plate to form a space connected to the fuel supply pipe between the upper plate and the upper plate; A partition plate disposed between them to divide the space between the upper plate and the lower plate, the outer edge of which is located inside the upper edge of the upper plate and the lower plate, and the center portion of which is perforated; It is inserted into a hole drilled in a plurality of corresponding positions of the upper plate, the lower plate and the divider, the hollow connecting the outlet of the oxidant supply pipe and the combustion chamber, and the space between the upper and lower plates and the space of the combustion chamber, A fuel injection face plate of a liquid rocket engine comprising a plurality of hollow injectors having a through-hole formed between a top plate and a divider plate. The method of claim 1, Fixing rings are installed at the lower ends of the injectors to separate the supporting plates from the lower plates, respectively. The through hole is formed in the upper end located between the top plate and the divider, The fuel injection face plate of the liquid rocket engine, characterized in that the diameter of the upper end is larger than the diameter of the lower end.

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