KR100717376B1 - A combustor chamber with regenerative cooling for high-pressure liquid rocket engine - Google Patents

Abstract

The present invention relates to a regenerative cooling combustion chamber for a high-pressure liquid rocket engine, and to uniformly supply and discharge cooling water to the regenerative cooling channel of the combustion chamber, and to obtain detailed information on the combustion chamber combustion phenomenon.

The regenerative cooling combustion chamber for a high pressure liquid rocket engine according to the present invention, the inner cylinder (10); An outer cylinder 20 coupled to the outside of the inner cylinder; A regenerative cooling channel (30) formed between the inner cylinder and the outer cylinder to guide the flow of cooling water; Manifold blocks (40, 50) are installed on both sides of the outer cylinder and provided with manifolds (41, 51) for uniformly distributed cooling water in the circumferential direction to guide the cooling water to be uniformly supplied and discharged; Supply / discharge holes (23,24) respectively formed in the outer cylinder to correspond to the manifold block to induce a uniform distribution of cooling water; The manifolds 33 and 34 are formed on the inlet and outlet sides of the regenerative cooling channel to correspond to the supply / discharge holes. The regenerative cooling channel is composed of a rib 31 formed at regular intervals along the circumferential portion of the inner cylinder and a cooling water passage 32 formed between the ribs.

Liquid Rocket, Combustor, Combustion Chamber, Regenerative Cooling, Manifold, Sensor

Description

A combustor chamber with regenerative cooling for high-pressure liquid rocket engine

1 is a side view of a regenerative cooling combustion chamber for a high pressure liquid rocket engine according to the present invention.

2 is a front view of a regenerative cooling combustion chamber for a high pressure liquid rocket engine according to the present invention;

Figure 3 is an enlarged view of the supply / discharge hole applied to the regenerative cooling combustion chamber for a high pressure liquid rocket engine according to the present invention.

Figure 4 is a partial extract to show the sensor mounting portion applied to the regenerative cooling combustion chamber for high-pressure liquid rocket engine according to the present invention.

5 and 6 show the measurement of the regenerative cooling combustion chamber for the high-pressure liquid rocket engine according to the present invention, respectively.

<Short description of the major reference symbols>

10: inner cylinder, 20: outer cylinder

23: supply hole, 24: discharge hole

30: regeneration cooling channel, 31: rib

32: coolant, 33,34: manifold

40,50: Manifold block, 41,51: Manifold part

60,70 tube, 80 sensor mounting part

90: probe,

The present invention relates to a regeneratively cooled combustion chamber for a high pressure liquid rocket engine, and more particularly, to regenerates and cools all parts of a combustion chamber of a high pressure combustion engine evenly and to check the pressure of the cooling water. It relates to a combustion chamber.

The rocket generates a high-temperature, high-pressure fuel gas, ejects it, and moves forward with its reaction force. The rocket includes a combustor for burning propellant and a nozzle for accelerating and directing the gas produced in the combustor.

Since the propellant must be a heat energy source that generates high heat and at the same time convert heat energy into kinetic energy, the propellant contains oxygen necessary for combustion as well as fuel and has a high degree of expansion as a gas. It is largely divided into solid state and liquid state.

Among them, liquid rockets using liquid propellant are widely used for satellite launch and space transport, and consist of propellant tank (oxidant and fuel), feeder and combustor.

The high-temperature, high-pressure combustion gas generated in the combustion chamber of such a rocket flows to the combustion chamber wall, so that a large amount of heat transfer occurs, and sufficient cooling is required to protect the wall. In particular, the reduction in cooling at the local combustion chamber wall causes fatal damage. Uniform cooling is essential.

In general, many regenerative cooling systems employing propellants or oxidants as coolants.

The regenerative cooling method uses one of the propellants as the coolant to transfer heat to one propellant externally induced along the hot surfaces of the rocket engine to maintain the combustor at an acceptable temperature.

The regenerative cooling channel should have a structure capable of sufficient cooling, and fuel, which is a coolant, should flow uniformly in each channel. That is, the combustion chamber must have a structure in which the coolant is uniformly supplied to each channel, and the amount flowing out through the channel must be uniform.

However, since the combustion chamber according to the prior art is only a level for supplying the cooling water, there is a problem in that the cooling water cannot be uniformly supplied and thus all parts are not uniformly cooled.

In addition, since the combustion state (static pressure, dynamic pressure) in the combustion chamber is not confirmed in real time, it is not practically managed.

An object of the present invention is to provide a combustion chamber for a high-pressure liquid rocket engine in which cooling water is uniformly distributed in all parts of the combustion chamber to cool all parts of the combustion chamber.

In addition, another object of the present invention is to make the shape of the sensor measuring unit on the wall surface of the combustion chamber to measure the combustion phenomenon (static pressure, dynamic pressure), etc. occurring in the combustion chamber, at this time, so as not to interfere with the supply of cooling water.

Combustion chamber for a high-pressure liquid rocket engine according to the present invention for achieving the above object, the inner cylinder / outer cylinder having a different diameter and are coupled to each other, the regenerative cooling channel is formed between the inner cylinder and the outer cylinder and the coolant circulates therein And a manifold block for supplying and discharging cooling water, respectively, installed in the outer cylinder, corresponding to the manifold of the manifold block in the outer cylinder, and having a larger effective cross-sectional area than that of the cooling water of the regeneration cooling channel. It is characterized in that it comprises a manifold formed in each of the inlet / outlet of the cooling channel in the circumferential direction so that the cooling water is uniformly supplied / discharged.

In addition, the sensor mounting unit for checking the state of the cooling water is preferably formed in the middle of the regenerative cooling channel.

Hereinafter, with reference to the accompanying drawings will be described a preferred embodiment of the present invention;

The regenerative cooling combustion chamber 100 for the high pressure liquid rocket engine includes an inner cylinder 10, an outer cylinder 20, a regenerative cooling channel 30 formed between the inner cylinder 10 and the outer cylinder 20, and a regenerative cooling channel. The manifold blocks 40 and 50 are formed at a circumferential portion 30 to supply and discharge coolant to the regenerative cooling channel 30, respectively, and are connected to the manifold blocks 40 and 50, respectively. It consists of tubes (60, 70) to guide the supply and discharge of.

The inner cylinder 10 and the outer cylinder 20 are formed with different diameters such that a regenerative cooling channel 30 is formed therebetween, and both left and right sides thereof are opened.

The regenerative cooling channel 30 is formed to circulate the cooling water between the inner cylinder 10 and the outer cylinder 20. As shown in FIG. 2, the regenerative cooling channel 30 is installed at a predetermined interval between the inner cylinder 10 and the outer cylinder 20. It consists of a plurality of cooling water passage 32 formed between a plurality of ribs 31 to be. That is, the cooling water passes along the cooling water path 32 between the ribs 31 and takes away the heat transferred to the inner cylinder 10 and the ribs 31.

At this time, the rib 31 may be formed separately and coupled between the inner cylinder 10 and the outer cylinder 20, but is preferably integrally formed on the outer circumferential surface of the inner cylinder 10 (or the inner circumferential surface of the outer cylinder 20). .

The inner cylinder 10 has a thickness of approximately 0.8 to 1.2, preferably about 1 mm, and the height of the ribs 31 is 3.5 to 4.5, preferably 4 mm.

The supply / discharge manifold blocks 40 and 50 are formed in annular shapes so as to communicate with the regenerative cooling channel 30 on both sides of the outer cylinder 20, respectively, so that the cooling water passage 32 of the regenerative cooling channel 30 is provided. Supplying and discharging cooling water.

As shown in FIG. 1, engaging jaws 21 and 22 for holding and engaging the manifold blocks 40 and 50 are formed at both sides of the outer periphery of the outer cylinder 20, respectively. The catching jaws 21 and 22 may be formed in an annular shape on the circumferential surface of the outer cylinder 20 or a plurality may be formed at regular intervals.

The cooling efficiency in the regenerative cooling channel 30 is closely related to the flow rate (ie, flow rate) of the cooling water passing through the cylinder section of the combustion chamber 100 if the cross section is constant. In the case of a liquid rocket engine, when the water is used as cooling water because the heat flux is 10MW / m ^ 2 or more in the combustion chamber, the flow rate should be 10m / s or more. Since liquid propellant combustion in the combustion chamber transfers heat in all directions, cooling in the combustion chamber should be uniform around the entire cylinder portion of the combustion chamber 100. That is, even if one or two cooling water passages 32 of the regenerative cooling channel 30 are not sufficiently cooled, the cooling water passages 32 and the outer cylinder 20 therein are above the melting point of the temperature due to heat transferred from the combustion chamber. It can rise and cause damage. Since the liquid rocket engine combustor operates at high pressure, even a momentary breakdown of the wall of a very small combustion chamber can cause very high temperature gas to be damaged by the pressure difference between the inside and the outside, resulting in damage to the combustor itself and the test equipment. In this relationship, the uniform cooling water supply in the regenerative cooling channel 30 is very important.

The tubes 60 and 70 guide the cooling water to the supply-side manifold block 40 and the discharge-side manifold block 50 so as to be smoothly supplied to and discharged from each other. It can be connected to four places at regular intervals along the circumferential direction.

The circumferential manifolds 41 and 51 are formed in the manifold blocks 40 and 50 so that the circumferential flow velocity of the coolant supplied through the tube 60 is small, thereby achieving a uniform distribution and discharging the circumferential manifolds. ) Is formed. In addition, the outer cylinder 20 has an elliptical shape formed in an elliptical shape so that the cross-sectional area is about 1.2 times larger than the effective cross-sectional area of the regenerative cooling channel 30 so as to uniformly supply and discharge the regenerative cooling channel 30 through the manifold 41. Supply / discharge holes 23 and 24 (see FIG. 3) are formed in the same quantity (about 120) as that of the cooling water channel of the regenerative cooling channel 30.

The supply / discharge holes 23 and 24 are for structural supply strength as well as for uniform supply and discharge of the cooling water.

Manifolds 33 and 34 are formed at the inlet / outlet side of the regeneration cooling channel 30 so that the coolant flowing through the supply hole 23 does not directly enter the cooling water passage 32 of the regeneration cooling channel 30.

That is, the cooling water is uniformly supplied to the cooling water path 32 through the supply tube 60-the supply side manifold block 40-the supply manifold part 41-the supply hole 23-the channel side supply manifold 33. Supplied and flows along the cooling water path 32 to deprive the heat of the inner cylinder 10 and the rib 31, and thereafter, the channel side discharge manifold 34-discharge hole 24-discharge manifold portion 51- Discharge side manifold block 50-discharge through the discharge tube (70).

In addition, in order to grasp combustion phenomenon and performance, combustion chamber pressure measurement is essential. Accordingly, a sensor mounting unit 80 for mounting a sensor S for measuring pressure during combustion is provided.

Sensor mounting portion 80 is formed along the shape of the sensor (S), because the size of the sensor (S) is larger than the width of one cooling water passage 31, several (depending on the size of the sensor (S)) of the coolant Closing the furnace 32 is made of a sealed structure with the outside. Since the flow of cooling water by the sensor mounting unit 80 should not be disturbed, the sensor mounting unit 80 preferably has a streamlined appearance.

In addition, the coolant flows from the right side (based on the drawing) of the sensor mounting unit 80 to the left side. At this time, the sensor mounting unit 80 and the ribs 31 adjacent to the sensor mounting unit 80 are not blocked by the sensor mounting unit 80. Naturally, the sensor mounting portion 80 end portion is spaced apart from the sensor mounting portion 80 by a predetermined distance. That is, the plurality of ribs 31 are formed in a structure in which a plurality of ribs 31 are cut off so that the space a of concentric circles is formed around the sensor mounting unit 80.

In addition, the amount of cooling water entering the cooling water path 32a corresponding to the rear side of the sensor mounting part 80 may be different from that of the other cooling water paths 32 due to the separation of flow on the downstream side of the sensor mounting part 80. In order to prevent the ribs 31b on both sides with the center of the ribs 31a coinciding with the center of the sensor mounting portion 80, the length of the ribs 31b is shorter, so that the ribs 31b are retracted to the rear. Thus, the cooling water flowing along the curvature of the sensor mounting portion 80 flows into the cooling water passages 32a on both sides of the center rib 31a in the same manner as the other cooling water passages 32.

In this case, the downstream side of the sensor mounting unit 80 becomes structurally weak as the length of the second rib 31b disposed downstream of the sensor mounting unit 80 (the left side of the drawing reference) is shortened, so as to reinforce it. The rib 31a is connected to the sensor mounting portion 80.

The first rib 31a serves to increase structural strength without disturbing the flow of cooling water. Due to this structure, the pressure can be measured without damage to the site where the sensor (S) is mounted during the combustion test.

On the other hand, as shown in Figure 5, according to the present invention by inserting the probe 90 to measure the flow rate and flow rate of the cooling water directly into the regenerative cooling channel 30 can be confirmed the uniformity of the flow by measuring the flow rate and flow rate . 6, the probe 90 may be installed in the discharge hole 24 of the outer cylinder 20 to measure the flow rate and the flow rate.

The uniformity of the flow was measured in the opposite hole 23 or 24 by mounting the probe 90 to only one of the supply manifold block 40 and the discharge manifold block 50 and supplying the actual cooling water and gas. You can verify the uniformity of the flow with.

Referring to the operation of the regenerative cooling combustion chamber for a high-pressure liquid rocket engine according to the present invention configured as described above are as follows.

Cooling water supplied through the plurality of supply-side tubes 50 is distributed in the circumferential direction along the manifold portion 41 by the pressure to supply the regeneration cooling channel 30 through the supply holes 23-the manifold 33. It is supplied to the cooling water path 32. At this time, the cooling water is uniformly supplied to all the cooling water paths 32 through the manifold portion 41, the supply hole 23, and the manifold 33.

Cooling water introduced into the cooling water passage 32 flows to the discharge side along the cooling water passage 32 to take heat from the inner cylinder 10 and the rib 31 to cool the combustion chamber 100.

On the other hand, while the cooling water flows along the cooling water path 32, some cooling water passes around the sensor mounting portion 80. When the cooling water passes around the sensor mounting portion 80, the sensor mounting portion 80 is curved (wired), so that the cooling water flows smoothly, and the rib 31a disposed at the center of the downstream side of the sensor mounting portion 80 is the sensor. Since the second rib 31b on both sides of the mounting portion 80 has a shorter length than the other ribs, the coolant may be discharged to all the cooling waters without any flow disturbance caused by the recirculation area occurring at the rear surface of the sensor mounting portion 80. 32) can be supplied uniformly.

As described above, according to the regeneratively cooled combustion chamber for the high-pressure liquid rocket engine according to the present invention, since the cooling water is uniformly distributed in all the cooling water paths, it is possible to uniformly cool all parts of the combustion chamber that have risen to a high temperature, thereby improving durability of the apparatus. And lifespan can be extended.

In addition, the combustion phenomenon of the combustion chamber can be confirmed through a sensor mounted in the combustion chamber, and even if the sensor is mounted, the flow of the cooling water is not disturbed, so that the management is easy.

Although the present invention has been described in connection with the above-mentioned preferred embodiments, it is possible to make various modifications or variations without departing from the spirit and scope of the invention. Accordingly, the appended claims will cover such modifications and variations as fall within the spirit of the invention.

Claims (6)

delete Inner cylinder 10; An outer cylinder 20 coupled to the outside of the inner cylinder; A regenerative cooling channel (30) formed between the inner cylinder and the outer cylinder to guide the flow of cooling water; In the regenerative cooling combustion chamber for a high-pressure liquid rocket engine, the regenerative cooling channel is provided with a sensor mounting portion 80 to which a sensor is mounted. Manifolds 41 and 51 are provided on both sides of the outer cylinder 20 so as to communicate with the regenerative cooling channel 30, respectively, and the cooling water is uniformly distributed in the circumferential direction. Manifold blocks (40, 50) for supplying and discharging cooling water to the cooling water passage 32 of the; A supply / discharge hole (23, 24) formed in the outer cylinder corresponding to the manifold block, respectively, and having a plurality of ellipses formed in an elliptical shape so as to have a larger cross-sectional area than an effective cross-sectional area of a regenerative cooling channel; And manifolds (33,34) formed corresponding to the supply / discharge holes on the inlet and outlet sides of the regenerative cooling channel. The regenerative cooling combustion chamber according to claim 2, wherein the supply / discharge holes (23, 24) have a larger cross-sectional area than that of the cooling water channel of the regenerative cooling channel. delete According to claim 2, wherein the sensor mounting portion 80 is a curved structure in which the periphery is sealed so that the sensor is mounted therein, the ribs corresponding to the sensor mounting portion of the ribs along the shape of the sensor mounting portion The regenerated cooling combustion chamber for a high-pressure liquid rocket engine, characterized in that the space (a) is formed spaced apart from the predetermined distance from the cooling water flow. The downstream side rib (31a) corresponding to the center of the sensor mounting portion 80 is connected to the sensor mounting portion, each one or more ribs 31b disposed on both sides of the rib (31a) is proximate. A regenerative cooling combustion chamber for a high pressure liquid rocket engine, wherein the length of the rib is shorter than that of the rib to allow the cooling water to flow uniformly.

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