An adjustable cooling channel

Abstract

This invention discloses an adjustable flow-dividing cooling channel, including a cooling wall coaxially mounted on the outer wall of the thrust chamber, forming a cooling cavity between the cooling wall and the outer wall of the thrust chamber. Coolant entering the first collector through the inlet pipe flows upward through a guide hole into the upper cooling cavity, then to the head of the thrust chamber, while the other part flows downward into the lower cooling cavity. Part of the coolant entering the lower cooling cavity enters the first outlet tank and is discharged from the first outlet hole to the second collector, while the other part enters the return tank and then the second outlet tank. Coolant entering the second return tank is discharged from the second outlet hole to the second collector. The coolant entering the second collector then flows back to the top of the upper cooling cavity through a conduit. This effectively cools the high-heat-flux area of ​​the thrust chamber, resulting in high coolant utilization, relatively low total flow resistance, reduced cooling system supply pressure, and solving the technical problem of low coolant utilization in the nozzle in the prior art.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of liquid rocket engine, and relates to a cooling pipe, in particular to a cooling channel with adjustable flow distribution. BACKGROUND

[0002] In recent years, with the development of space propulsion technology, the working chamber pressure of large-thrust liquid rocket engine in China is increasing, and the nozzle area ratio range is usually 30-100, and the maximum diameter of the nozzle can reach 1.5m-2m. When the chamber pressure increases, the heat flux density increases by the 0.8 power of the chamber pressure, and the heat flux density increases greatly. Under the condition of great increase of the nozzle area ratio and size, the thermal load is large, and the coolant demand is high.

[0003] The traditional large nozzle adopts a single flow structure, and the utilization rate of the coolant is not high, the flow resistance is high, the thickness of the nozzle is large, the weight is large, the temperature of the coolant in the downstream area is high, the reliability is poor, and the working life and system capacity are affected. SUMMARY

[0004] In view of the deficiencies of the prior art, the purpose of the present application is to provide a cooling channel with adjustable flow distribution to solve the technical problem of low utilization rate of the coolant in the nozzle in the prior art.

[0005] In order to solve the above technical problems, the present application adopts the following technical solutions:

[0006] A cooling channel with adjustable flow distribution, comprising a cooling wall coaxially arranged on the outer wall of a thrust chamber, a cooling cavity is formed between the cooling wall and the outer wall of the thrust chamber, the cooling wall comprises a fixedly connected upper end cooling wall and a lower end cooling wall, the cooling cavity comprises an upper cooling cavity and a lower cooling cavity corresponding to the upper end cooling wall and the lower end cooling wall respectively, the upper cooling cavity and the lower cooling cavity are communicated, a first collector is arranged on the upper end cooling wall, the first collector is communicated with the upper cooling cavity through a flow guide hole, and a water inlet pipe is connected to the first collector; a second collector is arranged on the lower end cooling wall, the second collector is communicated with the lower cooling cavity, and the second collector is communicated with the top of the upper cooling cavity through a guide pipe.

[0007] A plurality of reinforcing ribs distributed along the axis of the thrust chamber are uniformly arranged in the lower cooling cavity in the circumferential direction, the reinforcing ribs are connected to the outer wall of the thrust chamber and the inner wall of the cooling wall on both sides, respectively, and grooves are formed between adjacent reinforcing ribs, the grooves comprise a backflow groove and a water outlet groove, one end of the backflow groove is communicated with the upper cooling cavity.

[0008] The middle part of the water outlet groove is provided with a stopper, so as to be divided into a first water outlet groove and a second water outlet groove, one end of the first water outlet groove is communicated with the upper cooling cavity, and the other end of the first water outlet groove is communicated with the second collector through a first water outlet hole; one end of the second water outlet groove is communicated with the other end of the reflux groove, and the other end of the second water outlet groove is communicated with the second collector through a second water outlet hole.

[0009] The application also comprises the following technical features:

[0010] The conduit is provided with a throttle ring, and a plurality of small holes are arranged on the throttle ring.

[0011] The upper end cooling wall and the lower end cooling wall are fixed by welding through a connecting ring.

[0012] The height of the reinforcing rib ranges from 4 to 5 mm.

[0013] Compared with the prior art, the application has the beneficial technical effects that:

[0014] (I) In the application, the coolant of the first collector entering through the water inlet pipe flows upward into the upper cooling cavity through the flow guide hole, and then to the head of the thrust chamber, and the other part flows downward into the lower cooling cavity, part of the coolant entering the lower cooling cavity enters the first water outlet groove and is discharged from the first water outlet hole to the second collector, and the other part enters the reflux groove and then enters the second water outlet groove, the coolant entering the second reflux groove is discharged from the second water outlet hole to the second collector, and the coolant entering the second collector flows back to the top of the upper cooling cavity through the conduit, which can effectively cool the high heat flow area of the thrust chamber, the utilization rate of the coolant is high, the total flow resistance is relatively low, the supply pressure of the cooling system is reduced to a certain extent, and the technical problem of low utilization rate of the coolant in the nozzle in the prior art is solved.

[0015] (II) The application is suitable for high-pressure thrust chambers, is beneficial to cooling the convergent section and the throat with high heat flux density, has low average temperature rise of the coolant, and can reduce the total flow resistance by 20% under the same size.

[0016] (III) The conduit of the application can directly guide the coolant in the middle of the lower cooling cavity out to enter the head of the thrust chamber, so that the size and volume of the first collector and the second collector are reduced, and the weight of the device is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of the application;

[0018] Figure 2 It is a sectional view of the overall structure of the application;

[0019] Figure 3 It is Figure 2An enlarged schematic view of the part A in the middle;

[0020] Figure 4 As Figure 2 An enlarged schematic view of the part in the middle;

[0021] Figure 5 As Figure 4 A partial sectional view along the axial direction of the thrust chamber.

[0022] The meanings of the various reference numbers in the drawing are as follows: 1-thrust chamber, 2-cooling wall, 3-cooling cavity, 4-first collector, 5-flow guide hole, 6-water inlet pipe, 7-second collector, 8-conduit, 9-stiffening rib, 10-groove, 11-first water outlet hole, 12-second water outlet hole, 13-throttle ring, 14-connection ring;

[0023] 201-upper end cooling wall, 202-lower end cooling wall;

[0024] 301-upper cooling cavity, 302-lower cooling cavity;

[0025] 1001-backflow groove, 1002-water outlet groove;

[0026] 100201-stop block, 100202-first water outlet groove, 100203-second water outlet groove.

[0027] The specific content of the present application is further explained in detail in the following combined with embodiments. DETAILED DESCRIPTION

[0028] It should be noted that all the parts in the present application, in the absence of special explanation, adopt the parts known in the art.

[0029] The following gives specific embodiments of the present application, it should be noted that the present application is not limited to the following specific embodiments, any equivalent transformation made on the basis of the technical solutions of the present application falls within the protection scope of the present application.

[0030] The present application gives a cooling channel with adjustable flow distribution, such as Figures 1 to 5As shown, the cooling wall 2 is coaxially arranged on the outer wall of the thrust chamber 1, and the cooling cavity 3 is formed between the cooling wall 2 and the outer wall of the thrust chamber 1. The cooling wall 2 includes the upper end cooling wall 201 and the lower end cooling wall 202 fixedly connected. The cooling cavity 3 includes the upper cooling cavity 301 and the lower cooling cavity 302 corresponding to the upper end cooling wall 201 and the lower end cooling wall 202, respectively. The upper cooling cavity 301 and the lower cooling cavity 302 are connected in communication. The first collector 4 is arranged on the upper end cooling wall 201. The first collector 4 is in communication with the upper cooling cavity 301 through the flow guide hole 5. The first collector 4 is connected with the water inlet pipe 6.

[0031] A plurality of reinforcing ribs 9 distributed along the axial direction of the thrust chamber 1 are uniformly arranged in the lower cooling cavity 302 in the circumferential direction. The reinforcing ribs 9 are connected with the outer wall of the thrust chamber 1 and the inner wall of the cooling wall 2 on both sides, respectively. The grooves 10 are formed between adjacent reinforcing ribs 9. The grooves 10 include the return groove 1001 and the water outlet groove 1002. One end of the return groove 1001 is in communication with the upper cooling cavity 301.

[0032] The middle part of the water outlet groove 1002 is provided with the stop block 100201, which divides the water outlet groove 1002 into the first water outlet groove 100202 and the second water outlet groove 100203. One end of the first water outlet groove 100202 is in communication with the upper cooling cavity 301. The other end of the first water outlet groove 100202 is in communication with the second collector 7 through the first water outlet hole 11. One end of the second water outlet groove 100203 is in communication with the other end of the return groove 1001. The other end of the second water outlet groove 100203 is in communication with the second collector 7 through the second water outlet hole 12.

[0033] In the above technical solution, the coolant in the first collector 4 entering through the water inlet pipe 6 flows upward into the upper cooling cavity 301 through the flow guide hole 5, and then flows into the head of the thrust chamber 1. Another part flows downward into the lower cooling cavity 302. Part of the coolant entering the lower cooling cavity 302 enters the first water outlet groove 100202 and is discharged from the first water outlet hole 11 to the second collector 7. Another part enters the return groove 1001 and then enters the second water outlet groove 100203. The coolant entering the second return groove 100203 is discharged from the second water outlet hole 12 to the second collector 7. The coolant entering the second collector 7 is returned to the top of the upper cooling cavity 301 through the conduit 8. The high-heat-flow area of the thrust chamber can be effectively cooled. The utilization rate of the coolant is high, the total flow resistance is relatively low, the supply pressure of the cooling system is reduced to a certain extent, and the technical problem of low utilization rate of the coolant in the existing technology is solved.

[0034] Specifically, the conduit 8 is provided with a throttle ring 13. A plurality of small holes are arranged on the throttle ring 13.

[0035] In the above technical solution, the flow resistance of the throttle ring can conveniently compensate for the flow resistance deviation in the upper and lower cooling cavities, optimize the flow ratio, and ensure effective cooling under appropriate flow resistance.

[0036] Specifically, the upper end cooling wall 201 and the lower end cooling wall 202 are welded and fixed through the connecting ring 14. Under the premise of ensuring quality, the processing difficulty is reduced.

[0037] Specifically, the height of the reinforcing ribs 9 ranges from 4 to 5 mm.

[0038] In the above technical solution, the number of reinforcing ribs 9 can be set according to requirements, the height of the reinforcing ribs 9 in the cooling cavity 3 is reduced from 7 to 8 mm to 4 to 5 mm, and the three-dimensional depth of the grooves between the reinforcing ribs is shallower. Not only does it increase the flow rate, but also reduces the structural weight of the cooling wall by more than 30%.

Claims

1. An adjustable split cooling gallery characterized by, The application relates to a cooling wall (2) coaxially arranged on the outer wall of a thrust chamber (1), wherein a cooling cavity (3) is formed between the cooling wall (2) and the outer wall of the thrust chamber (1), the cooling wall (2) comprises an upper end cooling wall (201) and a lower end cooling wall (202) fixedly connected, the cooling cavity (3) comprises an upper cooling cavity (301) and a lower cooling cavity (302) corresponding to the upper end cooling wall (201) and the lower end cooling wall (202) respectively, the upper cooling cavity (301) and the lower cooling cavity (302) are communicated, a first collector (4) is arranged on the upper end cooling wall (201), the first collector (4) is communicated with the upper cooling cavity (301) through a flow guide hole (5), and a water inlet pipe (6) is connected to the first collector (4); a second collector (7) is arranged on the lower end cooling wall (202), the second collector (7) is communicated with the lower cooling cavity (302), and the second collector (7) is communicated with the top of the upper cooling cavity (301) through a guide pipe (8). A plurality of reinforcing ribs (9) distributed along the axial direction of the thrust chamber (1) are uniformly arranged in the lower cooling cavity (302) in the circumferential direction, the reinforcing ribs (9) are connected with the outer wall of the thrust chamber (1) and the inner wall of the cooling wall (2) on the two sides respectively, grooves (10) are formed between adjacent reinforcing ribs (9), the grooves (10) comprise a reflux groove (1001) and a water outlet groove (1002), one end of the reflux groove (1001) is communicated with the upper cooling cavity (301), and the middle part of the water outlet groove (1002) is provided with a stop block (100201) for dividing the water outlet groove (1002) into a first water outlet groove (100202) and a second water outlet groove (100203), one end of the first water outlet groove (100202) is communicated with the upper cooling cavity (301), the other end of the first water outlet groove (100202) is communicated with the second collector (7) through a first water outlet hole (11), one end of the second water outlet groove (100203) is communicated with the other end of the reflux groove (1001), and the other end of the second water outlet groove (100203) is communicated with the second collector (7) through a second water outlet hole (12). A throttle ring (13) is arranged in the guide pipe (8), and a plurality of small holes are arranged on the throttle ring (13).

2. The split cooling passage of claim 1, wherein, The upper end cooling wall (201) and the lower end cooling wall (202) are welded and fixed through a connecting ring (14).

3. The split cooling passage of claim 1, wherein, The height of the reinforcing rib (9) ranges from 4 mm to 5 mm.

4. The split cooling passage of claim 1, wherein, ​

Images