阅读说明：本技术 一种火箭发动机推力室热试用身部模块 (Body module for hot test of rocket engine thrust chamber ) 是由 刘占一 陈宏玉 周康 许婷 王勇 王丹 李舒欣 于 2021-08-31 设计创作，主要内容包括：本发明提供一种火箭发动机推力室热试用身部模块,解决现有火箭发动机推力室身部设计,难以满足长时间热试试验需求、加工复杂、成本较高的问题。该模块包括主冷却剂入口腔、主冷却剂出口腔、辅冷却剂腔体及依次连接的燃烧室、连接部、喉道；燃烧室包括燃烧室内壳、燃烧室外壳、设在燃烧室外壳和燃烧室内壳间的燃烧室冷却通道；主冷却剂出口腔设在燃烧室外壳前端且与燃烧室冷却通道连通；喉道包括喉道内壳、喉道外壳、设在喉道外壳和喉道内壳间的喉道冷却通道；主冷却剂入口腔设在喉道外壳后端且与喉道冷却通道连通；连接部开设有周向错位设置且不连通的多个辅冷却剂通道和连接通道；辅冷却剂腔体设在连接部外壁且与辅冷却剂通道入口端连通。(The invention provides a body module for a hot test of a rocket engine thrust chamber, which solves the problems that the existing rocket engine thrust chamber body design is difficult to meet the long-time hot test requirement, the processing is complex and the cost is high. The module comprises a main coolant inlet cavity, a main coolant outlet cavity, an auxiliary coolant cavity, a combustion chamber, a connecting part and a throat which are sequentially connected; the combustion chamber comprises a combustion chamber inner shell, a combustion chamber outer shell and a combustion chamber cooling channel arranged between the combustion chamber outer shell and the combustion chamber inner shell; the main coolant outlet cavity is arranged at the front end of the combustion chamber shell and communicated with the combustion chamber cooling channel; the throat comprises a throat inner shell, a throat outer shell and a throat cooling channel arranged between the throat outer shell and the throat inner shell; the main coolant inlet cavity is arranged at the rear end of the throat shell and communicated with the throat cooling channel; the connecting part is provided with a plurality of auxiliary coolant channels and connecting channels which are arranged in a circumferentially staggered manner and are not communicated; the auxiliary coolant cavity is arranged on the outer wall of the connecting part and communicated with the inlet end of the auxiliary coolant channel.)

1. A body module is used in hot examination of rocket engine thrust chamber which characterized in that: comprises a main coolant inlet cavity (4), a main coolant outlet cavity (5), an auxiliary coolant cavity (6), a combustion chamber (1), a connecting part (2) and a throat (3), which are coaxially connected in sequence from front to back along the incoming flow direction;

the combustion chamber (1) comprises a combustion chamber inner shell (101), a combustion chamber outer shell (102) and a plurality of combustion chamber cooling channels (103), wherein the combustion chamber inner shell and the combustion chamber outer shell (102) are coaxially arranged, and the combustion chamber cooling channels are uniformly distributed on the circumference of the combustion chamber cooling channels;

the main coolant outlet cavity (5) is arranged at the front end of the combustion chamber shell (102) and is respectively communicated with the front ends of the plurality of combustion chamber cooling channels (103);

the throat (3) comprises a throat inner shell (31), a throat outer shell (32) and a plurality of throat cooling channels (33), wherein the throat inner shell and the throat outer shell (32) are coaxially arranged, and the plurality of throat cooling channels (33) are arranged between the throat outer shell (32) and the throat inner shell (31) and are uniformly distributed on the circumference;

the main coolant inlet cavity (4) is arranged at the rear end of the throat shell (32) and is respectively communicated with the rear ends of the throat cooling channels (33);

the connecting part (2) is provided with a plurality of auxiliary coolant channels (204) which are uniformly distributed on the circumference and a plurality of connecting channels (205) which are uniformly distributed on the circumference, and the auxiliary coolant channels (204) and the connecting channels (205) are arranged in a staggered manner along the circumferential direction and are not communicated; two ends of the connecting channel (205) are respectively communicated with the rear end of the combustion chamber cooling channel (103) and the front end of the throat cooling channel (33); each auxiliary coolant channel (204) comprises a straight hole (241) and a tangential hole (242), the inlet end of the straight hole (241) is opened on the outer wall of the connecting part (2), the outlet end of the straight hole is communicated with the inlet end of the tangential hole (242), and the outlet end of the tangential hole (242) is opened on the inner wall of the connecting part (2);

the auxiliary coolant cavity (6) is arranged on the outer wall of the connecting part (2) and is respectively communicated with the inlet ends of the plurality of straight holes (241);

the main coolant inlet cavity (4), the main coolant outlet cavity (5), the auxiliary coolant cavity (6), the combustion chamber (1), the connecting part (2) and the throat (3) are integrated.

2. A rocket engine thrust chamber hot-test body module as recited in claim 1, further comprising: the combustion chamber cooling channel (103) and the throat cooling channel (33) are both of a spiral structure, and the spiral angle is 30 degrees.

3. A rocket engine thrust chamber hot-test body module as recited in claim 2, further comprising: a plurality of spiral combustion chamber ribs (104) which are uniformly distributed on the circumference are arranged between the combustion chamber inner shell (101) and the combustion chamber outer shell (102), and the combustion chamber cooling channel (103) is formed among the adjacent 2 spiral combustion chamber ribs (104), the outer wall of the combustion chamber inner shell (101) and the inner wall of the combustion chamber outer shell (102);

a plurality of main spiral throat ribs (34) which are uniformly distributed on the circumference are arranged between the throat inner shell (31) and the throat outer shell (32), and the throat cooling channel (33) is formed among the adjacent 2 main spiral throat ribs (34), the outer wall of the throat inner shell (31) and the inner wall of the throat outer shell (32).

4. A rocket engine thrust chamber hot-test body module as recited in claim 3, further comprising: the connecting part (2) comprises a connecting part inner shell (201) and a connecting part outer shell (202) which are coaxially arranged, and an annular connecting plate (203) arranged between the connecting part inner shell (201) and the connecting part outer shell (202);

through holes which are uniformly distributed on the circumference are formed in the annular connecting plate (203) along the axial direction and are used as the connecting channels (205); the auxiliary coolant channel (204) is arranged between the adjacent through holes on the annular connecting plate (203);

gaps are reserved between two end faces of the annular connecting plate (203) and the rear end face of the spiral combustion chamber rib (104) and between the two end faces of the annular connecting plate and the front end face of the main spiral throat rib (34).

5. The rocket engine thrust chamber hot-test body module of claim 4, wherein: auxiliary spiral throat ribs (35) are uniformly distributed between the rear parts of the adjacent 2 main spiral throat ribs (34), the rear part of the throat cooling channel (33) is divided into 2 second throat cooling channels, and a first throat cooling channel communicated with the corresponding 2 second throat cooling channels is formed in the front part of the throat cooling channel (33);

the diameter of a circle formed by the front ends of all the auxiliary spiral throat ribs (35) is equal to that of a circle formed by the front ends of all the main spiral throat ribs (34);

the number of the combustion chamber cooling channels (103) is equal to the number of the second throat cooling channels.

6. The rocket engine thrust chamber hot-test body module of claim 5, wherein: and an annular boss (26) positioned on the front side of the outlet end of the tangential hole (242) is arranged on the inner wall of the connecting part inner shell (201).

7. The rocket engine thrust chamber hot-test body module of claim 6, wherein: the front end part of the combustion chamber (1) is provided with a butt flange (11) for butt joint with the head part of the thrust chamber;

the butt flange (11) comprises a flange inner shell and a flange outer shell which are coaxially arranged and a plurality of spiral flange ribs which are arranged between the flange inner shell and the flange outer shell and are uniformly distributed on the circumference, the number of the spiral flange ribs is equal to that of the spiral combustion chamber ribs (104), and the spiral flange ribs are in one-to-one correspondence with the spiral combustion chamber ribs;

and flange cooling channels (111) are formed among the ribs of the adjacent 2 spiral flanges, the outer wall of the flange inner shell and the inner wall of the flange outer shell, one end of each flange cooling channel (111) is communicated with the front end of the combustion chamber cooling channel (103), and the other end of each flange cooling channel is communicated with the main coolant outlet cavity (5).

8. A body module for hot testing of a rocket engine thrust chamber according to any one of claims 1 to 7, wherein: a main coolant inlet (13), an inlet temperature sensor interface (14) and an inlet pressure sensor interface (15) are arranged on the main coolant inlet cavity (4);

the main coolant outlet cavity (5) is provided with main coolant outlets (16), outlet temperature sensor interfaces (18) and outlet pressure sensor interfaces (17), the number of the main coolant outlets (16) is 3, the number of the outlet temperature sensor interfaces (18) is 2, and the main coolant outlets, the outlet temperature sensor interfaces and the outlet pressure sensor interfaces are circumferentially distributed and used for respectively mounting a low-temperature sensor and a high-temperature sensor;

an auxiliary coolant inlet (19), an auxiliary temperature sensor interface (21) and an auxiliary pressure sensor interface (20) are arranged on the auxiliary coolant cavity (6);

and a main coolant inlet cavity discharge port (22), a main coolant outlet cavity discharge port (23) and an auxiliary coolant cavity discharge port (24) are also respectively arranged on the main coolant inlet cavity (4), the main coolant outlet cavity (5) and the auxiliary coolant cavity (6).

9. A rocket engine thrust chamber hot-test body module as recited in claim 1, further comprising: the side wall of the combustion chamber shell (102) or the side wall of the throat channel shell (32) is provided with a platform (25) for mounting an acceleration sensor.

Technical Field

The invention relates to the field of hot test of a thrust chamber of a rocket engine, in particular to a body module for hot test of the thrust chamber of the rocket engine.

Background

During the design test of the thrust chamber of the rocket engine, the influence of different injector designs on the performance of the thrust chamber is often required to be examined. In order to reduce the test cost, a detachable modular design is generally adopted, and the thrust chamber is divided into a body part and a head part containing the injector so as to replace different injectors for testing.

Currently, body design usually has two forms: heat sink form and water cooled form. The heat sink type has the advantages of simple design and convenience in processing, but the defects are also obvious, and as the heat sink type does not have active cooling, the thrust chamber of the body part in the heat sink type can only carry out heat test within 5s generally only by depending on the heat capacity and high heat conductivity of materials to bear the high-temperature environment of fuel gas. When a longer thermal test (such as continuous variable working condition adjustment) needs to be carried out, the heat sink body part is difficult to meet the thermal test requirement. The water cooling mode can meet the requirement of long-time hot test, but the design and processing are complex, the cost is high, and the application is less.

Disclosure of Invention

The invention provides a hot-test body module for a rocket engine thrust chamber, which aims to solve the technical problems that the body design of the existing rocket engine thrust chamber can only carry out hot test within 5 seconds, the long-time hot test requirement is difficult to meet, or the design and processing are complex and the cost is higher.

In order to achieve the purpose, the technical scheme provided by the invention is as follows:

a body module for hot test of a thrust chamber of a rocket engine is characterized in that: the device comprises a main coolant inlet cavity, a main coolant outlet cavity, an auxiliary coolant cavity, a combustion chamber, a connecting part and a throat which are sequentially and coaxially connected from front to back along the incoming flow direction;

the combustion chamber comprises a combustion chamber inner shell and a combustion chamber outer shell which are coaxially arranged, and a plurality of combustion chamber cooling channels which are arranged between the combustion chamber outer shell and the combustion chamber inner shell and are uniformly distributed on the circumference;

the main coolant outlet cavity is arranged at the front end of the combustion chamber shell and is respectively communicated with the front ends of the plurality of combustion chamber cooling channels;

the throat comprises a throat inner shell and a throat outer shell which are coaxially arranged, and a plurality of throat cooling channels which are arranged between the throat outer shell and the throat inner shell and are uniformly distributed on the circumference;

the main coolant inlet cavity is arranged at the rear end of the throat shell and is respectively communicated with the rear ends of the plurality of throat cooling channels;

the connecting part is provided with a plurality of auxiliary coolant channels which are uniformly distributed on the circumference and a plurality of connecting channels which are uniformly distributed on the circumference, and the auxiliary coolant channels and the connecting channels are arranged in a staggered way along the circumferential direction and are not communicated; two ends of the connecting channel are respectively communicated with the rear end of the cooling channel of the combustion chamber and the front end of the throat cooling channel; each auxiliary coolant channel comprises a straight hole and a tangential hole, the inlet end of the straight hole is opened on the outer wall of the connecting part, the outlet end of the straight hole is communicated with the inlet end of the tangential hole, and the outlet end of the tangential hole is opened on the inner wall of the connecting part;

the auxiliary coolant cavity is arranged on the outer wall of the connecting part and is respectively communicated with the inlet ends of the plurality of straight holes;

the primary coolant inlet cavity, the primary coolant outlet cavity, the secondary coolant cavity, the combustion chamber, the connecting portion, and the throat are one piece.

Further, the combustion chamber cooling channel and the throat cooling channel are both of a spiral structure, and the spiral angle is 30 degrees.

Furthermore, a plurality of spiral combustion chamber ribs which are uniformly distributed on the circumference are arranged between the combustion chamber inner shell and the combustion chamber outer shell, and a combustion chamber cooling channel is formed among the 2 adjacent spiral combustion chamber ribs, the outer wall of the combustion chamber inner shell and the inner wall of the combustion chamber outer shell;

a plurality of main spiral throat ribs which are uniformly distributed on the circumference are arranged between the throat inner shell and the throat outer shell, and the throat cooling channel is formed among the adjacent 2 main spiral throat ribs, the outer wall of the throat inner shell and the inner wall of the throat outer shell;

further, the connecting part comprises a connecting part inner shell and a connecting part outer shell which are coaxially arranged and an annular connecting plate arranged between the connecting part inner shell and the connecting part outer shell;

the annular connecting plate is provided with through holes which are uniformly distributed along the circumference along the axial direction and are used as the connecting channel;

the auxiliary coolant channel is arranged between the adjacent through holes on the annular connecting plate;

gaps are reserved between the two end faces of the annular connecting plate and the rear end face of the rib of the spiral combustion chamber and between the two end faces of the annular connecting plate and the front end face of the rib of the main spiral throat.

Furthermore, auxiliary spiral throat ribs are uniformly distributed between the rear parts of the adjacent 2 main spiral throat ribs, the rear part of the throat cooling channel is divided into 2 second throat cooling channels, and a first throat cooling channel communicated with the corresponding 2 second throat cooling channels is formed in the front part of the throat cooling channel;

the diameter of the circle formed by the front ends of all the auxiliary spiral throat ribs is equal to that of the circle formed by the front ends of all the main spiral throat ribs.

The number of the combustion chamber cooling channels is equal to the number of the second throat cooling channels.

Furthermore, an annular boss located on the front side of the outlet end of the tangential hole is arranged on the inner wall of the connecting part inner shell.

Furthermore, the front end part of the combustion chamber is provided with a butt flange for butt joint with the head part of the thrust chamber;

the butt flange comprises a flange inner shell and a flange outer shell which are coaxially arranged and a plurality of spiral flange ribs which are arranged between the flange inner shell and the flange outer shell and are uniformly distributed on the circumference, the number of the spiral flange ribs is equal to that of the spiral combustion chamber ribs, and the spiral flange ribs are in one-to-one correspondence with the spiral combustion chamber ribs;

and flange cooling channels are formed among the 2 adjacent spiral flange ribs, the outer wall of the flange inner shell and the inner wall of the flange outer shell, one end of each flange cooling channel is communicated with the front end of the combustion chamber cooling channel, and the other end of each flange cooling channel is communicated with the main coolant outlet cavity.

Further, a main coolant inlet, an inlet temperature sensor interface and an inlet pressure sensor interface are disposed on the main coolant inlet cavity;

the main coolant outlet cavity is provided with 3 main coolant outlets, 2 outlet temperature sensor interfaces and 2 outlet pressure sensor interfaces, wherein the main coolant outlets are circumferentially and uniformly distributed, and the outlet temperature sensor interfaces are used for respectively mounting a low-temperature sensor and a high-temperature sensor;

an auxiliary coolant inlet, an auxiliary temperature sensor interface and an auxiliary pressure sensor interface are arranged on the auxiliary coolant cavity;

and the main coolant inlet cavity, the main coolant outlet cavity and the auxiliary coolant cavity are respectively provided with a main coolant inlet cavity discharge port, a main coolant outlet cavity discharge port and an auxiliary coolant cavity discharge port.

Furthermore, a platform is arranged on the side wall of the outer shell of the combustion chamber or the side wall of the outer shell of the throat passage and used for installing an acceleration sensor and monitoring the vibration condition in the test process.

Compared with the prior art, the invention has the advantages that:

1. the body module adopts a composite cooling mode that cooling of a main coolant channel (a throat cooling channel, a connecting channel and a combustion chamber cooling channel) is mainly adopted and film cooling (auxiliary coolant channel cooling) is adopted as auxiliary, so that the reliability of thermal protection of the body module is improved. The main cooling and the auxiliary cooling are independent, the auxiliary cooling agent is sprayed out through the auxiliary cooling agent channel, an annular liquid/gas film with good coverage is formed on the inner wall surface, the utilization rate of the cooling agent is improved, meanwhile, the throat area with severe thermal environment can be protected, and the service life is prolonged.

2. The body module of the invention adopts an integrated design, thereby reducing the processing cost, improving the reliability and meeting the long-time hot test requirement of the thrust chamber.

3. The inner wall of the inner shell of the connecting part is provided with the annular boss for preventing the liquid/gas film from being damaged by gas.

4. According to the invention, the butt flange is designed into a hollow ribbed structure, so that the butt flange can be fully cooled, the active cooling of the butt flange is realized, and the sealing reliability of the butt flange is improved.

5. Three main coolant outlets are designed, when the main coolant is heated and vaporized and the density is reduced, the flow area of the outlets is increased, and the flow speed of the outlets is reduced, so that overlarge pressure loss of the outlets is avoided; two outlet temperature sensor interfaces are designed, a low-temperature sensor and a high-temperature sensor can be respectively installed, and the temperature range capable of being monitored is enlarged.

Drawings

FIG. 1 is a cross-sectional view of a body module for thermal testing of a thrust chamber of a rocket engine of the present invention;

FIG. 2 is a schematic view of a rocket engine thrust chamber hot trial body module with the housing removed;

FIG. 3 is a sectional view taken along line A-A of FIG. 1;

FIG. 4 is an enlarged view of a portion of FIG. 1 at I;

FIG. 5 is an enlarged view of a portion of FIG. 1 at II;

FIG. 6 is a first schematic view of the configuration of the body module for hot test of the thrust chamber of the rocket engine according to the present invention;

FIG. 7 is a schematic view of the exterior structure of the body module for hot test of the thrust chamber of the rocket engine according to the present invention;

FIG. 8 is a schematic view of the spiral channels in the body module for hot testing of the thrust chamber of the rocket engine of the present invention;

FIG. 9 is a schematic view of the groove width and flow resistance curves corresponding to different helix angles in the body module for hot trial of the rocket engine thrust chamber of the present invention;

wherein the reference numbers are as follows:

1-combustion chamber, 101-combustion chamber inner shell, 102-combustion chamber outer shell, 103-combustion chamber cooling channel, 104-spiral combustion chamber rib;

2-connection, 201-connection inner shell, 202-connection outer shell, 203-annular connection plate, 204-auxiliary coolant channel, 241-straight hole, 242-tangential hole, 205-connection channel, 206-annular boss;

3-throat, 31-throat inner shell, 32-throat outer shell, 33-throat cooling channel, 34-main spiral throat rib and 35-auxiliary spiral throat rib;

4-primary coolant inlet cavity, 5-primary coolant outlet cavity, 6-secondary coolant cavity; 11-counterflange, 111-flange cooling channel, 12-flange seal, 13-primary coolant inlet, 14-inlet temperature sensor interface, 15-inlet pressure sensor interface, 16-primary coolant outlet, 17-outlet pressure sensor interface, 18-outlet temperature sensor interface, 19-secondary coolant inlet, 20-secondary pressure sensor interface, 21-secondary temperature sensor interface, 22-primary coolant inlet cavity discharge, 23-primary coolant outlet cavity discharge, 24-secondary coolant cavity discharge, 25-platform.

Detailed Description

The invention is described in further detail below with reference to the figures and specific embodiments.

The invention relates to a body module for a hot test of a thrust chamber of a rocket engine, which comprises a body and a cavity.

From the structural point of view, the body of this embodiment adopts inside and outside double-deck ribbed structure, including inner shell, shell and setting up the rib between inner shell and shell, and the coolant flows along the passageway that is formed between inner shell, shell and the adjacent rib.

As shown in fig. 1 and 2, the body includes a combustion chamber 1, a connecting portion 2, and a throat 3, which are coaxially connected in order from front to back in the gas flow direction (incoming flow direction).

The combustor 1 includes a combustor inner casing 101 and a combustor outer casing 102 that are coaxially arranged and a plurality of spiral combustor ribs 104 that are arranged between the combustor inner casing 102 and the combustor inner casing 101 and are circumferentially and evenly distributed, combustor cooling channel 103 is formed by the outer wall of the combustor inner casing 101 and the inner wall of the combustor outer casing 102 between 2 adjacent spiral combustor ribs 104 and between the 2 adjacent spiral combustor ribs 104, in this embodiment, the spiral combustor ribs 104 are designed to be spiral, and then the combustor cooling channel 103 is a spiral channel, which can improve the cooling effect.

The throat 3 comprises a throat inner shell 31 and a throat outer shell 32 which are coaxially arranged, and a plurality of main spiral throat ribs 34 which are arranged between the throat outer shell 32 and the throat inner shell 31 and are uniformly distributed on the circumference, wherein the outer wall of the throat inner shell 31 and the inner wall of the throat outer shell 32 between every two adjacent main spiral throat ribs 34 and between every two adjacent main spiral throat ribs 34 form a throat cooling channel 33, and the throat cooling channel 33 is a spiral channel because the main spiral throat ribs 34 are spiral.

As shown in fig. 3 and 4, the connecting portion 2 includes a connecting portion inner shell 201 and a connecting portion outer shell 202 which are coaxially arranged, and an annular connecting plate 203 arranged between the connecting portion inner shell 201 and the connecting portion outer shell 202, and gaps are respectively present between two end surfaces of the annular connecting plate 203 and the rear end surface of the spiral combustor rib 104 and the front end surface of the main spiral throat rib 34; a plurality of auxiliary coolant channels 204 which are uniformly distributed on the circumference and a plurality of connecting channels 205 which are uniformly distributed on the circumference are arranged on the annular connecting plate 203, and the auxiliary coolant channels 204 and the connecting channels 205 are arranged in a staggered way along the circumferential direction and are not communicated; each auxiliary coolant channel 204 comprises a straight hole 241 and a tangential hole 242, wherein the inlet end of the straight hole 241 is opened on the outer wall of the connecting part outer shell 202, the outlet end of the straight hole is communicated with the inlet end of the tangential hole 242, and the outlet end of the tangential hole 242 is opened on the inner wall of the connecting part inner shell 201; through holes (windows) uniformly distributed circumferentially are formed in the annular connecting plate 203 at positions between adjacent auxiliary coolant channels 204 along the axial direction to serve as connecting channels 205 for main coolant to pass through, and two ends of each connecting channel 205 are respectively communicated with the rear end of the combustion chamber cooling channel 103 and the front end of the throat cooling channel 33.

Functionally, the body module of this embodiment has three cavities, be main coolant inlet cavity 4, main coolant outlet cavity 5, supplementary coolant cavity 6 respectively, and three cavities all set up in the outside of shell, and are the annular. The main coolant outlet cavity 5 is arranged at the front end of the combustor casing 102 and is communicated with the front ends of the plurality of combustor cooling channels 103 respectively; the main coolant inlet cavity 4 is arranged at the rear end of the throat housing 32 and is communicated with the rear ends of the plurality of throat cooling channels 33 respectively; the auxiliary coolant cavity 6 is disposed on the outer wall of the connecting portion 2 and is respectively communicated with the inlet ends of the plurality of straight holes 241.

The main coolant enters from the main coolant inlet cavity 4, flows through the throat cooling channel 33, the connecting channel 205, the combustion chamber cooling channel 103, and then flows out from the main coolant outlet cavity 5 for cooling the inner walls (body inner walls: the combustion chamber inner shell 101, the connecting portion inner shell 201, the throat inner shell 31) which are in contact with the high-temperature gas.

The auxiliary coolant enters from the auxiliary coolant cavity 6, flows through the straight holes 241 and the tangential holes 242 between the connecting part inner shell 201 and the connecting part outer shell 202, and then is sprayed out from the inner surface of the connecting part inner shell 201 to form an annular liquid/gas film for protecting the throat area with a severe thermal environment.

In the embodiment, the main coolant channel and the auxiliary coolant channel are mutually independent, the film coolant enters the combustion chamber through the tangential holes 242, and a liquid/gas film with good coverage is formed on the wall surface, so that the utilization rate of the coolant is improved; the present embodiment provides an annular boss 206 on the inner wall of the inner shell 201 of the connector portion upstream of the tangential hole 242 to prevent the gas from flushing the liquid/gas film.

The main coolant and the auxiliary coolant can be selected from the same coolant or different coolants.

As shown in fig. 8, assuming that the diameter of the bottom surface where the spiral groove (spiral channel) is formed between adjacent ribs is d, the included angle between the spiral groove and the axis of the thrust chamber is α, the width of the spiral groove (perpendicular to the direction of the groove) is a, the width of the spiral rib (perpendicular to the direction of the groove) is b, and the number of grooves is n, the following relationships are provided:

a＝π*d/n*cos(α)-b

in order to ensure the uniformity of the cooling effect in the circumferential direction, the number of the grooves should be as large as possible, but at the same time, due to the current process limitation of additive manufacturing, the groove width and the rib width cannot be smaller than 1mm, and the helix angle α cannot be larger than 45 °, so that the number of the grooves n, the groove width a, the rib width b and the helix angle α are restricted with each other when the bottom surface diameter d is determined.

In addition, in the case of a constant coolant flow rate, the spiral groove can increase the coolant flow rate and enhance the cooling effect, but the spiral angle is not so small as to be remarkable, so the spiral angle is generally not less than 20 degrees. And, the larger the helix angle, the larger the coolant flow rate, but the greater the flow resistance, which burdens the coolant supply system.

In this embodiment, the throat 3 includes a throat portion and an expansion portion coaxially connected to the rear end of the throat portion, the diameter of the throat portion gradually decreases from both ends to the middle portion, and the front end of the throat portion is connected to the rear end of the connection portion 2; the size of the helix angle is determined by the throat region due to the smallest diameter of the floor in which the throat channel is located. In the throat area, the number of the grooves is selected to be 60, the rib width is selected to be 1mm, and the groove width a and the flow resistance corresponding to different helix angles alpha are as follows:

helix angle/degree	Groove width/mm	Flow resistance/MPa
			20	1.44	0.536
25	1.35	0.632
			30	1.26	0.78
35	1.13	1.02
			40	0.99	1.44
45	0.84	2.23

Fig. 9 is a schematic view of the groove width a and the flow resistance corresponding to different helix angles α, and it can be seen from fig. 9 that the groove width a is less than 1mm when the helix angle is above 40 °, and therefore the helix angle needs to be less than 40 °. However, the flow resistance is significantly increased when the helix angle is 35 ° compared to 30 °, so considering comprehensively, if the helix angle is designed to be 30 °, the cooling effect is better, and the flow resistance is smaller, the helix angles of the spiral combustion chamber rib 104 and the main spiral throat rib 34 in this embodiment are both designed to be 30 °.

The outer circle surface space of the corresponding expansion part is much larger than that of the throat part, therefore, in order to improve the cooling effect of the expansion part, 1 auxiliary spiral throat rib 35 is uniformly distributed between the rear parts of the adjacent 2 main spiral throat ribs 34 (namely, the 2 main spiral throat ribs 34 positioned at the expansion part), the rear part of the throat cooling channel 33 is divided into 2 second throat cooling channels, and the front part of the throat cooling channel 33 (the throat cooling channel 33 positioned at the throat part) forms a first throat cooling channel communicated with the corresponding 2 second throat cooling channels; the diameter of the circle formed by the front ends of all the auxiliary spiral throat ribs is equal to that of the circle formed by the front ends of all the main spiral throat ribs. Accordingly, the number of spiral combustion chamber ribs 104 of the combustion chamber 1 is equal to the number of ribs of the expansion section at the rear of the throat 3 (the sum of the number of main spiral throat ribs and auxiliary spiral throat ribs), and the number of combustion chamber cooling channels 103 is equal to the number of second throat cooling channels.

As shown in fig. 5, the front end of the combustion chamber 1 is designed with a docking flange 11 for docking with the head of the thrust chamber. The connection region of the butt flange 11 and the combustion chamber inner shell 101 and the combustion chamber outer shell 102 is designed to be a hollow ribbed structure, specifically, the butt flange 11 comprises a flange inner shell and a flange outer shell which are coaxially arranged and a plurality of spiral flange ribs which are arranged between the flange inner shell and the flange outer shell and are uniformly distributed on the circumference, the number of the spiral flange ribs is equal to that of the spiral combustion chamber ribs 104, and the positions of the spiral flange ribs are in one-to-one correspondence; the flange cooling channel 111 is formed by the outer wall of the flange inner shell and the inner wall of the flange outer shell between every two adjacent 2 spiral flange ribs and between every two adjacent 2 spiral flange ribs, the front end of the flange cooling channel 111 is communicated with the front end of the combustion chamber cooling channel 103, the rear end of the flange cooling channel is communicated with the main coolant outlet cavity 5, and an arrow dotted line shown in figure 5 is the flowing direction of the main coolant.

As shown in fig. 6 and 7, the main coolant inlet chamber 4 is provided with a main coolant inlet 13, an inlet temperature sensor interface 14 and an inlet pressure sensor interface 15; the inlet temperature sensor interface 14 and the inlet pressure sensor interface 15 are used to arrange temperature and pressure sensors, respectively, to monitor the coolant temperature and pressure within the main coolant inlet cavity 4.

The main coolant outlet cavity 5 is provided with a main coolant outlet 16, an outlet temperature sensor interface 18 and an outlet pressure sensor interface 17, the outlet temperature sensor interface 18 and the outlet pressure sensor interface 17 being respectively used for arranging a temperature sensor and a pressure sensor for monitoring the coolant temperature and pressure in the main coolant outlet cavity 5. The main coolant outlet 16 comprises three outlets in order to increase the outlet flow area and reduce the outlet flow rate when the main coolant is heated to boil off and the density decreases, thereby avoiding excessive outlet pressure losses. Two outlet temperature sensor interfaces 18 are also arranged, and a low temperature sensor and a high temperature sensor can be respectively installed, so that the temperature range which can be monitored is enlarged.

An auxiliary coolant inlet 19, an auxiliary temperature sensor interface 21 and an auxiliary pressure sensor interface 20 are arranged on the auxiliary coolant cavity 6; the auxiliary temperature sensor interface 21 and the auxiliary pressure sensor interface 20 are respectively provided with a temperature sensor and a pressure sensor for monitoring the temperature and pressure of the coolant in the auxiliary coolant cavity 6.

Further, a main coolant inlet cavity discharge port 22, a main coolant outlet cavity discharge port 23 and a secondary coolant cavity discharge port 24 are disposed on the main coolant inlet cavity 4, the main coolant outlet cavity 5 and the secondary coolant cavity 6, respectively. When the body module is installed on the test bed, the main coolant inlet cavity discharge port 22, the main coolant outlet cavity discharge port 23 and the auxiliary coolant cavity discharge port 24 face downwards, the discharge ports are plugged by plugs during testing, and after the testing is finished, the plugs are detached to discharge the coolant accumulated in the cavity.

The side wall of the combustion chamber housing 102 or the side wall of the throat housing 32 of the present embodiment is provided with a platform 25, and an acceleration sensor can be arranged for monitoring the vibration condition of the body module in the test process.

The whole body module of the embodiment is a part and is manufactured by adopting an additive manufacturing technology, and the material can be selected from high-temperature alloys, such as GH4169, GH4202 and GH 3536. The body module is based on the integrated design of the additive manufacturing technology, the channel (between adjacent ribs) external cooling and the liquid/air film composite cooling are adopted, the integration of the inner wall and the outer wall is realized, the composite cooling mode with the channel external cooling as a main mode and the film cooling as an auxiliary mode is adopted, the processing cost is reduced, the reliability is improved, and the long-time hot test requirement of the thrust chamber can be met. The film cooling adopts an independent supply mode and is independent from the external cooling of the channel, the film cooling agent enters the combustion chamber through the tangential holes, and a liquid/gas film with good coverage is formed on the wall surface, so that the utilization rate of the cooling agent is improved.

The above description is only for the preferred embodiment of the present invention and does not limit the technical solution of the present invention, and any modifications made by those skilled in the art based on the main technical idea of the present invention belong to the technical scope of the present invention.