CN113431710B

CN113431710B - Reversing valve of liquid rocket engine and liquid rocket engine

Info

Publication number: CN113431710B
Application number: CN202110542934.8A
Authority: CN
Inventors: 李莹; 陈涛; 任志彬; 王喜良; 张思远; 李欢; 刘耀林; 范宇; 薛海龙
Original assignee: Lanjian Spaceflight Technology Co ltd
Current assignee: Lanjian Spaceflight Technology Co ltd
Priority date: 2021-05-19
Filing date: 2021-05-19
Publication date: 2022-06-17
Anticipated expiration: 2041-05-19
Also published as: CN113431710A

Abstract

The invention provides a reversing valve of a liquid rocket engine and the liquid rocket engine. The inner side of the auxiliary shell is provided with a first channel for the gas medium to flow through and a second channel with the extending direction different from that of the first channel; the main shell is provided with a first medium inlet, a first medium outlet and a second medium outlet; the sealing element is sleeved on the surface of the thrust assembly, and the outer side surface of the sealing element is mutually abutted with the inner wall of the auxiliary shell; one end of the thrust assembly is arranged in the auxiliary shell through a sealing piece, and the other end of the thrust assembly is used for pushing the valve main body in the main shell to move; the sealing element is a flooding ring, the flooding ring comprises a main body part, an annular accommodating part and an elastic element, the elastic element is arranged in the annular accommodating part, and an annular bulge for matching and abutting against the elastic element is arranged on the inner wall of the annular accommodating part; the circumferential outer surface of the main body portion is provided with an annular recess. Compared with the prior art, the sealing effect can be improved, and the loss of the liquid medium can be reduced.

Description

Reversing valve of liquid rocket engine and liquid rocket engine

Technical Field

The invention relates to the technical field of valves, in particular to a reversing valve of a liquid rocket engine and the liquid rocket engine.

Background

With the rapid development of the aerospace industry, all the technologies related to the rocket field also realize the rapid advance. The valve is an important part for realizing the starting and shutdown of the liquid rocket engine. The medium of the low-temperature liquid rocket engine is an ultralow-temperature propellant, the medium temperature range is usually about 20K-120K, and the pressure is more than 10 MPa. The valve operating gas is usually a high-pressure gas having a pressure of about 20 MPa.

Liquid propellant used by the existing domestic active low-temperature liquid rocket engine adopts liquid methane as propellant besides liquid hydrogen, liquid oxygen and the like. To facilitate the use of propellant, it is often applied to diverter valves which normally effect the expulsion of propellant from various outlets of the valve by the movement of an internal flap of the valve. During the movement, the thrust assembly is required to provide thrust for the valve, and the thrust assembly can be in direct contact with the inner wall of the valve. In order to ensure tight sealing, a dynamic sealing element is usually required between the thrust assembly and the inner wall of the valve. For example, the dynamic sealing element may be implemented as a metal bellows or a precious metal-coated sealing ring. The valve is actuated by high pressure helium gas, and the control gas is required to keep the state after the valve is actuated in place. However, the large-size metal corrugated pipe is difficult to form, long in production period, large in space structure, high in purchasing cost, low in service life, poor in reliability and the like. In addition, the design of the noble metal coating sealing ring is adopted, so that the friction force is overlarge, and the service efficiency of the valve is influenced.

It is desirable to provide a valve structure suitable for low temperature environment and having a state maintaining function.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provides a reversing valve of a liquid rocket engine and the liquid rocket engine. The valve device can improve the sealing effect and reduce the loss of gas medium, thereby improving the working reliability and efficiency of the rocket engine.

One aspect of the present invention provides a reversing valve for a liquid rocket engine, comprising a secondary housing, a primary housing, a seal, a thrust assembly, and a valve body, wherein,

the inner side of the auxiliary shell is provided with a first channel for the gas medium to flow through and a second channel with the extending direction different from that of the first channel;

the main housing has a first media inlet, a first media outlet and a second media outlet;

the sealing element is sleeved on the surface of the thrust assembly, and the outer side surface of the sealing element is mutually abutted with the inner wall of the auxiliary shell;

one end of the thrust assembly is arranged in the auxiliary shell through the sealing element, and the other end of the thrust assembly is used for pushing the valve main body in the main shell to move; the sealing element is a general plunger ring, the general plunger ring at least comprises a first general plunger ring and a second general plunger ring which are sequentially arranged along the axial direction of the thrust assembly, the first general plunger ring and the second general plunger ring are mutually clung, wherein,

the flooding plug ring comprises a main body part, an annular accommodating part surrounding the axial direction of the thrust assembly and an elastic piece, wherein the elastic piece is arranged in the annular accommodating part, and an annular bulge used for being matched and abutted to the elastic piece is arranged on the inner wall of the annular accommodating part;

the circumferential outer surface of the main body part is provided with an annular concave part;

the air flow enters from the side far away from the valve main body through the first channel, and pushes the thrust assembly to drive the valve main body to move towards the direction far away from the auxiliary shell, so that the first medium inlet and the second medium outlet on the main shell are communicated;

and the airflow enters through the second channel to push the thrust assembly and the valve main body to move towards the direction close to the auxiliary shell, so that the first medium inlet is communicated with the first medium outlet.

Furthermore, the number of the annular concave parts is A, and A is more than or equal to 1 and less than or equal to 4.

Further, one side surface of the main body part close to the annular accommodating part is matched and attached with the elastic piece so as to prevent the elastic piece from moving.

Furthermore, the shape of the annular bulge is isosceles trapezoid along the radial direction of the annular bulge.

Further, the end part of the annular bulge is of a bent arc structure.

Furthermore, the section of the curved arc structure tangent along the axial direction is a half ellipse, the length of the long axis of the half ellipse is B, the length of the short axis of the half ellipse is C, and B/C is more than or equal to 2 and less than or equal to 4.

Further, the annular bulge at least comprises 2, and 2 the annular bulge is arranged on the inner wall of the annular accommodating part at equal intervals along the axial direction of the thrust assembly.

Furthermore, the valve further comprises a first spring and a cover plate, wherein the first spring is located inside the main shell, the cover plate is located on one side, away from the auxiliary shell, of the main shell, the cover plate is connected with the main shell through a bolt, two ends of the first spring are respectively connected with the valve main body and the cover plate, and the first spring is used for pushing the valve main body to move towards one side, away from the cover plate.

Further, a first sealing ring and a second sealing ring are arranged on the circumferential surface of the thrust assembly at intervals at the inner side of the main shell and close to the position of the auxiliary shell.

Another aspect of the invention provides a liquid rocket engine including a reversing valve mechanism as described above for a liquid rocket engine.

According to the reversing valve mechanism of the liquid rocket engine provided by the embodiment of the invention, the flooding plug ring is sleeved on the surface of the thrust assembly, and the outer side surface of the flooding plug ring is mutually abutted with the inner wall of the auxiliary shell; one end of the thrust component is arranged in the auxiliary shell through the universal piston ring, and the other end of the thrust component is used for pushing the valve main body in the main shell to move. By adopting the reversing valve mechanism, when a high-pressure gas medium enters from the auxiliary shell, the thrust component is pushed to move so as to apply pressure to the valve main body to change the outlet position of the liquid medium, and the universal plug ring is used for sealing between the auxiliary shell and the thrust component, so that the high-pressure gas medium can be prevented from leaking into the main shell from a gap between the auxiliary shell and the thrust component, on one hand, the impact of the high-pressure gas medium on the valve main body can be reduced, and the discharge of the liquid medium can be accurately controlled; on the other hand, the gas supply (leakage reduction) can be reduced, and the manufacturing difficulty of the gas storage device can be reduced. An annular recess is provided through the circumferential outer surface of the main body portion. Due to the design of the annular concave portion, the universal plug ring can move quickly along with the thrust assembly, the contact area of the main body portion and the auxiliary shell can be reduced, and then friction force between the universal plug ring and the auxiliary shell is reduced, so that the universal plug ring can move quickly along with the thrust assembly. In addition, due to the design of the annular bulge, pressure applied to the elastic piece can be conveniently and quickly transmitted to the annular accommodating part through the annular bulge, so that the annular accommodating part is quickly attached to the inner wall of the auxiliary shell to achieve the effect of quick sealing, and high-pressure gas leakage is avoided. The whole valve structure can improve the sealing effect, reduce the loss of gas medium, is convenient to process, and can save the cost, thereby further improving the performance of the liquid rocket engine and improving the working reliability and efficiency of the liquid rocket engine.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description, serve to explain the principles of the invention.

FIG. 1 is a schematic structural diagram of a reversing valve according to an embodiment of the invention;

FIG. 2 is a schematic view of the seal and thrust assembly attachment configuration of an embodiment of the present invention;

FIG. 3 is a perspective view of an annular protrusion in an embodiment of the present invention;

FIG. 4 is a schematic view of a curved structure in an embodiment of the present invention;

FIG. 5 is an enlarged partial schematic view of a stopper ring in an embodiment of the present invention;

FIG. 6 is a top view of a stopper ring in an embodiment of the present invention;

FIG. 7 is a graph showing the variation of the sealing strength according to the number of the annular recessed portions in the embodiment of the present invention.

Description of the reference numerals:

1 sub-housing 2 Main housing

3 sealing element 4 thrust assembly

5 valve body 6 first medium inlet

7 first medium outlet 8 second medium outlet

9 drain channel 10 body part

11 annular receiving part 12 elastic member

13 annular projection 14 annular recess

15 spring 16 cover plate

17 first seal ring 18 second seal ring

19 curved arc structure

Detailed Description

Reference will now be made in detail to various exemplary embodiments of the invention, the detailed description should not be construed as limiting the invention but as a more detailed description of certain aspects, features and embodiments of the invention.

It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.

One aspect of the present invention provides a reversing valve for a liquid rocket engine, as shown in fig. 1, 2, 3, 5 and 6, the mechanism is composed of a sub-housing 1, a main housing 2, a seal 3, a thrust assembly 4 and a valve body 5. The inner side of the sub-housing 1 has a first passage through which a gas medium flows and a second passage extending in a direction different from the first passage. The main housing 2 has a first medium inlet 6, a first medium outlet 7 and a second medium outlet 8. The sealing element 3 is sleeved on the surface of the thrust assembly 4, and the outer side surface of the sealing element 3 is abutted against the inner wall of the auxiliary shell 1. One end of a thrust assembly 4 is arranged in the auxiliary shell 1 through a sealing piece 3, and the other end of the thrust assembly is used for pushing a valve main body 5 in the main shell 2 to move; sealing member 3 is general stopper circle, and general stopper circle contains two first general stopper circles and the general stopper circle of second that set gradually along the thrust subassembly axial at least, and first general stopper circle and the general stopper circle of second hug closely each other. The stopper ring comprises a main body part 10, an annular accommodating part 11 surrounding the axial direction of the thrust assembly and an elastic piece 12, wherein the elastic piece 12 is arranged in the annular accommodating part 11, and the inner wall of the annular accommodating part 11 is provided with an annular bulge 13 for matching and abutting against the elastic piece 12. The circumferential outer surface of the main body portion 10 is provided with an annular recess 14.

Specifically, according to the reversing valve of the liquid rocket engine provided by the embodiment of the invention, the flooding plug ring is sleeved on the surface of the thrust assembly 4, and the outer side surface of the flooding plug ring is mutually abutted with the inner wall of the auxiliary shell 1; one end of the thrust component 4 is arranged in the auxiliary shell 1 through a stopper ring, and the other end is used for pushing the valve main body 5 in the main shell 2 to move. In the whole process, when a high-pressure gas medium enters from the auxiliary shell, the thrust component 4 is pushed to move to apply pressure to the valve main body 5 so as to change the outlet position of the liquid medium, and the universal plug ring is used for sealing between the auxiliary shell 1 and the thrust component 4, so that the high-pressure gas medium can be prevented from leaking into the main shell 2 from a gap between the auxiliary shell 1 and the thrust component 4, on one hand, the impact of the high-pressure gas medium on the valve main body 5 can be reduced, and the discharge of the liquid medium can be accurately controlled; on the other hand, the gas supply (leakage reduction) can be reduced, the volume and the pressure of the gas storage device can be reduced, and the manufacturing difficulty of the gas storage device can be further reduced. An annular recess 14 is provided through the circumferential outer surface of the main body portion 10. Due to the design of the annular concave portion, the universal plug ring can move rapidly along with the thrust assembly 4, the contact area between the main body portion 10 and the auxiliary shell 1 can be reduced, the friction force between the universal plug ring and the auxiliary shell 1 is reduced, and the universal plug ring can move rapidly along with the thrust assembly conveniently. In addition, due to the design of the annular protrusion, the pressure applied to the elastic part 12 can be conveniently and quickly transmitted to the annular accommodating part through the annular protrusion 13, so that the annular accommodating part 11 is quickly attached to the inner wall of the auxiliary shell 1, the effect of quick sealing is achieved, and high-pressure gas leakage is avoided.

The valve structure can improve the sealing effect, reduce the loss of gas medium, is convenient to process, and can save the cost, thereby further improving the performance of the liquid rocket engine and improving the working reliability and efficiency of the liquid rocket engine.

It should be noted that, in order to further increase the sealing degree and reduce the gas leakage from the gap between the thrust assembly 4 and the inner wall of the sub-housing 1, for example, the flooding ring at least includes a first flooding ring and a second flooding ring which are sequentially arranged along the axial direction of the thrust assembly 4, and the first flooding ring and the second flooding ring are tightly attached to each other. Through the design of the general stopper of first general stopper circle and second, increased general stopper circle and vice casing 1 and thrust unit 4's area of contact, can reduce high-pressure gas medium's leakage, improve the stability of valve, and then guarantee liquid rocket engine's safe handling.

In the present embodiment, in order to facilitate the expansion and contraction of the jamming ring (expansion and contraction in the radial direction of the thrust assembly 4), for example, the jamming ring includes a main body portion 10, an annular housing portion 11 surrounding the axial direction of the thrust assembly 4, and an elastic member 12, and the elastic member 12 is provided in the annular housing portion 11. In order to enable the universal plug ring to be connected with the thrust assembly 4 more tightly and firmly (in use, the universal plug ring needs to move along with the thrust assembly 4 along the axial direction), for example, the universal plug ring is connected with the thrust assembly 4 in an interference fit manner. It is worth mentioning that, in order to make things convenient for annular accommodating part 11 to hug closely with thrust unit 4 and sub-housing 1, for example, elastic component 12 can be the spring, because the valve need work under low temperature environment, under high pressure state, through the spring inflation, can extrude annular accommodating part 11, and then make annular accommodating part 11 hug closely with thrust unit 4 and sub-housing 1, when reducing the gas medium leakage, conveniently turn to the use of valve.

The annular housing 11 is made of soft metal or non-metal material, such as soft metal indium, aluminum, copper, silver, etc., non-metal tetrafluoro, rubber, etc. The large non-metallic shrinkage at low temperatures results in a decrease in sealing performance at low temperatures. The compression amount of the energy storage spring is increased by the contraction of the annular protrusion 13, so that the load is increased, the sealing specific pressure of the sealing ring at low temperature is improved, and the sealing performance at low temperature is ensured.

In the present embodiment, in order to quickly make the spring obtain pressure, for example, the opening direction of the annular accommodating part of the first stopper ring away from the end of the main body part 10 is consistent with the axial direction of the thrust assembly 4, so that the spring is conveniently pressed by high-pressure gas, and the spring is conveniently and quickly deformed (expanded). Further, in order to avoid backflow of gas entering from the gas inlet passage in the sub-housing 1 (for pushing the thrust assembly to move away from the valve main body side) from the gap between the thrust assembly 4 and the sub-housing 1 to the gas inlet end (the inlet at which high-pressure gas enters along the first passage), for example, the opening of the annular accommodating portion of the second jamming ring opens to the side away from the first jamming ring. Namely, the openings of the two stopper rings are arranged oppositely.

Note that, since the valve operates in a low-temperature environment, in a high-pressure state, for convenience of the spring applying pressure to the annular accommodating portion 11 (which has thermal expansion and contraction properties), for example, the inner wall of the annular accommodating portion 11 is provided with an annular protrusion 13 for fitting against the elastic member 12. Through the design of the annular bulge 13, when the elastic piece is pressed and expanded, the time required by the contact between the elastic piece 12 and the annular accommodating part 12 is reduced (the expansion spring is quickly acted on the inner wall of the auxiliary shell through the annular bulge 13), and then the annular accommodating part 12 is quickly attached to the inner wall of the auxiliary shell 1, and further the leakage of high-pressure gas medium is further reduced.

It is worth mentioning that, as shown in fig. 1, fig. 2, fig. 3 and fig. 7, through a great deal of research, through experimental simulation and practice, it is found that the X axis is the annular concave portion, the Y axis is the sealing strength, the sealing strength changes along with the occurrence curve of the increase of the number of the annular concave portions, the number of the annular concave portions 14 can be 1 or 2, when the number of the annular concave portions 14 is a, and it is satisfied that a is not less than 1 and not more than 4, the sealing effect of the flooding ring is tighter, that is, the sealing effect between the flooding ring and the auxiliary shell is not affected, and the movement is more convenient.

It should be noted that, in order to avoid the elastic member 12 from moving in the axial direction, for example, a side surface of the main body 10 close to the annular accommodating portion 11 is in fit engagement with the elastic member 12 to prevent the elastic member 12 from moving.

In addition, it is to be noted that, in order to ensure the structural stability of the annular projection 13, for example, the outer shape of the annular projection 13 that is truncated in the radial direction of the annular projection is an isosceles trapezoid. Because isosceles trapezoid's design for elastic component 12 is when contacting and exerting pressure with annular protrusion 13, avoid causing the bellied 13 of annular bending (axial direction) because of pressure is too big, isosceles trapezoid follows the top (the bottom for keeping away from the one end on annular portion of holding surface) to the volume increase of bottom (the bottom is for being close to the one end of annular portion of holding) promptly, under the same pressure condition, pressure diminishes gradually, thereby guarantee the structure more stable, avoid taking place crooked, be favorable to general stopper ring's safe handling, and then improve the stability of valve.

It should be noted that in order to allow the elastic member 12 to rapidly apply pressure to the annular projection 13, while further improving the sealing effect, the end of the annular projection 13 is provided with a curved structure 19.

It is further noted that, as shown in fig. 1, 2, 3, 4 and 5, the cross section of the curved-arc structure 19 tangential along the axial direction may be a half ellipse after a lot of experimental studies. For example, the length of the major axis of the half ellipse is B, the length of the minor axis is C, and when 2/C is equal to or greater than 4, the curved structure 19 is more stable, and meanwhile, the pressure applied to the elastic member 12 is rapidly transmitted to the annular accommodating part through the annular protrusion 13, so that the annular accommodating part 11 is rapidly attached to the inner wall of the auxiliary housing 1, and the effect of rapid sealing is achieved, and high-pressure gas leakage is avoided.

It should be noted that, in order to ensure stable contact between the elastic member 12 and the annular protrusion 13, for example, the annular protrusion 13 includes at least 2, and 2 annular protrusions 13 are provided on the inner wall of the annular accommodating portion 11 at intervals along the axial direction of the thrust assembly 4. For example, the outer surface of the elastic member 12 abuts against the two annular protrusions 13, respectively. In addition, two annular protrusion 13 cooperation settings play the spacing groove effect of direction (two annular protrusion that the interval set up promptly contradict with the elastic component, can restrict the axial motion of elastic component) for elastic component 12 removes along the spacing groove of direction when the atress inflation or the shrink for further avoiding elastic component 12 axial displacement to appear, and then be convenient for exert pressure to annular accommodation portion 11, prevent that the propellant from revealing between the outer wall of inferior casing 2 and annular accommodation portion 11.

In addition, the steering valve mechanism further comprises a first spring 15 and a cover plate 16, wherein the first spring 15 is positioned inside the main shell 2, and the cover plate 16 is positioned on the side, away from the auxiliary shell 1, of the main shell 2. The cover plate 16 is bolted to the main housing 2, and the first spring 15 is connected at both ends to the valve main body 5 and the cover plate 16, respectively. The first spring 15 is used for applying elastic force to the valve main body 5 at the side far away from the cover plate 16, so that the force balance of the valve main body under the action of the thrust assembly and the spring elastic force is realized. In order to facilitate the movement of the main valve body 5, for example, an air inlet passage is provided on the auxiliary housing 1, and air is vented through the air inlet passage to push the thrust assembly 4 to drive the sealing member 3 to move towards the side away from the main housing 2.

In addition, in order to limit the axial movement of the jamming ring to damage the main casing 2, for example, a step for limiting the movement of the jamming ring to the main casing 2 side is formed at the transition portion between the sub-casing 1 and the main casing 2. Further, in order to avoid general stopper circle and step direct contact and cause the damage, for example, can set up the buffering clamping ring on thrust unit 4 and near step one side for alleviate general stopper circle and the direct pressure of step, and then guarantee the safe operation of valve body.

In addition, a first sealing ring 17 and a second sealing ring 18 are arranged on the circumferential surface of the thrust assembly 4 at intervals on the inner side of the main shell 2 and close to the auxiliary shell 1, wherein the first sealing ring 17 is used for further sealing the thrust assembly 4, so that high-pressure gas is prevented from leaking from a gap between the main shell 2 and the thrust assembly 4. And the second sealing ring 18 can prevent the liquid medium from flowing back into the auxiliary shell from the gap between the main shell 2 and the thrust assembly 4, thereby influencing the stability and safety of the steering valve.

The first seal ring 1 and the second seal ring 17 are located on both sides of a drain passage provided in the radial direction of the main casing 2, and the drain passage 9 is used to discharge the liquid medium leaking from the gap between the main casing 2 and the thrust assembly 4 from the drain passage 9.

As a low-temperature dynamic sealing structure of a liquid rocket engine, the first sealing ring 1 and the second sealing ring 17 are required to be applicable to the temperature range from minus 268 ℃ to 427 ℃, have stable performance and do not react with a liquid medium. For example, the first and second sealing rings may be soft metal indium, aluminum, copper, silver, etc., nonmetal tetrafluoro, rubber, etc.

The above embodiments may be combined with each other with corresponding technical effects.

Another aspect of the invention provides a liquid rocket engine comprising a reversing valve as above.

The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.

Claims

1. A reversing valve mechanism of a liquid rocket engine is characterized by comprising an auxiliary shell, a main shell, a sealing element, a thrust assembly and a valve main body, wherein,

one end of the thrust assembly is arranged in the auxiliary shell through the sealing element, and the other end of the thrust assembly is used for pushing the valve main body in the main shell to move; the sealing element is a plunger ring;

the stopper ring at least comprises a first stopper ring and a second stopper ring which are sequentially arranged along the axial direction of the thrust assembly, and the first stopper ring and the second stopper ring are mutually clung, wherein,

the universal plug ring comprises a main body part, an annular accommodating part surrounding the thrust assembly and an elastic piece, wherein the elastic piece is arranged in the annular accommodating part, and an annular bulge for being matched and abutted with the elastic piece is arranged on the inner wall of the annular accommodating part;

the air flow enters through the second channel to push the thrust assembly and the valve main body to move towards the direction close to the auxiliary shell, so that the first medium inlet is communicated with the first medium outlet;

the shape of the annular bulge intersected along the radial direction is an isosceles trapezoid;

the end part of the annular bulge is of a bent arc structure;

the section of the curved arc structure tangent along the axial direction is a half ellipse, the length of the long axis of the half ellipse is B, the length of the short axis of the half ellipse is C, and B/C is more than or equal to 2 and less than or equal to 4.

2. The reversing valve mechanism for a liquid rocket engine according to claim 1, wherein: the number of the annular concave parts is A, and A is more than or equal to 1 and less than or equal to 4.

3. The reversing valve mechanism for a liquid rocket engine according to claim 1, wherein: one side surface of the main body part close to the annular accommodating part is matched and attached with the elastic piece so as to prevent the elastic piece from moving.

4. The reversing valve mechanism for a liquid rocket engine according to claim 1, wherein: the annular bulge at least comprises 2, and the annular bulge is arranged on the inner wall of the annular accommodating part at equal intervals along the axial direction of the thrust assembly.

5. The reversing valve mechanism for a liquid rocket engine according to claim 1, wherein: still contain first spring and apron, first spring all is located the inside of the main casing body, the apron is located the main casing body is kept away from one side of vice casing, the apron with the main casing body passes through bolted connection, first spring both ends respectively with the valve main part with the cover connection, first spring is used for promoting the valve main part is to keeping away from apron one side removes.

6. The reversing valve mechanism for a liquid rocket engine according to claim 1, wherein: the inner side of the main shell body is close to the position of the auxiliary shell body, and a first sealing ring and a second sealing ring are arranged on the circumferential surface of the thrust assembly at intervals.

7. A liquid rocket engine comprising the reversing valve mechanism of the liquid rocket engine of any one of claims 1-6.