CN114645803A - Composite material winding regenerative cooling thrust chamber and processing technology - Google Patents

Abstract

The invention provides a composite material winding regeneration cooling thrust chamber and a processing technology, and relates to the field of liquid rocket engines. The composite material winding regeneration cooling thrust chamber includes a thrust chamber body and a composite material layer; the outer side wall of the thrust chamber body is provided with a cooling groove; the composite material layer is sleeved on the thrust chamber body, and the composite material layer coats the cooling groove to form a cooling channel , the composite material layer is formed by winding composite fibers on the thrust chamber body. The outer side wall of the thrust chamber body with the cooling groove formed corresponds to the inner shell of the sandwich structure, and the composite material layer sleeved on the thrust chamber body corresponds to the outer shell of the sandwich structure. Since the composite material layer is formed by winding composite fibers on the thrust chamber body, no brazing process is used in the processing process, so the wall thickness of the thrust chamber body and the height of the cooling channel are not limited by the brazing technical conditions, which can make the thrust chamber body The wall thickness is smaller and the height of the cooling channel is lower, thereby improving the cooling effect of the cooling channel.

Description

A kind of composite material winding regeneration cooling thrust chamber and processing technology

technical field

The invention relates to the field of liquid rocket engines, in particular to a composite material winding regeneration cooling thrust chamber and a processing technology.

Background technique

Regenerative cooling refers to designing the side wall of the thrust chamber body as a sandwich structure, forming an inner shell, an outer shell and a regenerative cooling channel between the inner shell and the outer shell, and making the propellant flow through the regenerative cooling channel, so as to cool the inner shell. The thermal protection method of convective cooling is widely used in medium-thrust and high-thrust liquid rocket engines.

The structure of the regenerative cooling channel is extremely complex, the processing is very difficult, and the rocket engine has high requirements on reliability. Therefore, when machining regenerative cooling channels, a very high machining quality must be guaranteed.

At present, it is more common practice to use the brazing process to manufacture regenerative cooling channels. However, due to the limitation of brazing technical conditions, there are defects such as the increase of the wall thickness of the thrust chamber and the increase of the height of the cooling channel when the regenerative cooling channel is processed by the brazing process, which leads to the reduction of the cooling effect of the regenerative cooling channel.

SUMMARY OF THE INVENTION

In order to solve the problems existing in the prior art, one of the objectives of the present invention is to provide a composite material wound regeneration cooling thrust chamber.

The present invention provides the following technical solutions:

A composite material winding regeneration cooling thrust chamber, comprising a thrust chamber body and a composite material layer;

A cooling groove is provided on the outer side wall of the thrust chamber body;

The composite material layer is sleeved on the thrust chamber body, the composite material layer covers the cooling groove to form a cooling channel, and the composite material layer is formed by winding composite fibers on the thrust chamber body.

As a further optional solution for regenerating the cooling thrust chamber by winding the composite material, the composite material layer includes an inner layer, a middle layer and an outer layer, and the composite fibers in the inner layer and the outer layer are along the For the circumferential winding of the thrust chamber body, the composite fibers in the middle layer are spirally wound.

As a further optional solution for regenerating the cooling thrust chamber by winding the composite material, the composite fiber is an expanded polytetrafluoroethylene fiber.

As a further optional solution for regenerating and cooling the thrust chamber by winding the composite material, the outer side wall of the thrust chamber body is provided with a rib plate and a cover plate;

the rib plate is arranged along the axial direction of the thrust chamber body, the rib plate is provided with a plurality of, and the plurality of the rib plate is arranged along the circumferential direction of the thrust chamber body to form the cooling groove;

The cover plates are arranged in pairs at both ends of the composite material layer along the axial direction of the thrust chamber body, the cover plates are sealedly connected to the thrust chamber body and the composite material layer at the same time, and the cover plates are simultaneously sealed with the thrust chamber body and the composite material layer. There is a coolant inlet and a coolant outlet.

As a further optional solution for regenerating and cooling the thrust chamber by winding the composite material, the thrust chamber body includes a combustion chamber section and a Laval nozzle section, and the combustion chamber section and the Laval nozzle section are respectively provided with the the cooling tank;

At least two composite material layers are provided, and the at least two composite material layers are respectively sleeved on the combustion chamber section and the Laval nozzle section.

Another object of the present invention is to provide a processing technique.

The present invention provides the following technical solutions:

A machining process for machining cooling passages on a thrust chamber body, comprising:

machining cooling grooves on the outer sidewall of the thrust chamber body;

Composite fibers are wound on the thrust chamber body to form a composite material layer covering the cooling groove.

As a further optional solution to the processing technology, the composite material layer includes an inner layer, a middle layer and an outer layer;

The winding composite fiber on the thrust chamber body includes:

First, the composite fibers are wound on the thrust chamber body along the circumferential direction of the thrust chamber body to form the inner layer;

Then, the composite fibers are spirally wound from one end of the inner layer to the other end, and then the composite fibers are wound back to the starting position in opposite spirals, repeating several times to form the middle layer;

Finally, the composite fibers are wound on the middle layer along the circumferential direction of the thrust chamber body to form the outer layer.

As a further optional solution to the processing technology, when the inner layer and the outer layer are formed by winding, the thrust chamber body is divided into a plurality of annular winding regions in the axial direction, and each of the Winding regions are respectively wound with multiple turns of the composite fibers, and the width of the winding regions is smaller than the width of the composite fibers, so that the composite fibers at the junction of two adjacent winding regions are overlapped and compacted;

When winding to form the middle layer, two adjacent turns of the composite fibers overlap.

As a further optional solution to the processing technology, when the composite fibers are wound on the thrust chamber body, the tension of the composite fibers decreases with the increase of the winding thickness, and the tension of the composite fibers under the same thickness be consistent.

As a further optional solution to the processing technology, when the composite fibers are wound on the thrust chamber body, the space between the thrust chamber body and the composite fibers and between the composite fibers and the composite fibers are A sealant is applied to maintain tension on the conjugate fibers and secure the conjugate fibers.

The embodiments of the present invention have the following beneficial effects:

The outer side wall of the thrust chamber body with the cooling groove formed is equivalent to the inner shell of the sandwich structure, the composite material layer sleeved on the thrust chamber body is equivalent to the outer shell of the sandwich structure, and the composite material layer wraps the cooling groove to form a cooling channel. Since the composite material layer is formed by winding composite fibers on the thrust chamber body, and no brazing process is used in the processing process, the wall thickness of the thrust chamber body and the height of the cooling channel are not limited by the technical conditions of brazing, which can make the thrust chamber body The wall thickness is smaller and the height of the cooling channel is lower, thereby improving the cooling effect of the cooling channel.

In order to make the above-mentioned objects, features and advantages of the present invention more obvious and understandable, preferred embodiments are hereinafter described in detail together with the accompanying drawings.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present invention more clearly, the following briefly introduces the accompanying drawings that need to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the present invention, and therefore do not It should be regarded as a limitation of the scope, and for those of ordinary skill in the art, other related drawings can also be obtained according to these drawings without any creative effort.

FIG. 1 shows a schematic diagram of the overall structure of a composite material winding regeneration cooling thrust chamber provided in Embodiment 1 of the present invention;

2 shows a schematic structural diagram of a thrust chamber body in a composite material winding regeneration cooling thrust chamber provided in Embodiment 1 of the present invention;

3 shows a schematic diagram of the connection relationship between the cover plate and the combustion chamber section in a composite material wound regeneration cooling thrust chamber provided in Embodiment 1 of the present invention;

Fig. 4 shows the overall flow chart of a kind of processing technology that the embodiment 2 of the present invention provides;

Fig. 5 shows the flow chart of step S3 in a kind of processing technology provided by Embodiment 2 of the present invention;

6 shows a schematic diagram of the winding direction of the inner layer and the outer layer composite fibers in a processing technology provided in Example 2 of the present invention;

7 shows a schematic diagram of the winding direction of the middle-layer composite fiber in a processing technology provided in Example 2 of the present invention;

FIG. 8 shows a schematic diagram of the winding direction of the middle-layer composite fiber during rewinding in a processing process provided in Example 2 of the present invention.

Description of main component symbols:

100 - thrust chamber body; 110 - combustion chamber section; 120 - Laval nozzle section; 130 - rib plate; 140 - annular groove; 150 - cover plate; 160 - O-ring; 200 - composite material layer; 300 - measuring nozzle mouth.

Detailed ways

The following describes in detail the embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals refer to the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary, only used to explain the present invention, and should not be construed as a limitation of the present invention.

It should be noted that when an element is referred to as being "fixed to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. In contrast, when an element is referred to as being "directly on" another element, there are no intervening elements present. The terms "vertical," "horizontal," "left," "right," and similar expressions are used herein for illustrative purposes only.

In the present invention, unless otherwise expressly specified and limited, the terms "installed", "connected", "connected", "fixed" and other terms should be understood in a broad sense, for example, it may be a fixed connection or a detachable connection , or integrated; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of the two elements or the interaction relationship between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

In addition, the terms "first" and "second" are only used for descriptive purposes, and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, a feature defined as "first" or "second" may expressly or implicitly include one or more of that feature. In the description of the present invention, "plurality" means two or more, unless otherwise expressly and specifically defined.

Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the technical field to which this application belongs. The terminology used herein in the specification of the template is for the purpose of describing particular embodiments only and is not intended to limit the present invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

When machining cooling channels on thrust chambers, there are three common machining processes at present, namely brazing, electroforming and 3D printing.

The process of brazing the cooling channel is relatively complicated, requires a lot of process equipment, and the production cost is high, and it is difficult to make the coolant flow area small within the throat of the thrust chamber. The throat of the thrust chamber is the location where cooling is most needed, and the problem of mutual restriction between the cooling effect of the throat and the complexity of the machining process under the brazing process is difficult to solve.

In addition, there are mainly four types of cooling channel structures processed by brazing process, which are pressure pit spot welding type, milling groove type, corrugated plate type and tube bundle type.

Among them, the connection strength of the pressure pit spot welding structure is limited by the number of solder joints, and increasing the number of solder joints will inevitably increase the hydraulic loss, and the position of the solder joints cannot be effectively cooled. In order to ensure the welding quality of the pressure pit spot welding structure, it is necessary to increase the wall thickness of the cooling channel, but the cooling effect will also decrease.

The processing method of the groove-milling structure is to first mill a groove on the outer surface of the inner wall of the cooling channel, then assemble the inner wall and the outer wall together, and braze a complete cooling channel in the furnace. The heat resistance of brazed joints is poor, and the strength of the joint is affected by the quality of the weld. During brazing, the cooling channel is often blocked by the solder. Therefore, the height of the cooling channel of the milling groove structure needs to be no less than 1.5mm.

The processing process of the corrugated plate structure and the tube bundle structure is also inseparable from the brazing process.

In the process of electroforming, there are problems such as pores, delamination, and uneven material strength. So far, the metal used to make electroformed thrust chambers is basically nickel, but at high temperatures, the strength of the nickel layer decreases significantly, and the specific gravity of nickel is greater than that of stainless steel, which weakens the ability of the engine to carry payloads. Therefore, the thrust chamber processed and formed by electroforming method usually has shortcomings such as low strength of electroforming layer and heavy structural quality.

3D printing is a new thrust chamber processing and molding process that has emerged in recent years, and is still in the stage of exploration and development. Through methods such as laser sintering of metal powders, 3D printing has been successfully applied to the processing and production of aerospace parts. However, the dimensional accuracy and surface roughness of 3D printed parts cannot reach the level of traditional machining, and the size of the 3D printing equipment will also limit the size of the thrust chamber. Moreover, there are few types of metal powders that not only meet the performance requirements of the thrust chamber, but also are suitable for the 3D printing process, and there are limitations.

Example 1

Referring to FIG. 1 , this embodiment provides a composite material winding regeneration cooling thrust chamber (hereinafter referred to as “thrust chamber”), which is applied to a liquid rocket engine, and includes a thrust chamber body 100 and a composite material layer 200 .

The composite material layer 200 is sleeved on the side wall of the thrust chamber body 100 to form a sandwich structure, and a cooling channel exists between the composite material layer 200 and the thrust chamber body 100 . The purpose of cooling the thrust chamber body 100 can be achieved by using the propellant as a coolant, making it flow through the cooling channel, and removing the heat on the side wall of the thrust chamber body 100 through the convection heat exchange heat. After the propellant flows out of the cooling channel, it is injected into the combustion chamber inside the thrust chamber body 100 through the injection panel, and the heat absorbed by the propellant is then returned to the combustion chamber to realize regenerative cooling.

Please refer to FIG. 2 . Specifically, the thrust chamber body 100 is composed of a combustion chamber section 110 and a Laval nozzle section 120 . The internal space of the combustion chamber section 110 is the combustion chamber. The end of the combustion chamber section 110 away from the Laval nozzle section 120 is provided with a Injection panel. The combustion chamber section 110 and the Laval nozzle section 120 are preliminarily positioned by pins, then connected by flanges, and sealed by graphite gaskets.

The outer side wall of the combustion chamber section 110 and the outer side wall of the Laval nozzle section 120 are respectively provided with cooling grooves, and the composite material layer 200 is provided with two cooling grooves. One of the composite material layers 200 is sleeved on the side wall of the combustion chamber section 110 to cover the cooling groove on the combustion chamber section 110 to form a cooling channel. Another composite material layer 200 is sleeved on the side wall of the Laval nozzle section 120 to cover the cooling groove on the Laval nozzle section 120 to form another cooling channel.

In particular, the shapes and sizes of the two cooling passages are independent of each other, and are designed according to the actual cooling requirements of the combustion chamber section 110 and the Laval nozzle section 120, respectively. However, the formation principles of the two cooling passages are the same, and the following description takes the cooling passage on the combustion chamber section 110 as an example.

In a specific implementation of this embodiment, a plurality of ribs 130 are provided on the outer side wall of the combustion chamber section 110 . Each rib plate 130 is disposed along the axial direction of the thrust chamber body 100 and arranged along the circumferential direction of the thrust chamber body 100 , and a cooling groove is formed between two adjacent rib plates 130 .

In particular, the cooling groove is formed by milling, and each rib 130 is integrally provided with the outer side wall of the combustion chamber section 110 . According to the actual cooling requirements of the combustion chamber section 110 and the Laval nozzle section 120 , cooling grooves of different numbers, widths and depths are milled on the outer sidewalls of the combustion chamber section 110 and the Laval nozzle section 120 respectively.

In another specific implementation of this embodiment, a corrugated plate can also be welded and fixed on the outer side wall of the combustion chamber section 110 , and the wave trough on the side of the corrugated plate facing away from the combustion chamber section 110 is used as a cooling groove.

After the cooling groove is formed, the composite material layer 200 is sleeved on the side wall of the combustion chamber section 110 to cover the cooling groove on the combustion chamber section 110 to form a plurality of flow channels with open ends and closed sides and independent of each other. The two flow channels together form a cooling channel.

Referring to FIG. 3 , further, taking the combustion chamber section 110 as an example, an annular groove 140 is also formed on the outer side wall, and an annular cover plate 150 is sleeved. The annular groove 140 and the cover plate 150 are both disposed along the circumferential direction of the combustion chamber section 110 , and are disposed in pairs at both ends of the composite material layer 200 along the axial direction of the thrust chamber body 100 . In particular, the side wall of the annular groove 140 facing the composite material layer 200 is flush with the end face of the composite material layer 200 .

In addition, the cross section of the cover plate 150 is U-shaped, and the opening of the cover plate 150 is directly opposite to the annular groove 140 . One end of the cover plate 150 along the axial direction of the thrust chamber body 100 is sleeved on the combustion chamber section 110 and fixed to the combustion chamber section 110 by welding. The other end of the cover plate 150 along the axial direction of the thrust chamber body 100 is sleeved on the composite material layer 200 , and an O-ring 160 is provided between the cover plate 150 and the composite material layer 200 and sealed by the O-ring 160 .

In one aspect, the cover plate 150 and the composite material layer 200 jointly compress the O-ring 160, giving the O-ring 160 an initial sealing capability. On the other hand, the propellant has a certain pressure when flowing in the cooling channel, and the pressure is transmitted to the O-ring 160 through the composite material layer 200 to further improve the sealing ability of the O-ring 160 .

The annular channel formed by the cover plate 150 and the annular groove 140 communicates with each flow channel at the same time. Wherein, a coolant inlet is provided on the cover plate 150 at the end of the composite material layer 200 away from the injection panel, and the annular channel corresponding to the cover plate 150 is used as a branch channel, so that the propellant entering from the coolant inlet is branched to the cooling channel. in each channel. A coolant outlet is provided on the cover plate 150 located at one end of the composite material layer 200 close to the injection panel, and the annular channel corresponding to the cover plate 150 is used as a confluence channel, so that the propellants in the various flow channels of the cooling channel are confluent, and the coolant is discharged from the coolant outlet. outflow.

Whether it is the combustion chamber section 110 or the Laval nozzle section 120, the propellant enters the cooling channel from the side away from the injection panel, and leaves the cooling channel from the side close to the injection panel. After that, the coolant is injected through the injection panel and enters the combustion chamber for combustion to realize the regenerative cooling function.

Specifically, the composite material layer 200 is formed by winding composite fibers on the thrust chamber body 100 .

In particular, the composite material layer 200 consists of an inner layer, a middle layer and an outer layer. The composite fibers in the inner layer are wound along the circumferential direction of the thrust chamber body 100 to provide radial strength. The composite fibers in the middle layer are helically wound, providing full axial strength and some radial strength. The composite fibers in the outer layer are wound along the circumference of the thrust chamber body 100, providing radial strength.

In this embodiment, the composite fibers are expanded polytetrafluoroethylene fibers, and the expanded polytetrafluoroethylene fibers are fluoropolymer fibers made of expanded polytetrafluoroethylene as raw materials.

Expanded polytetrafluoroethylene is processed by a special process of polytetrafluoroethylene dispersion resin. It is a pure inert material with strong chemical resistance, anti-wear properties, and strong high temperature and low temperature resistance. It ensures material integrity and performance reliability when in direct contact with propellants, making it ideal for sealing and transporting industrial liquids.

Expanded polytetrafluoroethylene fiber has the characteristics of high strength, low shrinkage, wear resistance, etc. The fabric processed from it is very light, thin, and waterproof. Require.

In a word, in the above-mentioned thrust chamber, the outer side wall of the thrust chamber body 100 with the cooling groove processed and formed is equivalent to the inner shell of the sandwich structure, and the composite material layer 200 sleeved on the thrust chamber body 100 is equivalent to the outer shell of the sandwich structure. Layer 200 wraps the cooling trough, forming cooling channels.

Since the composite material layer 200 is formed by winding composite fibers on the thrust chamber body 100, and no brazing process is used during the processing, it is not necessary to increase the wall thickness of the thrust chamber body 100 to ensure welding quality. In addition, there is no need to consider the problem that the cooling channel is blocked by solder during brazing, and the composite fiber can adapt to the complex and changeable shape of the sidewall of the thrust chamber. The flow velocity in the channel enhances the convective heat transfer and optimizes the cooling effect.

Example 2

Referring to FIG. 4 , the present embodiment provides a machining process for machining a cooling channel on the thrust chamber body 100 , which includes the following steps:

S1, machining a cooling groove on the outer side wall of the thrust chamber body 100, the specific steps are as follows:

S1-1, design the thrust chamber body 100 profile and cooling groove.

S1-2, a cooling groove is milled on the outer side wall of the thrust chamber body 100, and a rib plate 130 is formed at the same time.

S2, install the measuring nozzle 300.

Specifically, all the measuring nozzles 300 arranged in the combustion chamber section 110 are connected to the combustion chamber section 110 by welding or sealing threads, and it is confirmed that there is no leakage between the combustion chamber and the cooling groove, so as to ensure the safety of the thrust chamber. sex.

S3, winding composite fibers on the thrust chamber body 100 to form a composite material layer 200 covering the cooling groove. The composite fiber adopts expanded polytetrafluoroethylene fiber, and the composite material layer 200 is composed of an inner layer, a middle layer and an outer layer.

Please refer to Figure 5, the specific steps are as follows:

S3-1, winding the composite fiber on the thrust chamber body 100 along the circumferential direction of the thrust chamber body 100 to form an inner layer.

Referring to FIG. 6 , specifically, referring to the width of the composite fiber, the thrust chamber body 100 is divided into a plurality of annular winding regions of equal width in the axial direction.

One circle of composite fibers is wound around each winding area in turn, and the composite fibers are wound along the circumferential direction of the thrust chamber body 100 . This process is repeated until a sufficient number of turns of the composite fiber is finally wound around all the winding areas.

In addition, the width of the winding region is made smaller than the width of the composite fibers, so that the composite fibers at the junction of two adjacent winding regions are overlapped. On this basis, when the composite fiber is wound in the next winding area, the position overlapping the previous winding area needs to be compacted to ensure that no leakage occurs at the junction of the areas.

Finally, the inner layer formed by winding uniformly covers the entire length of the cooling groove.

S3-2, winding the composite fiber in a spiral shape from one end of the inner layer to the other end, and then winding the composite fiber back to the starting position in an opposite spiral, repeating several times to form a middle layer.

Please refer to FIG. 7 and FIG. 8 , in this embodiment, the composite fibers are firstly wound from the left end to the right end of the inner layer in a right-handed manner, and then the composite fibers are wound from the right end to the left end of the inner layer in a left-handed manner, and Winding multiple back and forth in this manner forms a tightly helically wound middle layer.

In addition, when helically wound, two adjacent turns of composite fibers overlap to ensure good sealing.

S3-3, winding the composite fiber on the middle layer along the circumferential direction of the thrust chamber body 100 to form the outer layer.

Referring to FIG. 6 , specifically, the same as when winding to form the inner layer, referring to the width of the composite fibers, the thrust chamber body 100 is axially divided into a plurality of annular winding regions of equal width and smaller than the width of the composite fibers.

Likewise, one circle of composite fibers is wound around each winding area in turn, and the composite fibers are wound along the circumferential direction of the thrust chamber body 100 . This process is repeated until a sufficient number of turns of the composite fiber is finally wound around all the winding areas.

In addition, the winding direction of the outer layer is the same as that of the inner layer.

Further, in the process of winding the composite fibers, the tension of the composite fibers under the same thickness remains the same, and the tension of the composite fibers under different thicknesses changes regularly.

In this embodiment, as the winding thickness increases, the tension of the composite fibers decreases linearly, so as to prevent the outer composite fibers from compressing the inner composite fibers, causing the inner composite fibers to relax and unable to bear the pressure of the propellant in the cooling channel.

That is, the tension on the middle layer composite fiber is slightly lower than that on the inner layer composite fiber, and the tension on the outer layer composite fiber is slightly lower than that on the middle layer composite fiber.

Further, in the process of winding the composite fibers, sealant is applied between the thrust chamber body 100 and the composite fibers, and between the composite fibers and the composite fibers, so as to maintain the tension on the composite fibers and fix the composite fibers.

On the one hand, the innermost composite fiber and the rib 130 are sealed by sealant, which can prevent the propellant from flowing laterally between different flow channels, thereby preventing the actual flow area of the propellant from being larger than the design value.

On the other hand, the composite fibers inside the composite material layer 200 are sealed by a sealant, which can prevent the leakage of the propellant and ensure the sealing performance of the composite material layer 200 .

In this embodiment, the sealant is a high-temperature and high-pressure sealant, which is made of inorganic copper oxide, ceramic materials, and polymer high-temperature curing agent in a certain proportion. 1000 ℃, meanwhile, it has high structural strength, and its cured product has good toughness.

S4, continue to wind the composite fiber at a specific position for reinforcement and leveling.

Specifically, the two ends of the outer layer along the axial direction of the thrust chamber body 100, the vicinity of the measuring nozzle 300 and the vicinity of the equator are continuously wound with composite fibers for reinforcement.

The composite fibers are continuously wound at both ends of the outer layer along the axial direction of the thrust chamber body 100, and are filled and leveled according to the design size. When making up the size, it is necessary to ensure that there is no interference between the composite material layer 200 and the cover plate 150, and also to ensure that the O-ring 160 is sufficiently squeezed so that it can perform its proper sealing function.

S5, the cover plate 150 is installed.

Specifically, an O-ring 160 is placed between the cover plate 150 and the composite material layer 200 , and then the cover plate 150 is fully welded and fixed on the outer side wall of the thrust chamber body 100 , and the cover plate 150 is formed on the O-ring 160 . a certain amount of squeezing.

In a word, the above processing technology is based on the milling and forming of the thrust chamber body 100 with the cooling groove as the winding basis, the expanded polytetrafluoroethylene fiber is used as the winding material, the high temperature and high pressure sealant is used as the auxiliary sealing, and the hoop winding and helical winding layered matching are adopted. The composite material layer 200 is made and used as the outer wall of the cooling channel by the winding molding additive manufacturing method.

Compared with the brazing process, the above-mentioned processing technology is simpler, cheaper, requires less process equipment, and effectively relieves the limitation of the brazing process on key design parameters such as the wall thickness of the thrust chamber and the height of the cooling channel. Compared with the electroforming process, the above processing process avoids problems such as pores, delamination, and uneven material strength. Compared with the 3D printing process, the above processing technology is not restricted by the type of wall metal material, and has stronger adaptability and wider application range.

In all examples shown and described herein, any specific value should be construed as merely exemplary and not as limiting, as other examples of exemplary embodiments may have different values.

It should be noted that like numerals and letters refer to like items in the following figures, so once an item is defined in one figure, it does not require further definition and explanation in subsequent figures.

The above-mentioned embodiments only represent several embodiments of the present invention, and the descriptions thereof are specific and detailed, but should not be construed as limiting the scope of the present invention. It should be pointed out that for those of ordinary skill in the art, without departing from the concept of the present invention, several modifications and improvements can also be made, which all belong to the protection scope of the present invention.

Claims (10)

1. a composite material winding regeneration cooling thrust chamber, is characterized in that, comprises thrust chamber body and composite material layer; A cooling groove is provided on the outer side wall of the thrust chamber body; The composite material layer is sleeved on the thrust chamber body, the composite material layer covers the cooling groove to form a cooling channel, and the composite material layer is formed by winding composite fibers on the thrust chamber body. 2. The composite material winding regeneration cooling thrust chamber according to claim 1, wherein the composite material layer comprises an inner layer, a middle layer and an outer layer, and the composite fibers in the inner layer and the outer layer Winding along the circumferential direction of the thrust chamber body, the composite fibers in the middle layer are spirally wound. 3 . The composite material winding regeneration cooling thrust chamber according to claim 1 , wherein the composite fibers are expanded polytetrafluoroethylene fibers. 4 . 4. The composite material winding regeneration cooling thrust chamber according to claim 1, wherein a rib plate and a cover plate are provided on the outer side wall of the thrust chamber body; the rib plate is arranged along the axial direction of the thrust chamber body, the rib plate is provided with a plurality of, and the plurality of the rib plate is arranged along the circumferential direction of the thrust chamber body to form the cooling groove; The cover plates are arranged in pairs at both ends of the composite material layer along the axial direction of the thrust chamber body, the cover plates are sealedly connected to the thrust chamber body and the composite material layer at the same time, and the cover plates A coolant inlet and a coolant outlet are provided. The composite material winding regeneration cooling thrust chamber according to claim 1, wherein the thrust chamber body comprises a combustion chamber section and a Laval nozzle section, the combustion chamber section and the Laval nozzle section are respectively is provided with the cooling tank; There are at least two composite material layers, and the at least two composite material layers are respectively sleeved on the combustion chamber section and the Laval nozzle section. 6. A processing technique, characterized in that, for processing a cooling channel on the thrust chamber body, comprising: machining cooling grooves on the outer sidewall of the thrust chamber body; Composite fibers are wound on the thrust chamber body to form a composite material layer covering the cooling groove. 7. The process according to claim 6, wherein the composite material layer comprises an inner layer, a middle layer and an outer layer; The winding composite fiber on the thrust chamber body includes: First, the composite fibers are wound on the thrust chamber body along the circumferential direction of the thrust chamber body to form the inner layer; Then, the composite fibers are spirally wound from one end of the inner layer to the other end, and then the composite fibers are wound back to the starting position in an opposite spiral, repeating multiple times to form the middle layer; Finally, the composite fibers are wound on the middle layer along the circumferential direction of the thrust chamber body to form the outer layer. 8. The process according to claim 7, wherein when forming the inner layer and the outer layer by winding, the thrust chamber body is axially divided into a plurality of annular winding areas, and each Each of the winding regions is wound with multiple turns of the composite fibers, and the width of the winding regions is smaller than the width of the composite fibers, so that the composite fibers at the junction of two adjacent winding regions are overlapped and compacted; When winding to form the middle layer, two adjacent turns of the composite fibers overlap. 9 . The process according to claim 6 , wherein when the composite fibers are wound on the thrust chamber body, the tension of the composite fibers decreases with the increase of the winding thickness, and the composite fibers under the same thickness are reduced. 10 . The tension of the fibers remains the same. 10 . The process according to claim 6 , wherein when the composite fibers are wound on the thrust chamber body, between the thrust chamber body and the composite fibers, and between the composite fibers and the composite fibers. 11 . Sealant is applied between them to maintain the tension on the composite fibers and fix the composite fibers.

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