CN115977831A - Engine subsystem of a liquid rocket - Google Patents

Abstract

The invention discloses an engine sub-system of a liquid rocket, which comprises a first-bottom main body, a second-bottom main body, a third-bottom main body and a combustion chamber which are sequentially fixedly connected. The bearing is cooled in the first gap between the main body of the second bottom, and the one-piece penetrating arrangement of the turbine shaft can not only simplify the system structure, reduce the weight, improve the compactness of the space arrangement, reduce the space occupation, but also save the complicated The dynamic sealing device of the turbine device between the structures solves the multi-machine layout problem of the traditional liquid rocket engine, promotes the lightweight development of reusable and recoverable rockets, and improves the flexibility of component layout.

Description

Engine subsystem of a liquid rocket

technical field

The present application relates to the technical field of liquid rocket engines, in particular to an engine subsystem of liquid rockets.

Background technique

The information provided in this section is for the purpose of generally presenting the context of the disclosure. To the extent described in this section, the work of the presently named inventors, and aspects of the description that may not constitute prior art at the time of filing, are neither expressly nor impliedly admitted to be prior art to the present disclosure.

The auxiliary system is an important part of the liquid rocket engine. It is generally composed of a gas generator (or pre-combustion chamber), a turbine device and a turbine exhaust gas discharge device. The turbine does work and provides continuous power to the fuel pump and oxidizer pump through the shaft. The gas generator (or pre-combustion chamber) and the turbine device in the traditional liquid rocket engine sub-system are independent components, which have the disadvantages of complex structure, many parts, heavy weight, space occupation, and not conducive to the compact layout of the engine assembly. With the development of reusable and recoverable rocket technology, the first-stage rocket often needs to arrange 5 or more engines. Due to the limitation of the engine's own outline size, this work is extremely difficult, and the engine subsystem determines the engine outline. The main contradiction of size.

Contents of the invention

Aiming at the defects in the prior art, the present application provides a liquid rocket engine sub-system to solve the problems of complex structure and high space occupation of the traditional sub-system in the prior art.

The above-mentioned purpose of the present application is mainly achieved through the following technical solutions:

An engine auxiliary system of a liquid rocket, comprising a first-bottom main body, a second-bottom main body, a third-bottom main body and a combustion chamber fixedly connected in sequence;

The first bottom body is used to form a pump cavity with the pump body, and there is a first space for accommodating oxidant with the second bottom body, and there is a space between the second bottom body and the third bottom body.

The second space for accommodating fuel, the side of the combustion chamber far away from the three-bottom main body is arranged with nozzle cascades, turbine disks and exhaust pipes in sequence 5, and one side of the turbine disk is provided with the nozzle cascade, the three-bottom body, the second-bottom body, and the turbine shaft of the one-bottom body;

A first nozzle is provided between the first space and the combustion chamber, and a second nozzle is provided between the second space and the combustion chamber;

Bearings are respectively provided between the turbine shaft, the second bottom body and the nozzle cascade, and a first gap is provided between the turbine shaft and the second bottom body.

Further, a cooling channel communicating with the second space is axially provided in the turbine shaft, and a cooling hole communicating with the cooling channel is radially provided on the turbine shaft for

Fuel in the cooling passage is directed towards the bearing between the nozzle cascade and the turbine shaft.

Further, the turbine disk and the nozzle cascade are arranged coaxially, and a plurality of corresponding discharge channels are respectively provided on the nozzle cascade and the turbine disk.

Further, the exhaust pipe and the nozzle cascade are fixed through detachable bolt connections.

Further, a sealing ring is provided between the exhaust pipe and the nozzle cascade.

Further, a guide surface for guiding gas is provided on the side of the nozzle cascade close to the combustion chamber.

Further, two stoppers are sheathed on the turbine shaft, and the two stoppers respectively bear against one side of the two bearings, so as to limit the separation of the bearings from the turbine shaft. 5 Further, the turbine shaft is provided with a coupling for connecting the pump shaft.

Further, the three-bottom main body, the combustion chamber and the nozzle cascade are respectively connected by flanges.

Further, the first nozzle is welded and fixed to the second-bottom body, and the second nozzle is welded and fixed to the triple-bottom body.

Compared with the prior art, the advantages of the present application are:

In this application, the main body of the first bottom, the main body of the second bottom, the main body of the third bottom and the combustion chamber are fixedly connected in sequence. There is a second space for accommodating fuel between the bottom body and the three-bottom body. The side of the combustion chamber far away from the three-bottom body is arranged in sequence with nozzle cascades, turbine discs and exhaust pipes. The nozzle cascade, the three-bottom main body, the second-bottom main body and the turbine shaft of the first-bottom main body, the oxidant in the first space enters the combustion chamber through the first nozzle, and the fuel in the second space enters the combustion chamber and the oxidant through the second nozzle Mixed combustion, and drive the turbine disk to rotate after passing through the nozzle cascade, the exhaust gas is discharged through the exhaust pipe, the turbine shaft is stably erected through the bearing and outputs rotational power, and a small amount of fuel enters the first gap between the turbine shaft and the second bottom body. Bearings are cooled, and the integral penetration of the turbine shaft can not only simplify the system structure, reduce the weight, improve the compactness of the space layout, reduce the space occupation, but also save the complicated dynamic sealing device of the turbine device between multiple structures, and solve the problem It solves the multi-machine layout problem of traditional liquid rocket engines, promotes the lightweight development of reusable recovery rockets, and improves the flexibility of component layout.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings that need to be used in the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those skilled in the art, other drawings can also be obtained based on these drawings without creative effort.

FIG. 1 is a schematic cross-sectional view of an engine sub-system provided by an embodiment of the present application;

In the figure: 11, the main body of the first bottom; 12, the main body of the second bottom; 13, the main body of the third bottom; 14, the combustion chamber; 15, the pump chamber; 16, the bearing; 21, the first space; 22, the second space; 23, the nozzle cascade; 24, turbine disk; 25, turbine shaft; 26, exhaust pipe; 31, first nozzle; 32, second nozzle; 41, first gap; 42, cooling channel; 43, cooling hole; 44, spray Exit channel; 51, bolt; 52, sealing ring; 61, guide surface; 71, block; 72, coupling.

Detailed ways

The present invention will be further elaborated below in conjunction with the accompanying drawings and specific embodiments. It should be noted here that the descriptions of these embodiments are used to help understand the present invention, but are not intended to limit the present invention. Specific structural and functional details disclosed herein are for purposes of describing example embodiments of the invention only. However, the invention may be embodied in many alternative forms and should not be construed as limited to the embodiments set forth herein.

As shown in FIG. 1 , an engine sub-system of a liquid rocket includes a first-bottom main body 11 , a second-bottom main body 12 , a third-bottom main body 13 and a combustion chamber 14 which are sequentially fixedly connected.

The first bottom body 11 is used to form a pump cavity 15 with the pump body, and there is a first space 21 for accommodating oxidant between the second bottom body 12, and the first bottom body 11 is fixed by the pump body. Assembling relationship, a pump chamber 15 is formed on one side of the bottom body 11, and communicates with the second space 22 through an external connecting pipeline, so that the external pressure of the pump chamber 15 can form a push output for the fuel in the second space 22 effect.

There is a second space 22 for accommodating fuel between the second bottom body 12 and the triple bottom body 13 .

The side of the combustion chamber 14 away from the three-bottom main body 13 is arranged with a nozzle cascade 23, a turbine disk 24 and an exhaust pipe 26 in sequence, the combustion chamber 14 is located between the three-bottom main body 13 and the nozzle cascade 23, and The three-bottom body 13 and the nozzle cascade 23 form a space for mixed combustion of fuel and oxidant. The high-temperature gas formed after combustion passes through the nozzle cascade 23 and then impacts towards the turbine disk 24, and acts on the turbine disk 24 to drive the turbine disk 24 to rotate. The exhaust gas after doing work is discharged under the guidance of the exhaust pipe 26, and generates part of the thrust.

One side of the turbine disk 24 is provided with a turbine shaft 25 that runs through the nozzle cascade 23, the three-bottom body 13, the second-bottom body 12, and the one-bottom body 11 at the same time. Through the connection of the turbine shaft 25, The power on the side of the turbine disk 24 is output to the side of the bottom main body 11 close to the pump chamber 15, so that the transmission efficiency is high.

A first nozzle 31 is provided between the first space 21 and the combustion chamber 14, and the first nozzle 31 is used to spray the oxidant in the first space 21 into the combustion chamber 14, and the second space 22 is connected to the combustion chamber 14. A second nozzle 32 is provided between the combustion chambers 14, and the second nozzle 32 is used to spray the fuel in the second space 22 into the combustion chamber 14. The number of the first nozzles 31 and the number and inner diameter of the second nozzles 32 can be adjusted. Corresponding settings are made according to the mixing ratio parameters of the oxidizer and the fuel, and the first nozzle 31 and the second nozzle 32 are evenly spaced to improve the mixing uniformity of the oxidizer and the fuel.

Bearings 16 are respectively arranged between the turbine shaft 25, the second bottom main body 12 and the nozzle cascade 23, and the bearings 16 provide the support for the stable rotation of the turbine shaft 25, and keep the turbine shaft 25 connected to the nozzle blade cascade 23, The relatively stable positional relationship among the three-bottom main body 13 , the second-bottom main body 12 and the first-bottom main body 11 ensures that the turbine shaft 25 continuously outputs power driven by the turbine disk 24 .

Moreover, a first gap 41 is provided between the turbine shaft 25 and the second bottom main body 12. When the turbine shaft 25 is driven to rotate and perform work, a space for the fuel in the second space 22 to pass through is provided through the first gap 41, and Heat exchange is carried out through the contact between the fuel and the bearing 16 between the turbine shaft 25 and the second bottom main body 12, thereby reducing the temperature of the bearing 16, maintaining the reliability of the overall continuous operation, and forming a pump with the first bottom main body 11 and the pump body. The cavity 15 is set as the fuel pump cavity 15, which can not only maintain the stable cooling effect of the bearing 16, but also save the complex dynamic sealing device, so as to ensure stable functionality and reduce the complexity of the system and device.

It should be noted that the size of the first gap 41 can be reasonably set according to the actual cooling efficiency requirements, and the amount of fuel flowing out of the first gap 41 is relatively small, which can meet the heat absorption requirements for cooling. Set the inner diameter of the first gap 41 to the minimum.

The working principle of this embodiment is: through the first bottom body 11, the second bottom body 12, the third bottom body 13 and the combustion chamber 14 are fixedly connected in sequence, the first bottom body 11 and the pump body form a pump cavity 15, and the pump chamber 15 is formed with the second bottom body 12 There is a first space 21 for accommodating the oxidant in between, a second space 22 for accommodating fuel is provided between the second-bottom body 12 and the triple-bottom body 13, and the side of the combustion chamber 14 away from the triple-bottom body 13 is sequentially arranged with Nozzle cascade 23, turbine disk 24 and exhaust pipe 26, one side of turbine disk 24 is provided with the turbine shaft 25 that runs through the nozzle cascade 23, three bottom main bodies 13, two bottom main bodies 12 and one bottom main body 11 at the same time, the second The oxidant in the first space 21 enters the combustion chamber 14 through the first nozzle 31, and the fuel in the second space 22 enters the combustion chamber 14 through the second nozzle 32 for mixed combustion with the oxidant, and drives the turbine disk 24 to rotate after passing through the nozzle cascade 23, Exhaust gas is discharged through the exhaust pipe 26, and the turbine shaft 25 is stably erected through the bearing 16 to output rotational power. 25’s one-piece penetration setting not only realizes simplified system structure, reduces weight, improves space layout compactness, reduces space occupation, but also eliminates the complicated dynamic sealing device of the turbine device between multiple structures, which solves the problem of traditional liquid rocket engines. The problem of multi-machine layout promotes the lightweight development of reusable recovery rockets and improves the flexibility of component layout.

Further, on the basis of the above-mentioned embodiments, a cooling passage 42 communicating with the second space 22 is arranged axially in the turbine shaft 25, and a cooling passage 42 communicating with the second space 22 is arranged radially on the turbine shaft 25. 42 communicated with the cooling hole 43 for guiding the fuel in the cooling passage 42 toward the bearing 16 between the nozzle cascade 23 and the turbine shaft 25, in the actual working process, the second space The fuel in 22 enters the cooling channel 42, and under the guidance of the cooling hole 43, flows to the bearing 16 between the nozzle cascade 23 and the turbine shaft 25. The low-temperature fuel contacts the bearing 16 to complete heat exchange and then merges with the exhaust gas to realize For the cooling operation of the bearing 16, it should be noted that the inner diameter of the cooling hole 43 can be reasonably set according to the needs of actual cooling efficiency, and the amount of fuel flowing out from the cooling hole 43 is relatively small, which can satisfy the heat absorption of cooling. On the premise of requirements, the inner diameter of the cooling hole 43 is set to the minimum.

Further, on the basis of the above-mentioned embodiments, the turbine disc 24 is arranged coaxially with the nozzle cascade 23 , and the nozzle cascade 23 and the turbine disc 24 are respectively provided with a plurality of corresponding spray nozzles. The channel 44 and the nozzle cascade 23 are relatively stationary, and the high-temperature gas passes through the turbine disk 24 through the injection channel 44, and drives the turbine disk 24 to rotate relative to the nozzle cascade 23. The turbine disk 24 and the nozzle cascade 23 are coaxially arranged and correspondingly The spray channel 44 can improve the utilization effect of high-temperature gas and avoid unnecessary waste of work.

Further, on the basis of the above embodiments, the exhaust pipe 26 and the nozzle cascade 23 are connected and fixed by detachable bolts 51, which facilitates the disassembly and assembly of the nozzle cascade 23 and the exhaust pipe 26. operation, improving the convenience of operation.

Further, on the basis of the above-mentioned embodiments, a sealing ring 52 is provided between the exhaust pipe 26 and the nozzle cascade 23, so that the generated exhaust gas can be more completely guided through the exhaust pipe 26, avoiding vibration in different A gap is generated in the working condition to cause leakage.

Further, on the basis of the above-mentioned embodiments, the side of the nozzle cascade 23 close to the combustion chamber 14 is provided with a guide surface 61 for guiding the gas, so that the high-temperature gas after the fuel and the oxidant are fully mixed and combusted is smoother and faster. Pass through the nozzle cascade 23 to avoid turbulent flow.

Further, on the basis of the above-mentioned embodiment, two stoppers 71 are sheathed on the turbine shaft 25, and the two stoppers 71 respectively bear against one side of the two bearings 16 for limiting The bearing 16 is separated from the turbine shaft 25 to further keep the distance between the bottom body 11 and the nozzle cascade 23 stable, and keep the turbine shaft 25 rotating without axial deviation, thereby improving reliability.

Further, on the basis of the above embodiments, the turbine shaft 25 is provided with a coupling 72 for connecting the pump shaft, the turbine disc 24 is driven to rotate, and the turbine shaft 25 outputs the power through the coupling 72, and Powers the fuel and oxidizer pumps.

Further, on the basis of the above-mentioned embodiments, the three-bottom main body 13, the combustion chamber 14 and the nozzle cascade 23 are respectively connected by flanges to maintain the three-bottom main body 13, the combustion chamber 14 and the nozzle cascade. The flexible disassembly and assembly capabilities between the cascades 23 can interpose a sealing layer between the flanges to maintain the sealing performance, and the three-bottom main body 13, the combustion chamber 14 and the nozzle cascades 23 can also be welded in sequence to improve Overall connection stability and tightness.

Further, on the basis of the above embodiment, the first nozzle 31 is welded and fixed to the second bottom main body 12, and the second nozzle 32 is welded and fixed to the third bottom main body 13, maintaining the second The stable connection relationship between the first nozzle 31 and the second bottom body 12, the second nozzle 32 and the third bottom body 13, and the separately processed first nozzle 31 and the second nozzle 32 reduce the overall production and processing difficulty, and the second nozzle 32 can also be processed The first nozzle 31 and the second nozzle 32 are arranged integrally with the second-bottom main body 12 and the third-bottom main body 13 to improve overall integrity and overall structural stability.

Further, in the above embodiment, the bottom body 11 is provided with studs for connecting the pump housing.

It should be understood that the terms first, second, etc. are only used for distinguishing descriptions, and cannot be interpreted as indicating or implying relative importance. Although the terms first, second, etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one unit from another. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of example embodiments of the present invention.

It should be understood that the term "and/or" in this article is only an association relationship describing associated objects, indicating that there may be three relationships, for example, A and/or B may mean: A exists alone, B exists alone, and at the same time There are three situations of A and B. The term "/and" in this article describes another associated object relationship, which means that there can be two relationships, for example, A/ and B, which can mean: A exists alone, and A and B exist alone In both cases, in addition, the character "/" in this article generally indicates that the contextual objects are an "or" relationship.

It should be understood that in the description of the present invention, the orientation or positional relationship indicated by the terms "upper", "vertical", "inner", "outer", etc. is the orientation or positional relationship that the disclosed product is usually placed in use, Or the orientation or positional relationship commonly understood by those skilled in the art is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, Therefore, it should not be construed as limiting the invention.

In the description of the present invention, it should also be noted that, unless otherwise clearly specified and limited, the terms "setting", "installation" and "connection" should be interpreted in a broad sense, for example, it can be a fixed connection or an optional connection. Disassembled connection, or integral connection; it can be directly connected, or indirectly connected through an intermediary, and it can be the internal communication of two components. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention in specific situations.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments of the invention. As used herein, the singular forms "a", "an" and "the" are intended to include plural forms unless the context clearly dictates otherwise. It should also be understood that the terms "comprises", "comprises", "comprises", and/or "comprises" when used herein designate the presence of stated features, integers, steps, operations, elements and/or components and does not exclude the existence or addition of one or more other features, quantities, steps, operations, units, components and/or combinations thereof.

In the following description specific details are provided to facilitate a thorough understanding of example embodiments. However, it will be understood by those of ordinary skill in the art that example embodiments may be practiced without these specific details. In other embodiments, well-known processes, structures and techniques may not be shown in unnecessary detail in order not to obscure the example embodiments.

The above are only specific implementation manners of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the application. Therefore, the present application will not be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features claimed herein.

It should be noted that the information disclosed in the above background section is only for enhancing the understanding of the background of the present disclosure, and therefore may include information that does not constitute the prior art known to those of ordinary skill in the art.

Claims (10)

1. An engine auxiliary system of a liquid rocket is characterized by comprising a first bottom main body, a second bottom main body, a third bottom main body and a combustion chamber which are fixedly connected in sequence;

the first bottom main body is used for forming a pump cavity with a pump body, a first space for containing an oxidant is formed between the first bottom main body and the second bottom main body, a second space for containing fuel is formed between the second bottom main body and the third bottom main body, a nozzle cascade, a turbine disc and an exhaust pipe are sequentially arranged on one side of the combustion chamber, which is far away from the third bottom main body, and a turbine shaft which simultaneously penetrates through the nozzle cascade, the third bottom main body, the second bottom main body and the first bottom main body is arranged on one side of the turbine disc;

a first nozzle is arranged between the first space and the combustion chamber, and a second nozzle is arranged between the second space and the combustion chamber;

bearings are arranged between the turbine shaft and the two bottom main bodies and between the turbine shaft and the two bottom main bodies, and first gaps are arranged.

2. A liquid rocket engine subsystem as defined in claim 1, wherein: and a cooling channel communicated with the second space is axially arranged in the turbine shaft, and a cooling hole communicated with the cooling channel is radially arranged on the turbine shaft and used for guiding the fuel in the cooling channel to the bearing between the nozzle cascade and the turbine shaft.

3. A liquid rocket engine subsystem as defined in claim 1, wherein: the turbine disc and the nozzle blade grid are coaxially arranged, and a plurality of corresponding spraying channels are respectively arranged on the nozzle blade grid and the turbine disc.

4. A liquid rocket engine subsystem as defined in claim 1, wherein: the exhaust pipe and the nozzle blade cascade are fixedly connected through a detachable bolt.

5. A liquid rocket engine subsystem according to claim 1 wherein: and a sealing ring is arranged between the exhaust pipe and the nozzle cascade.

6. A liquid rocket engine subsystem as defined in claim 1, wherein: and one side of the nozzle cascade, which is close to the combustion chamber, is provided with a guide surface for guiding gas.

7. A liquid rocket engine subsystem as defined in claim 1, wherein: two check blocks are sleeved on the turbine shaft and respectively abutted against one side of the two bearings so as to limit the bearings from being separated from the turbine shaft.

8. A liquid rocket engine subsystem as defined in claim 1, wherein: and a coupling used for connecting the pump shaft is arranged on the turbine shaft.

9. A liquid rocket engine subsystem as defined in claim 1, wherein: the three-bottom main body, the combustion chamber and the nozzle cascade are connected through flanges respectively.

10. A liquid rocket engine subsystem as defined in claim 1, wherein: the first nozzle and the second bottom main body are welded and fixed, and the second nozzle and the third bottom main body are welded and fixed.

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