CN114278462A

CN114278462A - Sealed engine device and flight device

Info

Publication number: CN114278462A
Application number: CN202111423264.4A
Authority: CN
Inventors: 季朦; 高辉; 李晨轩; 许诺
Original assignee: Beijing Machinery Equipment Research Institute
Current assignee: Beijing Machinery Equipment Research Institute
Priority date: 2021-11-26
Filing date: 2021-11-26
Publication date: 2022-04-05
Anticipated expiration: 2041-11-26
Also published as: CN114278462B

Abstract

The application relates to a sealed engine device and flying device, include: the spray pipe subassembly with seal assembly rotates the setting, seal assembly includes the sealing member, the pipeline with seal assembly rotates the setting be equipped with partial stripe structure on the inside wall of sealing member, stripe structure is kept away from spacing hole, the inside wall of sealing member encloses to be established the pipeline stretches into extremely in the combustion chamber on the lateral wall of pipeline, the lateral wall of sealing member with the inside wall sealing contact in combustion chamber, just stripe structure with the lateral wall contact of pipeline, the sealing member pastes and establishes on the combustion chamber lateral wall. Therefore, the problem that the existing dynamic sealing structure is easy to leak gas at high temperature, high pressure and high speed is solved, and the sealing structure is simple.

Description

Sealed engine device and flight device

Technical Field

The application relates to the field of solid rocket engines, in particular to a sealed engine device and a flight device comprising the same.

Background

At present, a solid rocket engine commonly used for rail control systems such as guided missiles, kinetic energy interceptors and the like usually adopts a mode of rotating a spray pipe, a combustion chamber of the solid rocket engine is kept static in the working process, and the spray pipe rotates, so that a dynamic sealing structure needs to be designed aiming at the joint of the combustion chamber and a rotating shaft, great challenge is brought to the sealing performance of a dynamic sealing interface of the rotating spray pipe under the conditions of high temperature, high pressure and high speed in the working process, and the problem of air leakage of the existing dynamic sealing structure easily occurs at the conditions of high temperature, high pressure and high speed.

Disclosure of Invention

The application provides a sealed engine device and flight device to solve the problem that current dynamic seal structure appears leaking gas easily under high temperature, high pressure and high speed.

In a first aspect, the present application provides a sealed engine apparatus comprising:

the limiting assembly is provided with a combustion chamber, a limiting hole is formed in the limiting assembly, and the limiting hole is communicated with the combustion chamber;

the spray pipe assembly comprises a pipeline, and the pipeline is arranged in the limiting hole and extends into the combustion chamber;

seal assembly, the nozzle assembly with seal assembly rotates the setting, seal assembly includes the sealing member, the pipeline with seal assembly rotates the setting be equipped with partial stripe structure on the inside wall of sealing member, stripe structure keeps away from spacing hole, the inside wall of sealing member encloses to be established the pipeline stretches into to in the combustion chamber on the lateral wall of pipeline, the lateral wall of sealing member with the inside wall sealing contact in combustion chamber, just stripe structure with the lateral wall contact of pipeline, the sealing member pastes and establishes on the combustion chamber lateral wall.

Preferably, the sealing element is provided with a fixing hole, the fixing hole corresponds to the limiting hole, a part of the stripe structure is arranged on the inner side wall of the fixing hole, and the pipeline penetrates through the limiting hole and extends into the fixing hole.

Preferably, a first step and a second step are arranged on the sealing element, the first step and the second step are symmetrical relative to the central axis of the fixing hole, the first step portion is in sealing contact with the inner side wall of the combustion chamber, the second step portion is in sealing contact with the inner side wall of the combustion chamber, and a fixing position is formed between the second step and the combustion chamber.

Preferably, the seal assembly further comprises a first seal ring and a second seal ring, the first seal ring is disposed on the first fixing position, and the second seal ring is disposed on the second fixing position.

Preferably, the stripe structure is zigzag-shaped.

Preferably, the spout assembly further comprises a spout in communication with the conduit.

Preferably, spacing subassembly includes mounting and driving piece, the driving piece encloses to be established on the driving piece and with set up spacing hole on the driving piece forms spacing fixed space, the driving piece is equipped with the combustion chamber.

Preferably, the second step corresponds to the stripe structure.

Preferably, the spray pipe assembly further comprises a control valve, and the control valve is arranged on the spray pipe assembly.

In a second aspect, the present application provides a flying apparatus comprising a sealed engine apparatus as claimed in any one of the preceding claims.

This application is through be equipped with partial stripe structure on the inside wall of sealing member, the stripe structure is kept away from spacing hole, the inside wall of sealing member is enclosed to be established the pipeline stretches into extremely in the combustion chamber on the lateral wall of pipeline, the lateral wall of sealing member with the inside wall sealing contact in combustion chamber, just the stripe structure with the lateral wall contact of pipeline, the sealing member pastes and establishes on the combustion chamber lateral wall to solve current dynamic seal structure problem that gas leakage appears easily under high temperature, high pressure and high speed, and seal structure is simple.

Drawings

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

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.

FIG. 1 is a schematic illustration of a sealed engine assembly according to an embodiment of the present disclosure;

the names and corresponding reference numbers of the main components of the present application are as follows:

a limiting component 10; a combustion chamber 111; a limiting hole 112; a fixing member 12; a driver 11;

a spout assembly 20; a pipe 21; a nozzle 22;

a seal assembly 30; a seal member 31; a stripe structure 32; a fixing hole 33; a first step 34; a second step 35; a fixed position 36; a first seal ring 37; a second sealing ring 38.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

As illustrated in fig. 1, the present application provides a sealed engine apparatus comprising: spacing subassembly 10, spray tube subassembly 20 and seal assembly 30, spacing subassembly 10 has a combustion chamber 111, and set up spacing hole 112 on the spacing subassembly 10, spacing hole 112 with combustion chamber 111 intercommunication, spray tube subassembly 20 includes pipeline 21, pipeline 21 sets up in spacing hole 112 and stretch into in the combustion chamber 111, spray tube subassembly 20 with seal assembly 30 rotates the setting, seal assembly 30 includes sealing member 31, pipeline 21 with seal assembly 30 rotates the setting, be equipped with partial stripe structure 32 on the inside wall of sealing member 31, stripe structure 32 keeps away from spacing hole 112, the inside wall of sealing member 31 encloses to establish pipeline 21 stretches into to in the combustion chamber 111 on the outside wall of pipeline 21, the outside wall of sealing member 31 with the inside wall sealing contact in combustion chamber 111, and the stripe structure 32 is contacted with the outer side wall of the pipeline 21, and the sealing member 31 is attached to the side wall of the combustion chamber 111. Therefore, the problem that the existing dynamic sealing structure is easy to leak gas at high temperature, high pressure and high speed is solved, and the sealing structure is simple.

In another embodiment, the seal 31 is adapted for use at high and low temperatures, and is typically formed by ring-welding stainless steel ultra-thin-walled tubing at a temperature range of-257 deg.C to 1100 deg.C. In order to reduce the friction between the sealed pipe 21 and the shaft or the like, the sealing member 31 has a partial stripe structure 32, and preferably, the stripe structure 32 is zigzag-shaped. In practical application, the sealing member 31 is in contact with the pipe 21 of the rotary nozzle 22, and due to the small contact area of the zigzag structure, the generated friction force is small, and the normal rotation of the pipe 21 of the rotary nozzle 22 is not greatly influenced. The length of the saw-toothed structure is mainly related to the rotational speed of the pipe 21 and the friction force, and typically 3-10 teeth can be provided. In addition, the part of the sealing member 31 having the stripe structure 32 is in close contact with the rotary nozzle 22, and the part without the stripe structure 32 is not in contact with the rotary nozzle 22, so that the rotation of the rotary nozzle 21 is not affected.

In an embodiment, the sealing member 31 is provided with a fixing hole 33, the fixing hole 33 corresponds to the limiting hole 112, a part of the stripe structure 32 is disposed on an inner side wall of the fixing hole 33, and the pipeline 21 passes through the limiting hole 112 and extends into the fixing hole 33. Preferably, the sealing element 31 is a circumferential rotary structure, with a toothing, i.e. the sealing surface side, distributed only on the inner circumference side. The sealing member 31 is made of metal material, and the function of the metal sealing member 31 is to expand radially under the pressure of the medium, so as to promote the sealing member 31 to be tightly matched with the pipeline 21 of the rotary nozzle 22, thereby achieving the purpose of sealing.

In one embodiment, a first step 34 and a second step 35 are provided on the sealing member 31, the first step 34 and the second step 35 are symmetrical with respect to a central axis of the fixing hole 33, a portion of the first step 34 is in sealing contact with an inner side wall of the combustion chamber 111, another portion of the first step 34 forms a first fixing position 36 with the combustion chamber 111, a portion of the second step 35 is in sealing contact with an inner side wall of the combustion chamber 111, and a fixing position 36 is formed between the second step 35 and the combustion chamber 111. Preferably, the sealing assembly 30 further comprises a first sealing ring 38 and a second sealing ring 39, the first sealing ring 38 being disposed on the first fixing location 36, and the second sealing ring 39 being disposed on the second fixing location 37. The first sealing ring 38 and the second sealing ring 39 are made of metal materials, and have the function of expanding radially under the pressure of a medium to promote the sealing element 31 to be tightly matched with the pipeline 21, so that the sealing purpose is achieved. The high-temperature gas sprayed out of the combustion chamber has higher pressure, so that the first sealing ring 38 and the second sealing ring 39 are expanded in the radial direction after being pressed, the sealing element 31 is extruded, and the teeth of the sealing element 31 are tightly pressed on the channel, thereby achieving the purpose of sealing. Preferably, the second step 35 corresponds to the stripe structure 32.

Preferably, the nozzle assembly 20 further comprises a nozzle 22, the nozzle 22 being in communication with the conduit 21. Specifically, when the high-temperature gas sprayed from the combustion chamber has a large pressure, the pressure will be transmitted into the channel, and the pressure is transmitted to the nozzle 22 through the channel, so that the nozzle 22 can generate an acting force to adjust the movement angle of the whole flying device.

In one embodiment, the limiting assembly 10 includes a fixing member 12 and a driving member 11, the driving member 11 is disposed around the driving member 11 and forms a limiting fixing space (not shown) with a limiting hole 112 disposed on the driving member 11, wherein the limiting fixing space can limit the position of a sealing member, and the driving member 11 is provided with the combustion chamber 111. Preferably, the fixing member 12 is used to fix and limit the axial and radial positions of the sealing member 31 and the first and second sealing rings 38 and 39, without direct connection with the passage of the rotary nozzle 22, with a certain clearance. The fixing member 12 is integrally connected to the housing of the driving member 11 by conventional means such as screws, and cooperates with the combustion chamber to limit the sealing member 31 and the first and second metal sealing rings 38 and 39 to have shapes and sizes not specifically required.

In one embodiment, a control valve (not shown) is also included and is disposed on the spout assembly 20. The control valve is used for controlling the connection and disconnection between the pipeline 21 and the spray pipe 22, so that the angle of the aircraft can be adjusted at any time.

Specifically, the present application employs a combination of a metallic first seal ring 38, a second seal ring 39, and a tooth seal 31 for high temperature and high pressure rotary dynamic sealing of the passageway of the rotary nozzle 22. Can realize good sealing effect under the complex working conditions of 1000 ℃, 10MPa, high-speed rotation and the like.

The present application provides a flying device comprising a sealed engine arrangement as claimed in any preceding claim.

It is noted that, in this document, relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The foregoing are merely exemplary embodiments of the present invention, which enable those skilled in the art to understand or practice the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A sealed engine apparatus, comprising:

2. The sealed engine assembly of claim 1, wherein the seal member defines a mounting hole corresponding to the retention hole, and wherein a portion of the striation is disposed on an inner sidewall of the mounting hole, and wherein the conduit extends through the retention hole and into the mounting hole.

3. The sealed engine apparatus of claim 2, wherein the seal member has a first step and a second step, the first step and the second step are symmetrical with respect to a central axis of the fixing hole, the first step portion is in sealing contact with the inner side wall of the combustion chamber, the second step portion is in sealing contact with the inner side wall of the combustion chamber, and a fixing position is formed between the second step and the combustion chamber.

4. The sealed engine apparatus of claim 3, wherein the seal assembly further comprises a first seal ring disposed in the first fixed position and a second seal ring disposed in the second fixed position.

5. The sealed engine apparatus of claim 1, wherein the striation structure is saw-toothed.

6. The sealed engine apparatus of claim 1, wherein the nozzle assembly further comprises a nozzle in communication with the conduit.

7. The sealed engine apparatus of claim 1, wherein the limiting assembly comprises a fixing member and a driving member, the driving member is enclosed on the driving member and forms a limiting fixing space with a limiting hole provided on the driving member, and the driving member is provided with the combustion chamber.

8. The sealed engine apparatus of claim 2, wherein the second step corresponds to the striation structure.

9. The sealed engine apparatus of claim 1, further comprising a control valve disposed on the spout assembly.

10. A flying device comprising a sealed engine apparatus according to any one of claims 1 to 9.