CN215808631U

CN215808631U - Rocket engine combustion chamber air supply device

Info

Publication number: CN215808631U
Application number: CN202122324842.0U
Authority: CN
Inventors: 李晶; 胡红梅; 刘志; 曾强
Original assignee: Xiangyang Honghang Industry Co ltd
Current assignee: Xiangyang Honghang Industry Co ltd
Priority date: 2021-09-24
Filing date: 2021-09-24
Publication date: 2022-02-11
Anticipated expiration: 2031-09-24

Abstract

The utility model discloses a rocket engine combustion chamber air supply device, which comprises an upper adjusting plate, a lower adjusting plate and a second baffle plate, wherein one side of the top of the upper adjusting plate is fixedly connected with an air cylinder, the top of the air cylinder is fixedly connected with the top of the inner wall of a shell, the top of the second baffle plate is fixedly connected with a supporting spring, and the top end of the supporting spring is fixedly connected with the top of the inner wall of the shell. This rocket engine combustion chamber air supply arrangement, through at last regulating plate, under the cooperation of regulating plate, second baffle, cylinder, supporting spring, picture peg, recess and backup pad is used, the effectual bore that changes inlet air channel for fuel combustion in the engine is more abundant, and the bore of having solved current air inlet duct is certain, can not change, thereby makes the not intensive mixing of oxidant and fuel, leads to the lower problem of combustion efficiency of engine.

Description

Rocket engine combustion chamber air supply device

Technical Field

The utility model relates to the technical field of engines, in particular to an air supply device for a combustion chamber of a rocket engine.

Background

The combustion chamber is an important component of a liquid rocket engine, producing all or most of the thrust of the liquid rocket engine. The liquid propellant enters the combustion chamber through the injector to finish the processes of atomization, mixing and combustion, and high-temperature and high-pressure gas is generated to convert the chemical energy of the propellant into heat energy. The gas converts heat energy into kinetic energy in the jet pipe, and the kinetic energy is discharged from the outlet section of the jet pipe at a high speed to generate engine thrust.

The oxidant of the liquid rocket engine is injected into the combustion chamber through the supercharging system and then burns with the fuel, so that the combustion process represents typical diffusion combustion, and the caliber of the existing air inlet duct is fixed and cannot be changed, so that the oxidant and the fuel are not fully mixed, and the combustion efficiency of the engine is lower.

SUMMERY OF THE UTILITY MODEL

Aiming at the defects of the prior art, the utility model provides an air supply device for a combustion chamber of a rocket engine, which solves the problem that the combustion efficiency of the engine is lower due to insufficient mixing of an oxidant and a fuel because the caliber of an existing air inlet duct is fixed and cannot be changed.

In order to achieve the purpose, the utility model is realized by the following technical scheme: the utility model provides a rocket engine combustion chamber air supply arrangement, includes the casing and sets up propellant inlet joint and propellant outlet joint on the casing, the first baffle of bottom fixedly connected with of shells inner wall, shells inner wall's first baffle of top fixedly connected with and second baffle, be provided with adjustment mechanism on the casing.

Adjustment mechanism includes regulating plate, lower regulating plate and second baffle, go up one side fixedly connected with cylinder at regulating plate top, the top of cylinder and shells inner wall's top fixed connection, the top fixedly connected with supporting spring of second baffle, supporting spring's top and shells inner wall's top fixed connection, the bottom of second baffle and the opposite side contact at last regulating plate top, go up the bottom fixedly connected with picture peg of regulating plate, be provided with the recess on the lower regulating plate, the inside of recess and the inside looks adaptation of picture peg, the bottom fixedly connected with backup pad of regulating plate down, the bottom of backup pad and shells inner wall's bottom fixed connection.

Preferably, first baffle, second baffle and second baffle all set up and are the arc, the bottom of lower regulating plate and the top fixed connection of first baffle.

Preferably, the lower adjusting plate is formed by integrally forming a first connecting plate and a second connecting plate, and the groove is formed in the top of the second connecting plate.

Preferably, the cross sections of the first connecting plate and the upper adjusting plate are both semicircular, and the cross section calibers of the first connecting plate and the upper adjusting plate are the same.

Preferably, the top of the inner wall of the shell is fixedly connected with a first connecting cover outside the cylinder, a first through hole is formed in the bottom of the first connecting cover in a penetrating mode, and a second connecting cover is slidably connected inside the first through hole.

Preferably, the bottom of the second connecting cover is provided with a second through hole in a penetrating manner, the inside of the second through hole is matched with the outer surface of the output end of the air cylinder, and the bottom of the second connecting cover is fixedly connected with the top of the upper adjusting plate.

Advantageous effects

The utility model provides an air supply device for a combustion chamber of a rocket engine. Compared with the prior art, the method has the following beneficial effects:

(1) this rocket engine combustion chamber air supply arrangement, through at last regulating plate, under the cooperation of regulating plate, second baffle, cylinder, supporting spring, picture peg, recess and backup pad is used, the effectual bore that changes inlet air channel for fuel combustion in the engine is more abundant, and the bore of having solved current air inlet duct is certain, can not change, thereby makes the not intensive mixing of oxidant and fuel, leads to the lower problem of combustion efficiency of engine.

(2) This rocket engine combustion chamber air supply arrangement uses through the cooperation at first connecting cover, first through-hole, second connecting cover and second through-hole under, realizes wrapping up the cylinder to reach the purpose of protecting the cylinder.

Drawings

FIG. 1 is a front view of the internal structure of the present invention;

FIG. 2 is a side cross-sectional view of an upper adjustment plate and a lower adjustment plate of the present invention;

FIG. 3 is a front cross-sectional view of a first coupling housing and a second coupling housing of the present invention.

In the figure: 1-shell, 2-propellant inlet joint, 3-propellant outlet joint, 4-first baffle, 5-first baffle, 6-second baffle, 7-adjusting mechanism, 71-upper adjusting plate, 72-lower adjusting plate, 721-first connecting plate, 722-second connecting plate, 73-second baffle, 74-air cylinder, 75-supporting spring, 76-plug plate, 77-groove, 78-supporting plate, 8-first connecting cover, 9-first through hole, 10-second connecting cover and 11-second through hole.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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 invention.

Referring to fig. 1-3, the present invention provides a technical solution: a rocket engine combustion chamber air supply device comprises a shell 1, and a propellant inlet joint 2 and a propellant outlet joint 3 which are arranged on the shell 1, wherein the bottom of the inner wall of the shell 1 is fixedly connected with a first baffle 4, the top of the inner wall of the shell 1 is fixedly connected with a first clapboard 5 and a second clapboard 6, and the shell 1 is provided with an adjusting mechanism 7; the adjusting mechanism 7 comprises an upper adjusting plate 71, a lower adjusting plate 72 and a second baffle plate 73, wherein one side of the top of the upper adjusting plate 71 is fixedly connected with an air cylinder 74, the top of the air cylinder 74 is fixedly connected with the top of the inner wall of the shell 1, the top of the second baffle plate 73 is fixedly connected with a supporting spring 75, the top end of the supporting spring 75 is fixedly connected with the top of the inner wall of the shell 1, the bottom of the second baffle plate 73 is contacted with the other side of the top of the upper adjusting plate 71, the bottom of the upper adjusting plate 71 is fixedly connected with an inserting plate 76, the lower adjusting plate 72 is provided with a groove 77, the interior of the groove 77 is matched with the interior of the inserting plate 76, the bottom of the lower adjusting plate 72 is fixedly connected with the bottom of the inner wall of the shell 1, and under the matching use of the upper adjusting plate 71, the lower adjusting plate 72, the second baffle plate 73, the air cylinder 74, the supporting spring 75, the inserting plate 76, the groove 77 and the supporting plate 78, the caliber of an air inlet channel is effectively changed, fuel in an engine is combusted more fully, the problem that the existing air inlet channel has a certain caliber and cannot be changed, so that oxidant and fuel are not fully mixed, and the combustion efficiency of the engine is low is solved, the first baffle plate 4, the first partition plate 5, the second partition plate 6 and the second baffle plate 73 are all arranged in an arc shape, the bottom of the lower adjusting plate 72 is fixedly connected with the top of the first baffle plate 4, the lower adjusting plate 72 is formed by integrally forming a first connecting plate 721 and a second connecting plate 722, the groove 77 is formed in the top of the second connecting plate 722, the cross sections of the first connecting plate 721 and the upper adjusting plate 71 are both in a semicircular shape, the calibers of the cross sections of the first connecting plate 721 and the upper adjusting plate 71 are the same, the top of the inner wall of the shell 1 and the outer part of the air cylinder 74 are fixedly connected with a first connecting cover 8, the bottom of the first connecting cover 8 is provided with a first through hole 9, the inside sliding connection of first through-hole 9 has second connecting cover 10, second connecting cover 10's bottom is run through and has been seted up second through-hole 11, the inside of second through-hole 11 and the surface looks adaptation of cylinder 74 output, the bottom of second connecting cover 10 and the top fixed connection of last regulating plate 71, through at first connecting cover 8, first through-hole 9, the cooperation of second connecting cover 10 and second through-hole 11 is used down, the realization wraps up cylinder 74, thereby reach the purpose of protecting cylinder 74.

And those not described in detail in this specification are well within the skill of those in the art.

During operation, through opening cylinder 74, and then drive upper adjusting plate 71 and rise, thereby utilize upper adjusting plate 71 to drive picture peg 76 and rise, and then make the whole bore grow that forms between upper adjusting plate 71 and the lower adjusting plate 72, the effectual bore that changes air inlet channel, make the fuel burning in the engine more abundant, it is certain to have solved the bore of current air inlet duct, can not change, thereby make the not intensive mixing of oxidant and fuel, lead to the lower problem of combustion efficiency of engine, use at cylinder 74 work, drive second connecting cover 10 to first connecting cover 8 internal motion, make the output and the second connecting cover 10 synchronous motion of cylinder 74, the realization wraps up cylinder 74, thereby reach the purpose of protecting cylinder 74.

It is noted that, herein, 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.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. A rocket engine combustion chamber air supply arrangement, includes casing (1) and sets up propellant inlet joint (2) and propellant outlet joint (3) on casing (1), its characterized in that: the bottom of the inner wall of the shell (1) is fixedly connected with a first baffle (4), the top of the inner wall of the shell (1) is fixedly connected with a first partition plate (5) and a second partition plate (6), and the shell (1) is provided with an adjusting mechanism (7);

the adjusting mechanism (7) comprises an upper adjusting plate (71), a lower adjusting plate (72) and a second baffle plate (73), wherein a cylinder (74) is fixedly connected to one side of the top of the upper adjusting plate (71), the top of the cylinder (74) is fixedly connected with the top of the inner wall of the shell (1), a supporting spring (75) is fixedly connected to the top of the second baffle plate (73), the top end of the supporting spring (75) is fixedly connected with the top of the inner wall of the shell (1), the bottom of the second baffle plate (73) is in contact with the other side of the top of the upper adjusting plate (71), a plugboard (76) is fixedly connected to the bottom of the upper adjusting plate (71), a groove (77) is formed in the lower adjusting plate (72), the inside of the groove (77) is matched with the inside of the plugboard (76), and a supporting plate (78) is fixedly connected to the bottom of the lower adjusting plate (72), the bottom of the supporting plate (78) is fixedly connected with the bottom of the inner wall of the shell (1).

2. A rocket engine combustion chamber air supply apparatus as recited in claim 1, wherein: first baffle (4), first baffle (5), second baffle (6) and second baffle (73) all set up and are the arc, the bottom of lower regulating plate (72) and the top fixed connection of first baffle (4).

3. A rocket engine combustion chamber air supply apparatus as recited in claim 1, wherein: the lower adjusting plate (72) is formed by integrally molding a first connecting plate (721) and a second connecting plate (722), and the groove (77) is formed at the top of the second connecting plate (722).

4. A rocket engine combustion chamber air supply apparatus as recited in claim 3, wherein: the cross sections of the first connecting plate (721) and the upper adjusting plate (71) are semicircular, and the cross section calibers of the first connecting plate (721) and the upper adjusting plate (71) are the same.

5. A rocket engine combustion chamber air supply apparatus as recited in claim 1, wherein: the top of casing (1) inner wall just is located the first connecting cover (8) of outside fixedly connected with of cylinder (74), first through-hole (9) have been seted up in the bottom of first connecting cover (8) run through, the inside sliding connection of first through-hole (9) has second connecting cover (10).

6. A rocket engine combustion chamber air supply arrangement as recited in claim 5, wherein: the bottom of second connecting cover (10) is run through and has been seted up second through-hole (11), the inside of second through-hole (11) and the surface looks adaptation of cylinder (74) output, the bottom of second connecting cover (10) and the top fixed connection of last regulating plate (71).