CN112483428A

CN112483428A - End face sealing test device for turbopump of rocket engine

Info

Publication number: CN112483428A
Application number: CN202011357110.5A
Authority: CN
Inventors: 刘青丽; 王娜
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-11-27
Filing date: 2020-11-27
Publication date: 2021-03-12

Abstract

The invention discloses an end face sealing test device for a turbopump of a rocket engine, which comprises a rack device for supporting the turbopump of the rocket engine and also comprises an interface device for connecting a liquid inlet and a liquid outlet of the turbopump of the rocket engine, wherein a pipeline device for conveying is arranged behind the interface device, a water tank device for containing test liquid is arranged below the rack device, and a telescopic device for moving is arranged on the rack device. According to the invention, through the arrangement of automatic compression clamping, the assembly is simplified, the installation of a plurality of bolts and nuts is avoided, and the labor intensity of workers is reduced; through the arrangement of test solution backflow recycling, the requirement and waste of the test solution are reduced, and the utilization rate of the test solution is improved; through the automatic telescopic setting, the cooperation with different length rocket engine turbopump liquid outlet terminal surfaces has been guaranteed, test device's application scope has been increased.

Description

End face sealing test device for turbopump of rocket engine

Technical Field

The invention relates to the technical field of advanced aerospace power design, in particular to an end face sealing test device for a turbopump of a rocket engine.

Background

The engine is referred to as the heart of the rocket, and the turbopump is also referred to as the heart of the rocket engine. The turbopump is a high-speed rotating component in the liquid rocket engine and is also the only high-speed rotating machine in an important assembly of the engine. Statistically, about half of the failures of rocket engines occur in turbopumps. The design of the turbopump has many requirements, for example, the requirement of the reliability of engine distribution is met under all working conditions of the engine. Meanwhile, in order to ensure that the liquid rocket engine has smaller size and mass, the turbopump device has smaller size and mass. The liquid rocket engine turbopump is very emphasised by light weight and high performance in design, and many turbopump assemblies are designed to be close to the limit of the technical development level. High rotational speeds require good bearings; high pressure, requires good sealing; high efficiency, good leaf profile is required; high performance, inducer with high pumping performance is required to reduce the pressure and weight of the tank. In order to ensure reliable fuel delivery of the rocket engine turbopump, end face seal tests are required to prevent fuel leakage and danger.

However, in the prior art, the end face sealing test device for the turbopump of the rocket engine needs to be mounted by dismounting a plurality of bolts and nuts, so that the following problems are caused: 1. the assembly cannot be simplified through the automatic pressing and clamping arrangement, so that the labor intensity of workers is increased; 2. the arrangement of test solution backflow recycling is omitted, so that the requirement and waste of the test solution are increased, and the utilization rate of the test solution is reduced; 3. the automatic telescopic device is not arranged, the matching with the end faces of the liquid outlets of the turbopumps of rocket engines with different lengths can not be ensured, and the application range of the test device is reduced.

Disclosure of Invention

The invention aims to solve the problems and provide an end face seal testing device for a turbopump of a rocket engine.

The invention realizes the purpose through the following technical scheme:

an end face sealing test device for a turbopump of a rocket engine comprises a rack device for supporting the turbopump of the rocket engine and also comprises an interface device for connecting a liquid inlet and a liquid outlet of the turbopump of the rocket engine, wherein a pipeline device for conveying is arranged behind the interface device; the rack device comprises a supporting table, four supporting legs are uniformly distributed at four corners of the bottom of the supporting table, a fixing frame is mounted behind the supporting table, and an avoidance groove is formed in front of the fixing frame; the interface device comprises a supporting plate, a stop plate is arranged in front of the supporting plate, a connecting pipe is arranged behind the supporting plate, four first supporting plates are uniformly distributed around the supporting plate, a first air cylinder is arranged on the first supporting plate, a limiting block is arranged below the first air cylinder, and an inclined chamfer is arranged on the inner side of the limiting block; the pipeline device comprises a water outlet pipe, a connecting seat is arranged on the water outlet pipe, a water inlet pipe is arranged behind the water outlet pipe, and a filter head is arranged at the bottom of the water inlet pipe; the water tank device comprises a water tank body, a filling pipe is arranged at the top of the water tank body, a sealing cover is mounted on the filling pipe, a sealing ring is arranged on one side of the water tank body, a through hole is formed in the bottom of the rear wall of the water tank body, a guide plate is arranged in the water tank body, a water outlet pipe is connected with the sealing ring in a plugging and pulling mode, and a water inlet pipe is fixedly connected with the water tank body.

Preferably: the telescopic device comprises two second support plates which are symmetrically arranged, a servo motor is installed on one side of each second support plate, and a lead screw is installed on one side of each servo motor.

According to the arrangement, the second support plate supports the servo motor to drive the screw rod to rotate so as to push the connecting seat to move.

Preferably: the telescopic device comprises two third support plates which are symmetrically arranged, and a second cylinder is arranged in the middle of each third support plate.

So set up, the third extension board supports the flexible promotion of second cylinder the connecting seat removes.

Preferably: the guide plate is V-shaped, and the guide plate and the water tank body are welded together.

So set up, the V-arrangement the guide plate has alleviateed the direct impact of test liquid, and the welding has guaranteed the guide plate is firm reliable.

Preferably: the supporting plate, the spigot plate and the connecting pipe are all made of 204 stainless steel materials, and the supporting plate, the spigot plate and the connecting pipe are integrally formed.

So set up, 204 stainless steel material has guaranteed the backup pad the tang board with connecting pipe corrosion resistance, integrated into one piece has guaranteed the backup pad the tang board with the intensity and the sealed of connecting pipe.

Preferably: the outlet pipe with the inlet tube respectively with connecting pipe clamp connection, the filter head with the sealed threaded connection of inlet tube.

So set up, the clamp connection dismouting of being convenient for is better the outlet pipe with the inlet tube, sealed threaded connection has guaranteed the sealing of filter head.

Preferably: the first air cylinder is respectively connected with the first support plate and the limiting block through bolts, and the fixing frame is respectively connected with the support table and the support plate through bolts.

So set up, bolted connection is convenient for the dismouting first cylinder with the mount is maintained.

Preferably: the filling pipe and the water tank body are welded together, and the sealing cover is connected with the filling pipe in a buckling mode.

So set up, the welding has guaranteed the filling pipe is firm reliable, and the buckle is connected the dismouting of being convenient for sealed lid.

Preferably: the second support plate and the telescopic support platform are welded together, the servo motor is connected with the second support plate through a bolt, and the lead screw is connected with the connecting seat through threads.

According to the arrangement, welding ensures that the second support plate is firm and reliable, the bolt connection is convenient for disassembly, assembly and maintenance of the servo motor, and the threaded connection ensures that the screw rod pushes the connecting seat to move.

Preferably: the third supporting plate and the telescopic supporting platform are welded together, and the second cylinder is respectively connected with the third supporting plate and the connecting seat through bolts.

So set up, the welding has guaranteed the third extension board is firm reliable, bolted connection is convenient for dismouting maintenance the second cylinder.

The working principle is as follows: placing a rocket engine turbopump on the supporting table, aligning and inserting a liquid inlet of the rocket engine turbopump into the spigot plate, enabling the first supporting plate to support the first air cylinder to push the limiting block to move towards the middle from the periphery, pressing the liquid inlet of the rocket engine turbopump tightly, enabling the end surface of the liquid inlet to be attached and sealed with the spigot plate, then enabling the second supporting plate to support the servo motor to drive the screw rod to rotate to push the connecting seat to move, or enabling the third supporting plate to support the second air cylinder to stretch and push the connecting seat to move, enabling the connecting seat to drive the water outlet pipe to be close to the liquid outlet of the rocket engine turbopump, enabling the water outlet pipe to further penetrate into the water tank body, aligning and inserting the liquid outlet of the rocket engine turbopump into the spigot plate, enabling the first supporting plate to support the first air cylinder to push the limiting, and (3) compressing a liquid outlet of the turbopump of the rocket engine, enabling the end face of the liquid outlet to be attached and sealed with the seam allowance plate, starting the turbopump of the rocket engine, extracting the test liquid filtered by the filter head in the water tank body through the water inlet pipe, and flowing back into the water tank body through the water outlet pipe.

Compared with the prior art, the invention has the following beneficial effects:

1. through the arrangement of automatic compression clamping, the assembly is simplified, the installation of a plurality of bolts and nuts is avoided, and the labor intensity of workers is reduced;

2. through the arrangement of test solution backflow recycling, the requirement and waste of the test solution are reduced, and the utilization rate of the test solution is improved;

3. through the automatic telescopic setting, the cooperation with different length rocket engine turbopump liquid outlet terminal surfaces has been guaranteed, test device's application scope has been increased.

Drawings

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 that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

FIG. 1 is a schematic structural diagram of an end face seal testing device for a turbopump of a rocket engine according to the present invention;

FIG. 2 is a schematic view of a frame assembly of the end face seal test device for a turbopump of a rocket engine according to the present invention;

FIG. 3 is a formal isometric view of an interface device of an end-face seal testing apparatus for a rocket engine turbopump in accordance with the present invention;

FIG. 4 is a rear isometric view of an interface device for a rocket engine turbopump end-face seal testing apparatus in accordance with the present invention;

FIG. 5 is a schematic view of a piping arrangement of an end face seal test device for a turbopump of a rocket engine according to the present invention;

FIG. 6 is a formal cross-sectional view of a water tank device of an end face seal testing device for a turbopump of a rocket engine according to the present invention;

FIG. 7 is a schematic view of a telescoping device of embodiment 1 of an end face seal testing device for a turbopump of a rocket engine according to the present invention;

fig. 8 is a schematic view of a telescopic device in embodiment 2 of the end face seal testing device for the turbopump of the rocket engine.

The reference numerals are explained below:

1. a rack device; 101. a support table; 102. supporting legs; 103. a fixed mount; 104. an avoidance groove; 2. an interface device; 201. a support plate; 202. a spigot plate; 203. a first support plate; 204. a first cylinder; 205. a limiting block; 206. a connecting pipe; 207. chamfering; 3. a pipeline device; 301. a water outlet pipe; 302. a connecting seat; 303. a water inlet pipe; 304. a filter head; 4. a water tank device; 401. a water tank body; 402. a seal ring; 403. a baffle; 404. a filling pipe; 405. a sealing cover; 406. a through hole; 5. a telescoping device; 501. a second support plate; 502. a servo motor; 503. a lead screw; 504. a third support plate; 505. a second cylinder.

Detailed Description

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.

The invention will be further described with reference to the accompanying drawings in which:

example 1

As shown in fig. 1-7, an end face sealing test device for a turbopump of a rocket engine comprises a rack device 1 for supporting the turbopump of the rocket engine, and further comprises an interface device 2 for connecting a liquid inlet and a liquid outlet of the turbopump of the rocket engine, wherein a pipeline device 3 for conveying is installed behind the interface device 2, a water tank device 4 for containing test liquid is arranged below the rack device 1, and a telescopic device 5 for moving is arranged above the rack device 1; the rack device 1 comprises a support table 101, four support legs 102 are uniformly distributed at four corners of the bottom of the support table 101, a fixing frame 103 is arranged behind the support table 101, and an avoidance groove 104 is arranged in front of the fixing frame 103; the interface device 2 comprises a supporting plate 201, a spigot plate 202 is arranged in front of the supporting plate 201, a connecting pipe 206 is arranged behind the supporting plate 201, four first supporting plates 203 are uniformly distributed around the supporting plate 201, a first cylinder 204 is arranged on the first supporting plates 203, a limiting block 205 is arranged below the first cylinder 204, and an inclined chamfer 207 is arranged on the inner side of the limiting block 205; the pipeline device 3 comprises a water outlet pipe 301, a connecting seat 302 is arranged on the upper surface of the water outlet pipe 301, a water inlet pipe 303 is arranged behind the water outlet pipe 301, and a filter head 304 is arranged at the bottom of the water inlet pipe 303; the water tank device 4 comprises a water tank body 401, a filling pipe 404 is arranged at the top of the water tank body 401, a sealing cover 405 is arranged on the filling pipe 404, a sealing ring 402 is arranged on one side of the water tank body 401, a through hole 406 is arranged at the bottom of the rear wall of the water tank body 401, a guide plate 403 is arranged in the water tank body 401, a water outlet pipe 301 is connected with the sealing ring 402 in a plugging and unplugging manner, and a water inlet pipe 303 is fixedly connected with.

Preferably: the telescopic device 5 comprises two second support plates 501 which are symmetrically arranged, a servo motor 502 is arranged on one side of each second support plate 501, a lead screw 503 is arranged on one side of each servo motor 502, and the second support plates 501 support the servo motors 502 to drive the lead screws 503 to rotate to push the connecting seats 302 to move; the guide plate 403 is V-shaped, the guide plate 403 and the water tank body 401 are welded together, the V-shaped guide plate 403 relieves the direct impact of the test liquid, and the welding ensures that the guide plate 403 is stable and reliable; the support plate 201, the spigot plate 202 and the connecting pipe 206 are all made of 204 stainless steel materials, the support plate 201, the spigot plate 202 and the connecting pipe 206 are integrally formed, the 204 stainless steel materials ensure the corrosion resistance of the support plate 201, the spigot plate 202 and the connecting pipe 206, and the strength and the sealing of the support plate 201, the spigot plate 202 and the connecting pipe 206 are ensured by the integral forming; the water outlet pipe 301 and the water inlet pipe 303 are respectively connected with the connecting pipe 206 in a clamping manner, the filter head 304 is in sealing threaded connection with the water inlet pipe 303, the clamping connection facilitates the assembly and disassembly of the water outlet pipe 301 and the water inlet pipe 303, and the sealing threaded connection ensures the sealing of the filter head 304; the first cylinder 204 is respectively in bolted connection with the first supporting plate 203 and the limiting block 205, the fixing frame 103 is respectively in bolted connection with the supporting table 101 and the supporting plate 201, and the bolted connection facilitates the disassembly and assembly of the first cylinder 204 and the fixing frame 103 for maintenance; the filling pipe 404 and the water tank body 401 are welded together, the sealing cover 405 and the filling pipe 404 are connected in a buckling mode, the welding ensures that the filling pipe 404 is firm and reliable, and the buckling connection facilitates the disassembly and assembly of the sealing cover 405; the second support plate 501 and the telescopic support platform 101 are welded together, the servo motor 502 is connected with the second support plate 501 through bolts, the lead screw 503 is connected with the connecting seat 302 through threads, the second support plate 501 is firmly and reliably welded, the servo motor 502 is convenient to disassemble, assemble and maintain through bolts, and the lead screw 503 is guaranteed to push the connecting seat 302 to move through threads.

Example 2

As shown in fig. 8, embodiment 2 differs from embodiment 1 in that: the telescopic device 5 comprises two second support plates 501 which are symmetrically arranged, a second cylinder 505 is arranged in the middle of each second support plate 501, and the third support plate 504 supports the second cylinder 505 to stretch and push the connecting seat 302 to move; the third supporting plate 504 and the telescopic supporting platform 101 are welded together, the second cylinder 505 is respectively in bolted connection with the third supporting plate 504 and the connecting seat 302, the third supporting plate 504 is guaranteed to be firm and reliable through welding, and the second cylinder 505 is convenient to disassemble, assemble and maintain through bolted connection.

The working principle is as follows: the rocket engine turbopump is placed on the support table 101, a liquid inlet of the rocket engine turbopump is aligned to the insertion spigot plate 202, the first support plate 203 supports the first air cylinder 204 to push the limiting block 205 to move towards the middle from the periphery, the liquid inlet of the rocket engine turbopump is tightly pressed, the end face of the liquid inlet is enabled to be attached and sealed with the spigot plate 202, then the second support plate 501 supports the servo motor 502 to drive the lead screw 503 to rotate to push the connecting seat 302 to move, or the third support plate 504 supports the second air cylinder 505 to stretch and push the connecting seat 302 to move, the connecting seat 302 drives the water outlet pipe 301 to be close to the liquid outlet of the rocket engine turbopump, the water outlet pipe 301 is further extended into the water tank body 401, the liquid outlet of the rocket engine turbopump is aligned to the insertion spigot plate 202, the first support plate 203 supports the first air cylinder 204 to push the limiting block 205 to move towards the, and starting the turbopump of the rocket engine, pumping the test liquid filtered by the filter head 304 in the water tank body 401 through the water inlet pipe 303, and flowing back into the water tank body 401 through the water outlet pipe 301.

The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed.

Claims

1. The utility model provides an end face seal test device for rocket engine turbopump, includes the frame device that is used for supporting rocket engine turbopump, its characterized in that: the test device is characterized by also comprising an interface device for connecting a liquid inlet and a liquid outlet of a turbopump of the rocket engine, wherein a pipeline device for conveying is arranged behind the interface device, a water tank device for containing test liquid is arranged below the rack device, and a telescopic device for moving is arranged above the rack device;

the rack device comprises a supporting table, four supporting legs are uniformly distributed at four corners of the bottom of the supporting table, a fixing frame is mounted behind the supporting table, and an avoidance groove is formed in front of the fixing frame;

the interface device comprises a supporting plate, a stop plate is arranged in front of the supporting plate, a connecting pipe is arranged behind the supporting plate, four first supporting plates are uniformly distributed around the supporting plate, a first air cylinder is arranged on the first supporting plate, a limiting block is arranged below the first air cylinder, and an inclined chamfer is arranged on the inner side of the limiting block;

the pipeline device comprises a water outlet pipe, a connecting seat is arranged on the water outlet pipe, a water inlet pipe is arranged behind the water outlet pipe, and a filter head is arranged at the bottom of the water inlet pipe;

the water tank device comprises a water tank body, a filling pipe is arranged at the top of the water tank body, a sealing cover is mounted on the filling pipe, a sealing ring is arranged on one side of the water tank body, a through hole is formed in the bottom of the rear wall of the water tank body, a guide plate is arranged in the water tank body, a water outlet pipe is connected with the sealing ring in a plugging and pulling mode, and a water inlet pipe is fixedly connected with the water tank body.

2. A face seal test apparatus for a rocket engine turbopump according to claim 1, wherein: the telescopic device comprises two second support plates which are symmetrically arranged, a servo motor is installed on one side of each second support plate, and a lead screw is installed on one side of each servo motor.

3. A face seal test apparatus for a rocket engine turbopump according to claim 1, wherein: the telescopic device comprises two third support plates which are symmetrically arranged, and a second cylinder is arranged in the middle of each third support plate.

4. A face seal test apparatus for a rocket engine turbopump according to claim 1, wherein: the guide plate is V-shaped, and the guide plate and the water tank body are welded together.

5. A face seal test apparatus for a rocket engine turbopump according to claim 1, wherein: the supporting plate, the spigot plate and the connecting pipe are all made of 204 stainless steel materials, and the supporting plate, the spigot plate and the connecting pipe are integrally formed.

6. A face seal test apparatus for a rocket engine turbopump according to claim 1, wherein: the outlet pipe with the inlet tube respectively with connecting pipe clamp connection, the filter head with the sealed threaded connection of inlet tube.

7. A face seal test apparatus for a rocket engine turbopump according to claim 1, wherein: the first air cylinder is respectively connected with the first support plate and the limiting block through bolts, and the fixing frame is respectively connected with the support table and the support plate through bolts.

8. A face seal test apparatus for a rocket engine turbopump according to claim 1, wherein: the filling pipe and the water tank body are welded together, and the sealing cover is connected with the filling pipe in a buckling mode.

9. A face seal test device for a rocket engine turbopump according to claim 2, characterized in that: the second support plate and the telescopic support platform are welded together, the servo motor is connected with the second support plate through a bolt, and the lead screw is connected with the connecting seat through threads.

10. A face seal test device for a rocket engine turbopump according to claim 3, characterized in that: the third supporting plate and the telescopic supporting platform are welded together, and the second cylinder is respectively connected with the third supporting plate and the connecting seat through bolts.