Turbine pump end face sealing test system and method

Abstract

The invention provides a turbine pump end face sealing test system and method.The turbine pump end face sealing test system comprises a power mechanism, an adjusting mechanism and a sealing mechanism, and the power mechanism is used for driving a low-temperature pump to be detected; the adjusting mechanism is used for adjusting the output power of the power mechanism; and the sealing mechanism is used for establishing end face sealing of the to-be-detected low-temperature pump. According to the technical scheme, independent adjustment of the rotating speed of the turbine pump and the pressure and flow of the sealing cavity can be achieved, and testing of end face sealing of the turbine pump under different working conditions is met.

Description

Background Art

[0002] Cryogenic liquid rocket engines are rocket engines that use low-boiling-point liquid as propellant, and have the advantages of high performance, high safety, and good environmental protection. The oxidizer is generally liquid oxygen, and the fuel is generally liquid hydrogen or liquid methane. In recent years, with the development of materials, thermal insulation, 3D printing and other technologies, as well as the increase in demand for rocket recovery, satellite networking, manned spaceflight, and deep space exploration, cryogenic liquid rocket engines have become a hot research direction.

[0003] As the "heart" of cryogenic liquid rocket engines, turbo pumps are a key link in the development of cryogenic liquid rocket engines. Due to the low boiling point of cryogenic propellants, they are very easy to vaporize and leak, and have high requirements for sealing. Therefore, the end face sealing research of cryogenic liquid rocket engine turbo pumps has become an urgent need in engine development.

[0004] There is a test method for the end face seal of the hydrogen-oxygen rocket engine turbine pump. It uses a motor, coupling and speed control device to provide power to drive the pump shaft to rotate. The test system is complex and costly, which is suitable for batch testing. For the cryogenic liquid engine in the development stage, the excessive complexity and cost are not conducive to the development work. Summary of the invention

[0005] The present application provides a test system and method for a turbine pump end face seal, which are used to solve the problems of high complexity and cost in the prior art.

[0006] In a first aspect, a test system for a turbine pump end face seal is provided, comprising: a power mechanism, an adjustment mechanism and a sealing mechanism, wherein:

[0007] The power mechanism is used to drive the cryopump to be tested;

[0008] The regulating mechanism is used to regulate the output power of the power mechanism;

[0009] The sealing mechanism is used to establish the end face seal of the cryopump to be tested.

[0010] In the above technical solution, a power mechanism, an adjusting mechanism and a sealing mechanism are provided, wherein the power mechanism is used to drive the cryopump to be tested; the adjusting mechanism is used to adjust the output power of the power mechanism; the sealing mechanism is used to establish the end face seal of the cryopump to be tested; and the independent adjustment of the turbine pump speed, the sealing chamber pressure and the flow rate can be realized to meet the test of the turbine pump end face seal under different working conditions.

[0011] In a specific embodiment, the power mechanism includes an exhaust pipe and a turbine disk arranged in the exhaust pipe, wherein:

[0012] The turbine disk is connected to the power shaft of the cryopump to be tested, and is used to drive the cryopump to be tested.

[0013] In a specific implementation scheme, the regulating mechanism includes a solenoid valve and a first regulating unit, wherein:

[0014] The solenoid valve, the first regulating unit and the air inlet of the turbine disc are connected through a pipeline, and the solenoid valve is communicated with the swirling air inlet.

[0015] In a specific embodiment, the regulating mechanism further includes a pressure reducing valve, wherein:

[0016] The pressure reducing valve is connected to the solenoid valve and the swirling gas inlet.

[0017] In a specific embodiment, the sealing mechanism includes a second adjustment unit, wherein:

[0018] One end of the second regulating unit is connected to the pump outlet of the cryopump to be tested through a pipeline, and the other end of the second regulating unit is connected to the sealed cavity inlet of the cryopump to be tested through a pipeline.

[0019] In a specific embodiment, a third regulating unit is further included, wherein:

[0020] One end of the third regulating unit is connected to the sealed cavity inlet of the cryopump to be tested, and the other end is connected to the pump outlet.

[0021] In a specific embodiment, a fourth regulating unit is further included, wherein:

[0022] One end of the fourth regulating unit is connected to the sealing outlet of the cryopump to be inspected, and the other end is connected to the pump outlet and the outlet of the third regulating unit.

[0023] In a specific embodiment, the pressure reducing valve is a membrane pressure reducing valve or an adjustable pressure reducing valve.

[0024] In a specific implementation manner, the second regulating unit, the third regulating unit and the fourth regulating unit are cavitation venturis or orifice plates.

[0025] In a second aspect, a test method for a turbine pump end face seal is provided, comprising the following steps:

[0026] Precool the cryopump to be tested;

[0027] Using a power mechanism to drive the cryopump to be tested;

[0028] Using a sealing mechanism to establish an end face seal of the cryopump to be tested;

[0029] The output power of the power mechanism is adjusted by using the adjustment mechanism to regulate the end face seal of the cryopump to be tested.

[0030] In the above technical solution, a power mechanism, an adjusting mechanism and a sealing mechanism are provided, wherein the power mechanism is used to drive the cryopump to be tested; the adjusting mechanism is used to adjust the output power of the power mechanism; the sealing mechanism is used to establish the end face seal of the cryopump to be tested; and the independent adjustment of the turbine pump speed, the sealing chamber pressure and the flow rate can be realized to meet the test of the turbine pump end face seal under different working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 A schematic diagram of the structure of a test system for a turbine pump end face seal provided in an embodiment of the present application;

[0032] Figure 2 A flowchart of a test system for a turbine pump end face seal provided in an embodiment of the present application.

[0033] Among them, 1-turbine disk; 2-exhaust pipe; 3-cryogenic pump; 4-pressure reducing valve; 5-solenoid valve; 6-first orifice plate; 7-second orifice plate; 8-third orifice plate; 9-fourth orifice plate. DETAILED DESCRIPTION

[0034] The present application is further described in detail below through the accompanying drawings and embodiments. Through these descriptions, the characteristics and advantages of the present application will become clearer and more specific.

[0035] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. Although various aspects of the embodiments are shown in the drawings, the drawings are not necessarily drawn to scale unless otherwise noted.

[0036] In addition, the technical features involved in different embodiments of the present application described below can be combined with each other as long as they do not conflict with each other.

[0037] To facilitate understanding of the test system and method for the end face seal of the turbopump provided in the embodiment of the present application, its application scenario is first explained. The test system and method for the end face seal of the turbopump provided in the embodiment of the present application are used to solve the problems of high complexity and cost in the prior art. A cryogenic liquid rocket engine is a rocket engine that uses a low-boiling point liquid as a propellant, which has the advantages of high performance, high safety, and good environmental protection. The oxidizer generally uses liquid oxygen, and the fuel generally uses liquid hydrogen or liquid methane. In recent years, with the development of materials, insulation, 3D printing and other technologies, as well as the increase in demand for rocket recovery, satellite networking, manned spaceflight, and deep space exploration, cryogenic liquid rocket engines have become a hot research direction. As the "heart" of a cryogenic liquid rocket engine, the turbopump is a key link in the development of a cryogenic liquid rocket engine. Due to the characteristics of a low boiling point, cryogenic propellants are very easy to vaporize and leak, and have high requirements for sealing. Therefore, the end face seal research of a cryogenic liquid rocket engine turbopump has become an urgent need for engine development. There is a test method for the end seal of the turbine pump of a hydrogen-oxygen rocket engine. The test system is complex and costly, which is suitable for batch testing. For the cryogenic liquid engine in the development stage, the high complexity and cost are not conducive to the development work. For this reason, the embodiment of the present application provides a test system and method for the end seal of a turbine pump to solve the problem of high complexity and cost in the prior art. The following is a detailed description of the embodiment in conjunction with the specific drawings.

[0038] refer to Figure 1 and Figure 2 , Figure 1 A schematic diagram of the structure of a test system for a turbine pump end face seal provided in an embodiment of the present application; Figure 2 A flowchart of a test system for a turbine pump end face seal provided in an embodiment of the present application.

[0039] exist Figure 1 In the embodiment of the present application, a test system for the end face seal of a turbine pump is provided, comprising: a power mechanism, an adjustment mechanism and a sealing mechanism, wherein:

[0040] The power mechanism is used to drive the cryopump 3 to be tested;

[0041] The regulating mechanism is used to regulate the output power of the power mechanism;

[0042] The sealing mechanism is used to establish the end face seal of the cryopump to be tested.

[0043] In the above technical solution, a power mechanism, an adjusting mechanism and a sealing mechanism are provided, wherein the power mechanism is used to drive the cryopump to be tested; the adjusting mechanism is used to adjust the output power of the power mechanism; the sealing mechanism is used to establish the end face seal of the cryopump to be tested; and the independent adjustment of the turbine pump speed, the sealing chamber pressure and the flow rate can be realized to meet the test of the turbine pump end face seal under different working conditions.

[0044] In a specific implementation scheme, the power mechanism includes an exhaust pipe 2 and a turbine disk 1 arranged in the exhaust pipe, wherein:

[0045] The turbine disk is connected to the power shaft of the cryopump to be tested, and is used to drive the cryopump to be tested.

[0046] In a specific implementation scheme, the regulating mechanism includes a solenoid valve 5 and a first regulating unit, wherein:

[0047] The electromagnetic valve, the first regulating unit and the air inlet of the turbine disc are connected through a pipeline, and the electromagnetic valve is communicated with the swirling air inlet. The first regulating unit is a first orifice plate 6.

[0048] In a specific implementation scheme, the regulating mechanism further includes a pressure reducing valve 4, wherein:

[0049] The pressure reducing valve is connected to the solenoid valve and the swirling gas inlet.

[0050] In a specific embodiment, the sealing mechanism includes a second adjustment unit, wherein:

[0051] One end of the second regulating unit is connected to the pump outlet of the cryopump to be tested through a pipeline, and the other end is connected to the sealed cavity inlet of the cryopump to be tested through a pipeline. The second regulating unit is a second orifice plate 7 .

[0052] In a specific embodiment, a third regulating unit is further included, wherein:

[0053] One end of the third regulating unit is connected to the sealed cavity inlet of the cryopump to be tested, and the other end is connected to the pump outlet. The third regulating unit is a third orifice plate 8 .

[0054] In a specific embodiment, a fourth regulating unit is further included, wherein:

[0055] One end of the fourth regulating unit is connected to the sealing outlet of the cryopump to be tested, and the other end is connected to the pump outlet and the outlet of the third regulating unit. The fourth regulating unit is a fourth orifice plate 9 .

[0056] In a specific embodiment, the pressure reducing valve is a membrane pressure reducing valve or an adjustable pressure reducing valve.

[0057] In a specific implementation manner, the second regulating unit, the third regulating unit and the fourth regulating unit are cavitation venturis or orifice plates.

[0058] Specifically, the test system for the turbine pump end face seal includes a complete set of test systems such as turbine pumps, valves, pipelines, and regulating elements. After the swirling gas passes through the pressure reducing valve, solenoid valve, and orifice plate, it reaches the turbine inlet with a certain pressure and flow rate, drives the turbine disk to rotate, and the turbine disk drives the pump shaft to rotate, realizing the pressure buildup after the cryogenic pump. After the propellant after the pump is pressure-regulated by the orifice plate, part of it flows into the sealing chamber. The cryogenic propellant with a certain pressure and flow rate in the sealing chamber ensures the reliable function of the pump end face seal.

[0059] In order to prevent air from being trapped in the liquid flow path, causing pump cavitation and abnormal pressure buildup in the sealed chamber, the pump chamber, sealed chamber and corresponding pipelines of the cryogenic pump need to be precooled before the swirling gas supply is started. The cryogenic propellant is introduced from the pump inlet, and after passing through the pump chamber and the second orifice plate of the cryogenic pump, it is divided into two paths. One path passes through the third orifice plate and is discharged from the pump outlet, and the other path passes through the sealed chamber and the fourth orifice plate and is discharged from the pump outlet. During the precooling process, the temperature of the cryogenic propellant is monitored. If the propellant temperature is stable and there is no air trapped, the precooling is completed.

[0060] A pressure reducing valve is set on the swirling air supply pipeline, and the outlet pressure of the pressure reducing valve is stable, which can ensure the stability of the air supply pressure. A solenoid valve + orifice plate is set after the pressure reducing valve. By setting the orifice plate aperture, inlet pressure, flow coefficient and other parameters, the speed of the turbine pump can be adjusted to adapt to the test of the end face seal of the turbine pump under different speed conditions.

[0061] A plurality of orifice plates (second orifice plate, third orifice plate and fourth orifice plate) are arranged in the pipeline after the pump. By setting the orifice plate parameters, the sealing chamber pressure, flow rate and other parameters can be adjusted to adapt to the end face sealing test under different sealing chamber pressures and flow rates.

[0062] In the above technical solution, by setting the parameters of valves, orifice plates in the swirling air supply line and the pipeline after the pump, the independent adjustment of the turbine pump speed, sealing chamber pressure and flow rate can be achieved, which can meet the test of the turbine pump end face seal under different working conditions (turbine pump speed, pump back pressure, sealing chamber pressure and flow rate). It is suitable for the end face seal test of cryogenic turbine pumps with different structural forms and different working points, and even some normal temperature turbine pumps.

[0063] exist Figure 2 In the embodiment of the present application, a test method for a turbine pump end face seal is provided, comprising the following steps:

[0064] Precool the cryopump to be tested;

[0065] Using a power mechanism to drive the cryopump to be tested;

[0066] Using a sealing mechanism to establish an end face seal of the cryopump to be tested;

[0067] The output power of the power mechanism is adjusted by using the adjustment mechanism to regulate the end face seal of the cryopump to be tested.

[0068] In the above technical solution, a power mechanism, an adjusting mechanism and a sealing mechanism are provided, wherein the power mechanism is used to drive the cryopump to be tested; the adjusting mechanism is used to adjust the output power of the power mechanism; the sealing mechanism is used to establish the end face seal of the cryopump to be tested; and the independent adjustment of the turbine pump speed, the sealing chamber pressure and the flow rate can be realized to meet the test of the turbine pump end face seal under different working conditions.

[0069] Specifically, the test method for the turbine pump end face seal comprises the following steps:

[0070] The cryogenic propellant is introduced into the pump inlet to fully pre-cool the pump chamber, sealing chamber and pipeline after the cryogenic pump;

[0071] The swirling gas passes through the pressure reducing valve, the solenoid valve and the first orifice plate, driving the turbine disk to rotate, and then driving the cryogenic pump shaft to rotate, so that the pressure behind the pump and the sealing chamber is built up, and the end face of the cryogenic pump is sealed;

[0072] A plurality of orifice plates (second orifice plate, third orifice plate, fourth orifice plate) are arranged in the pipeline after the pump. By adjusting the orifice plate parameters, the flow and pressure of the sealing chamber and the discharge chamber of the cryogenic pump are controlled, thereby ensuring the reliable sealing of the end face of the cryogenic pump;

[0073] The swirling gas supply pipeline is provided with a pressure reducing valve, a solenoid valve and an orifice plate 1, which ensures the stability of the swirling gas supply flow and pressure and ensures that the speed of the turbine pump is stably controlled.

[0074] Wherein, the cryogenic propellant is selected from at least one of the following: liquid oxygen, methane or other cryogenic liquid propellants.

[0075] The swirling gas supply source can be a gas cylinder, and the gas medium is nitrogen or helium.

[0076] A pressure reducing valve is provided on the gas supply pipeline to ensure the stability of the gas supply pressure. The pressure reducing valve is a diaphragm type pressure reducing valve or an adjustable pressure reducing valve.

[0077] The solenoid valve + first orifice plate is used to control the flow and pressure of the swirling air supply path, and can be a switch type solenoid valve + orifice plate or a regulating type solenoid valve, a manual valve.

[0078] The turbine disk has a certain flow-guiding structure to ensure that the swirling gas can effectively do work and drive the turbine disk to rotate.

[0079] The second orifice plate, the third orifice plate and the fourth orifice plate are all liquid regulating elements, and may be cavitation venturis or orifice plates.

[0080] The cryogenic pump comprises a pump chamber, a sealing chamber and a discharge chamber.

[0081] Before supplying the swirling gas, the pump chamber, sealing chamber and pipeline after the cryogenic pump are required to be fully pre-cooled to prevent air from being trapped in the liquid flow path, causing pump cavitation and abnormal pressure buildup in the sealing chamber.

[0082] A portion of the cryogenic liquid propellant is drawn out from the rear of the pump and flows into the cryogenic pump sealing cavity to achieve end face sealing of the cryogenic pump.

[0083] The swirling gas drives the turbine disk and the pump shaft to rotate, and the pressure is built up behind the pump. The cryogenic liquid propellant in the sealed chamber establishes a certain pressure flow, ensuring the reliable function of the cryogenic pump end face seal.

[0084] Furthermore, the turbine pump end face seal test system includes a turbine disc, an exhaust pipe, a cryogenic pump (composed of a pump chamber, a sealing chamber, and a discharge chamber), a pressure reducing valve, a solenoid valve, an orifice plate, and a pipeline. The swirling gas is decompressed by the pressure reducing valve, and then drives the turbine disc to rotate after passing through the solenoid valve and the first orifice plate, and then drives the cryogenic pump impeller to rotate, pressurizing the liquid. Part of the propellant after the pump is discharged through the pump discharge pipeline, and the other part enters the sealing chamber to achieve the end face seal of the cryogenic pump.

[0085] Liquid cryogenic propellant is introduced into the pump inlet, and the cryogenic propellant is divided into two paths after passing through the pump cavity of the cryogenic pump 3 and the second orifice plate 7. One path is discharged from the pump outlet through the third orifice plate 8, and the other path is discharged from the pump outlet after passing through the sealing cavity and the fourth orifice plate 9. The cryogenic propellant precools the pump cavity, sealing cavity and corresponding pipelines of the cryogenic pump 3.

[0086] After precooling, the solenoid valve 5 is opened, and the swirling gas passes through the pressure reducing valve 4, the solenoid valve 5, and the first orifice plate 6 to drive the turbine disk 1 to rotate. The turbine disk 1 is connected to the pump shaft, driving the pump shaft to rotate. The swirling gas continuously works on the turbine disk 1, and the speed of the turbine disk 1 and the pump shaft gradually increases until the design speed is reached. The pump shaft speed increases, working on the liquid propellant in the cryopump 3, and the pressure after the pump increases. As the pressure after the pump increases, the sealing chamber gradually establishes a stable pressure and flow, realizing the end face sealing of the cryopump.

[0087] During the precooling and stable operation of the cryogenic pump, due to factors such as high propellant temperature, heat transfer inside and outside the pipeline, and low pressure in the sealed chamber, a small amount of cryogenic propellant will be vaporized, and the generated gaseous propellant will be discharged from the discharge port through the discharge chamber. After the swirling gas works on the turbine disk 1, the exhaust gas is discharged through the exhaust pipe 2.

[0088] Those skilled in the art will appreciate that the present application may be implemented as a system, method or computer program product.

[0089] Therefore, the present disclosure may be specifically implemented in the following forms, namely: it may be completely hardware, it may be completely software (including firmware, resident software, microcode, etc.), or it may be a combination of hardware and software, generally referred to herein as a "circuit", "module" or "system". In addition, in some embodiments, the present application may also be implemented in the form of a computer program product in one or more computer-readable media, and the computer-readable medium may contain computer-readable program code.

[0090] Any combination of one or more computer-readable media can be used. Computer-readable media can be computer-readable signal media or computer-readable storage media. Computer-readable storage media can be, for example, but not limited to, electrical, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices or devices, or any combination of the above. More specific examples (non-exhaustive list) of computer-readable storage media include: electrical connections with one or more wires, portable computer disks, hard disks, random access memories (RAM), read-only memories (ROM), erasable programmable read-only memories (EPROM or flash memory), optical fibers, portable compact disk read-only memories (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the above. In this document, computer-readable storage media can be any tangible medium containing or storing a program, which can be used by an instruction execution system, device or device or used in combination with it.

[0091] Although the embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and cannot be understood as limiting the present application. A person of ordinary skill in the art can change, modify, replace and modify the above embodiments within the scope of the present application. On this basis, a variety of replacements and improvements can be made to the present application, all of which fall within the scope of protection of the present application.

Claims

1. A test system for a turbine pump end face seal, characterized in that: include: Power mechanism, regulating mechanism and sealing mechanism, wherein: The power mechanism is used to drive the cryopump to be tested; The regulating mechanism is used to regulate the output power of the power mechanism; The sealing mechanism is used to establish the end face seal of the cryopump to be tested.

2. The test system for the turbine pump end face seal according to claim 1, characterized in that: The power mechanism includes an exhaust pipe and a turbine disk arranged in the exhaust pipe, wherein: The turbine disk is connected to the power shaft of the cryopump to be tested, and is used to drive the cryopump to be tested.

3. The test system for the turbine pump end face seal according to claim 2, characterized in that: The regulating mechanism includes a solenoid valve and a first regulating unit, wherein: The solenoid valve, the first regulating unit and the air inlet of the turbine disc are connected through a pipeline, and the solenoid valve is communicated with the swirling air inlet.

4. The test system for the turbine pump end face seal according to claim 3, characterized in that: The regulating mechanism also includes a pressure reducing valve, wherein: The pressure reducing valve is connected to the solenoid valve and the swirling gas inlet.

5. The test system for the turbine pump end face seal according to claim 4, characterized in that: The sealing mechanism comprises a second adjustment unit, wherein: One end of the second regulating unit is connected to the pump outlet of the cryopump to be tested through a pipeline, and the other end of the second regulating unit is connected to the sealed cavity inlet of the cryopump to be tested through a pipeline.

6. The test system for the turbine pump end face seal according to claim 5, characterized in that: Also includes a third adjustment unit, wherein, One end of the third regulating unit is connected to the sealed cavity inlet of the cryopump to be tested, and the other end is connected to the pump outlet.

7. The test system for the turbine pump end face seal according to claim 6, characterized in that: Also includes a fourth adjustment unit, wherein, One end of the fourth regulating unit is connected to the sealing outlet of the cryopump to be inspected, and the other end is connected to the pump outlet and the outlet of the third regulating unit.

8. The test system for the turbine pump end face seal according to claim 7, characterized in that: The pressure reducing valve is a film type pressure reducing valve or an adjustable pressure reducing valve.

9. The test system for the turbine pump end face seal according to claim 8, characterized in that: The second regulating unit, the third regulating unit and the fourth regulating unit are cavitation venturis or orifice plates.

10. A test method for a turbine pump end face seal, characterized in that: The following steps are involved: Precool the cryopump to be tested; Using a power mechanism to drive the cryopump to be tested; Using a sealing mechanism to establish an end face seal of the cryopump to be tested; The output power of the power mechanism is adjusted by using the adjustment mechanism to regulate the end face seal of the cryopump to be tested.

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