CN114607615A

CN114607615A - Liquid oxygen pre-pressing turbine pump and turbine pump

Info

Publication number: CN114607615A
Application number: CN202210144745.XA
Authority: CN
Inventors: 崔生磊; 刘磊; 王磊; 李永鹏; 张树强; 王琳; 张力豪; 李金鸽; 梁润孜
Original assignee: Landspace Technology Co Ltd
Current assignee: Landspace Technology Co Ltd
Priority date: 2022-02-17
Filing date: 2022-02-17
Publication date: 2022-06-10

Abstract

A liquid oxygen pre-pressurizing turbopump and a turbopump are provided, wherein the liquid oxygen pre-pressurizing turbopump is arranged at the upstream of a main pump in the turbopump. The liquid oxygen pre-pressing turbine pump comprises a turbine cover, a volute, a turbine disc, a pump impeller and a pre-pressing pump shaft; the turbine disc inner ring is installed at pre-compaction pump shaft one end, and the pump impeller inner ring is installed at the pre-compaction pump shaft other end, and all sets up in the spiral case. The volute is provided with an extension section facing the pre-pressing pump shaft, a turbine cavity is formed between one side of the extension section and the turbine disc, a pump impeller cavity is formed between the other side of the extension section and the pump impeller, the extension section of the volute and the pre-pressing pump shaft are arranged at intervals, and a labyrinth sealing ring installed on the pre-pressing pump shaft is arranged in the interval. The grate sealing ring is arranged in a non-contact way with the volute and is used for preventing generation of redundant substances and friction explosion. The liquid oxygen pre-pressing turbine pump can be placed in the liquid oxygen storage tank, so that liquid oxygen in the propellant storage tank can be fully and effectively utilized, and the propellant redundancy in the storage tank is reduced.

Description

Liquid oxygen pre-pressing turbine pump and turbine pump

Technical Field

The invention relates to the technical field of aerospace carrier rocket engines, in particular to a liquid oxygen pre-pressurizing turbine pump and a turbine pump.

Background

Space vehicles need to operate at high altitudes or in space, far from the ground, and the structural size and mass of the propellant supply system are severely limited. High thrust, high specific impulse, high performance liquid rocket engine systems are typically closed cycle. In the closed circulation system, the outlet pressure of the pump is very high, and the rotating speed of the turbopump is selected to be higher in order to reduce the structural size and the quality of the turbopump, so that the required inlet pressure of the pump is higher when the turbopump is prevented from cavitation, and the wall thickness and the quality of the storage tank can be directly influenced by the pressure rise of the storage tank.

Therefore, it is a problem to be solved to provide a liquid oxygen pre-compressed turbo pump capable of increasing the inlet pressure of the main pump.

Disclosure of Invention

In order to solve the technical problems in the related art, the invention provides a liquid oxygen pre-pressurizing turbopump and a turbopump, which are suitable for a pumping pressure type liquid rocket engine with high thrust and high specific impulse, have the advantages of simple structure, small number of parts, high reliability and the like, and reduce the production, manufacturing and assembly test cost of the liquid oxygen pre-pressurizing turbopump. The liquid oxygen pre-pressing turbine pump can be arranged in a rocket storage tank, so that liquid oxygen in the propellant storage tank is fully and effectively utilized, and the redundancy of the propellant in the storage tank is reduced. In addition, the liquid oxygen pre-pressurizing turbine pump optimizes the overall structural layout of a power system, and meanwhile, the high-efficiency and high-reliability work of the liquid oxygen pre-pressurizing turbine pump is guaranteed.

The invention provides a liquid oxygen pre-pressing turbine pump which is arranged at the upstream of a main pump in the turbine pump and comprises a turbine cover, a volute, a turbine disc, a pump impeller and a pre-pressing pump shaft. The turbine disc inner ring is installed at one end of the pre-pressing pump shaft, the pump impeller inner ring is installed at the other end of the pre-pressing pump shaft, and the pump impeller inner ring and the pre-pressing pump shaft are all arranged in the volute. A volute inlet pipe and a volute outlet pipe are arranged at the position, close to the pump impeller, of the volute, the volute inlet pipe is connected with the liquid oxygen storage tank, and the volute outlet pipe is connected with a main pump inlet pipeline; and a nozzle hole is formed in the position, close to the turbine disc, of the volute and is used for being connected with a main pump outlet. The volute has an extension towards the pre-pressure pump shaft; one side of the extension section of the volute and the turbine disc form a turbine cavity, the other side of the extension section of the volute and the pump impeller form a pump impeller cavity, the extension section of the volute and the pre-pressing pump shaft are arranged at intervals, and a labyrinth sealing ring installed on the pre-pressing pump shaft is arranged in the interval; the grate sealing ring is arranged in a non-contact way with the volute and is used for preventing generation of excess and friction explosion.

The turbine cover is arranged at one end, close to the turbine disc, of the volute, and meanwhile, the turbine cover and the turbine disc are matched to form an accommodating space, one side, far away from the pre-pressing pump shaft, of the turbine disc is provided with turbine blades, and the turbine blades are arranged in the space.

In one embodiment, a turbine end bearing is arranged in a space between the extension section of the volute and the pre-pressing pump shaft; the labyrinth sealing ring is axially attached and arranged between the pump impeller and the turbine end bearing.

In one embodiment, a first radial gap is formed between the outer ring of the turbine disc and the volute, a first axial gap communicated with the first radial gap is formed between the turbine disc and the extension section of the volute, a second radial gap is formed between the outer ring of the labyrinth seal ring and the extension section of the volute, and a second axial gap is formed between the extension section of the volute and the outer ring of the pump impeller. And high-pressure propellant entering from the nozzle hole flows into the volute sequentially through the first radial gap, the first axial gap, the gap between the inner ring and the outer ring of the turbine end bearing, the second radial gap and the second axial gap, and is used for cooling the turbine end bearing. The second axial gap can be adjusted by adjusting the axial thickness of the labyrinth sealing ring.

In one embodiment, a third axial clearance is formed between the turbine blade and the turbine cover, and a fourth axial clearance is formed between one side, close to the pre-pressing pump shaft, of the turbine disc and the turbine cover; and high-pressure propellant entering from the nozzle hole passes through the third axial gap and the fourth axial gap in sequence and is used for driving the turbine disc to rotate.

In one embodiment, the inner ring of the turbine end bearing is arranged on the pre-pressing pump shaft, and the outer ring is arranged at the position of a bearing hole of the volute; one side of the turbine end bearing, which is far away from the labyrinth sealing ring, is attached to the turbine disc through an adjusting pad.

In one embodiment, the first axial gap, the third axial gap and the fourth axial gap can be adjusted by adjusting an axial thickness of the adjustment pad.

In one embodiment, the pump impeller is locked on the pre-pressing pump shaft through a pump impeller locking plate and a pump impeller fixing nut. And a third radial gap is formed between the outer ring of the pump impeller and the inlet pipe of the volute, so that the outer ring of the pump impeller and the inlet pipe of the volute are prevented from rubbing by friction.

In one embodiment, one end of the pump impeller, which is far away from the turbine disc, is provided with a pump end bearing and a guide vane ring arranged on the outer ring of the pump end bearing; the pump end bearing inner ring is locked and fixed on the pre-pressing pump shaft through a pump end bearing fixing locking plate and a pump end bearing fixing nut, the outer ring passes through the guide vane locking plate and the guide vane gland nut is installed in the guide vane ring, and the guide vane ring outer ring is arranged in the volute.

In one embodiment, the first, third, fourth and first radial gaps are each 0.5mm to 3mm, the second axial gap is 0.5mm to 3mm, the third radial gap is 0.5mm to 2mm, the second radial gap is 0.3mm to 1 mm.

The invention also provides a turbopump, which comprises a main pump and a liquid oxygen pre-pressurizing turbopump arranged upstream of the main pump. The liquid oxygen pre-pressurizing turbine pump is arranged inside the liquid oxygen storage tank or at the outlet of the liquid oxygen storage tank. The hydraulic storage tank is connected with a volute inlet pipeline of the liquid-oxygen pre-pressurizing turbine pump, a main pump inlet pipeline is connected with a volute outlet pipeline of the liquid-oxygen pre-pressurizing turbine pump, and a main pump outlet pipeline is connected with a nozzle hole, close to the turbine disc, of the liquid-oxygen pre-pressurizing turbine pump.

According to the liquid oxygen pre-pressurizing turbopump and the turbopump provided by the embodiment of the invention, the main pump high-pressure liquid propellant is used for driving the turbine disc of the liquid oxygen pre-pressurizing turbopump to rotate, and a rocket is not required to carry other media to drive the turbine. The prepressing pump of the traditional high-pressure afterburning closed system adopts high-temperature oxygen-enriched gas to drive the turbine disc, the working environment of the turbine disc is more superior than that of the traditional high-pressure afterburning closed system, the turbine disc is not easy to generate ablation deformation and fatigue damage, the service life of a bearing is long, the operation is reliable, and the safe and reliable operation of the liquid oxygen prepressing turbine pump can be ensured.

According to the liquid oxygen pre-pressing turbine pump provided by the embodiment of the invention, the turbine cavity and the pump impeller cavity are sealed through the non-contact labyrinth sealing ring, so that friction explosion and excess are not easy to generate in a low-temperature liquid oxygen environment, and the liquid oxygen pre-pressing turbine pump can be ensured to work safely and reliably.

The bearing cooling loop of the embodiment of the invention is simple, and the high-pressure propellant in the turbine cavity flows through the bearing from the gap between the inner ring and the outer ring of the turbine end bearing, then passes through the second radial gap and the second axial gap of the labyrinth seal ring, and finally flows into the volute from the pump impeller cavity.

Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.

Fig. 1 is a schematic view of the overall structure of a liquid oxygen pre-compressed turbo pump according to the present invention.

Fig. 2 is a sectional view of the internal structure of the liquid oxygen pre-compressed turbo pump according to the embodiment of the present invention.

Fig. 3 is a schematic view of a connection structure of the liquid oxygen pre-compressed turbo pump according to the embodiment of the present invention.

Detailed Description

The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.

Referring to fig. 1, one aspect of the present invention is directed to a liquid oxygen pre-compressed turbo pump. The liquid oxygen pre-pressing turbine pump is arranged on the upstream of a main pump in the turbine pump and comprises a turbine cover 1, a volute 2, a turbine disc 3, a pump impeller 4 and a pre-pressing pump shaft 5. The liquid oxygen pre-pressing turbine pump is a coaxial liquid rocket engine turbine pump structure, a turbine disc 3 and a pump impeller 4 are coaxially arranged on a pre-pressing pump shaft 5, liquid is axially fed into the liquid oxygen pre-pressing turbine pump, liquid is tangentially discharged, and the turbine disc 3 is of an impact structure and is tangentially fed into the liquid and axially discharged. The inner ring of the turbine disc 3 is arranged at one end of the pre-pressing pump shaft 5, and the inner ring of the pump impeller 4 is arranged at the other end of the pre-pressing pump shaft 5 and is arranged in the volute 2. Wherein, the pump impeller 4 and the turbine disc 3 are respectively connected with the prepressing pump shaft 5 in a key connection mode.

Further, the liquid oxygen pre-pressurizing turbine pump can be installed inside the liquid oxygen storage tank or at the outlet of the liquid oxygen storage tank, and a volute inlet pipe 21 and a volute outlet pipe (not marked in the figure, and can be set at appropriate positions according to the operation requirements) are arranged at the position of the volute 2 close to the pump impeller 4. Wherein, the volute inlet pipe 21 is connected with the liquid oxygen storage tank, and the volute outlet pipe is connected with the main pump inlet pipeline. The volute 2 is also provided with a nozzle hole (not marked in the figure, and can be arranged at a proper position according to the operation requirement) at a position close to the turbine disc 3, and the nozzle hole is used for being connected with a main pump outlet. High-pressure liquid oxygen from the outlet of the main pump is introduced into the turbine cavity through the outlet of the main pump and a nozzle hole of the volute and is used for driving the turbine disc to rotate.

The volute 2 also has an extension towards the pre-pressure pump shaft. The extension of the volute 2 forms a turbine chamber 300 with the turbine disc 3 on one side and a pump impeller chamber 400 with the pump impeller 4 on the other side. And the extension section of the volute 2 and the pre-pressing pump shaft 5 are arranged at intervals, and a grate sealing ring 6 arranged on the pre-pressing pump shaft 5 is arranged in the interval. The grate sealing ring 6 is arranged in a non-contact way with the volute 2 and is used for preventing generation of excess and friction explosion and ensuring that the oxygen precompression pump can work safely and reliably.

Turbine cover 1 sets up in the one end that 6 volutes are close to turbine dish 3, forms accommodation space with the cooperation of turbine dish 3 simultaneously, and one side that pre-compaction pump shaft 5 was kept away from to turbine dish 3 has turbine blade 31, and turbine blade 31 sets up in this space, guarantees that turbine blade can the internal rotation in this space do work.

According to the liquid oxygen pre-pressing turbine pump provided by the embodiment of the invention, the high-pressure liquid propellant generated after the main pump applies work and is pressurized is used for driving the turbine disc to rotate, a rocket is not required to additionally carry other media to drive the turbine, and the liquid oxygen pre-pressing turbine pump can be arranged in the propellant storage tank, so that the liquid oxygen pre-pressing turbine pump is simple in structure, convenient to install and high in reliability.

The turbine cavity and the pump cavity of the liquid oxygen pre-pressurizing turbine pump are sealed through the non-contact labyrinth sealing ring, the liquid oxygen pre-pressurizing turbine pump is safer and more reliable than the traditional contact type end face sealing and floating ring sealing, is not easy to rub and explode in the face of a low-temperature liquid oxygen environment, is not easy to generate redundancy, and can ensure the safe and reliable work of the liquid oxygen pre-pressurizing turbine pump.

Referring to fig. 2, in one embodiment, a turbine end bearing 7 is also provided in the space between the extension of the volute 2 and the pre-pressure pump shaft 5. The labyrinth seal ring 6 is axially attached and installed between the pump impeller 4 and the turbine end bearing 7. The liquid oxygen pre-pressurizing turbo pump and the volute are matched to prevent the propellant in the turbine cavity 300 and the impeller cavity 400 from leaking mutually, so that the volumetric efficiency of the liquid oxygen pre-pressurizing turbo pump is improved.

Furthermore, considering the working environment, the labyrinth sealing ring can be made of stainless steel, and the cylindrical surface of the labyrinth is coated with pure silver, so that the pure silver layer is used as a friction layer, and the risk of metal collision and abrasion between the rotor (a turbine disc, a turbine end bearing and the like) and the stator (a pre-pressed pump shaft) can be prevented.

With continued reference to fig. 2, in the above embodiment, a first radial gap X1 is provided between the outer ring of the turbine disc 3 and the inner wall of the volute 2, a first axial gap X2 communicated with the first radial gap X1 is provided between the turbine disc 3 and the extension section of the volute 2, a second radial gap X3 is provided between the outer ring of the labyrinth seal ring 6 and the extension section of the volute 2, and a second axial gap X4 is provided between the extension section of the volute 2 and the outer ring of the pump impeller 4. The high-pressure propellant entering from the nozzle hole flows into the volute 2 through the first radial gap X1, the first axial gap X2, the gap between the inner ring and the outer ring of the turbine end bearing 7, the second radial gap X3 and the second axial gap X4 in sequence, and is used for cooling the turbine end bearing 7. The second axial gap X4 can be adjusted by adjusting the axial thickness of the labyrinth seal ring 6.

The bearing cooling loop is simple, and the high-pressure propellant in the turbine cavity flows through the bearing from the gap between the inner ring and the outer ring of the turbine end bearing, then passes through the second radial gap and the second axial gap of the labyrinth seal ring, and finally flows into the volute from the pump impeller cavity.

Further, a third axial clearance X5 is provided between the turbine blade 31 and the turbine cover 1, and a fourth axial clearance X6 is provided between the side of the turbine disc 3 close to the pre-pressure pump shaft 5 and the turbine cover 1. High-pressure propellant from the outlet of the main pump enters the volute 2 through the nozzle hole, passes through the third axial gap X5 and the fourth axial gap X6 in sequence, and is used for driving the turbine disc 3 to rotate.

Referring to fig. 2 and 3, in the above embodiment, the inner ring of the turbine end bearing 7 is disposed on the pre-pressure pump shaft 5, and the outer ring is mounted at the position of the bearing hole of the volute 2 and fixed by the bearing pressing locking piece 71 and the bearing pressing nut 72. One side of the turbine end bearing 7, which is far away from the labyrinth sealing ring 6, is attached to the turbine disc 3 through an adjusting pad 8. The turbine disc 3, the adjusting pad 8, the turbine end bearing 7, the comb tooth sealing ring 6 and the pump impeller 4 are sequentially and axially attached to the pre-pressing pump shaft 5.

In one embodiment, the first axial gap X2, the third axial gap X5, and the fourth axial gap X6 can be adjusted by adjusting the axial thickness of the adjustment pad 8, so that each of the above-described gaps can be adjusted to the most appropriate value.

In one embodiment, the first axial gap X2, the third axial gap X5, the fourth axial gap X6, and the first radial gap X1 are each 0.5mm to 3mm, the second axial gap X4 is 0.5mm to 3mm, and the second radial gap X3 is 0.3mm to 1 mm. Specifically, the liquid oxygen pre-compressed turbo pump according to the embodiment of the present invention may select an optimum interval for each gap for the purpose of eliminating the cavitation phenomenon of the engine.

Referring to fig. 2 and fig. 3, in one embodiment, the pump impeller 4 is locked to the pre-pressing pump shaft 5 by a pump impeller locking plate 41 and a pump impeller fixing nut 42, and transmits torque by 1 or 2 flat keys. And a third radial gap X7 is formed between the outer ring of the pump impeller 4 and the volute inlet pipe 21, and the third radial gap X7 is 0.5 mm-2 mm, so that the outer ring of the pump impeller and the volute inlet pipe are prevented from being rubbed and scratched.

Further, the end of the pump impeller 4 away from the turbine disk 3 has a pump end bearing 9 and a vane guide ring 43 provided on the outer ring of the pump end bearing 9. The inner ring of the pump end bearing 9 is locked and fixed on the pre-pressing pump shaft 5 through a pump end bearing fixing locking sheet 91 and a pump end bearing fixing nut 92, the outer ring is installed in the guide vane ring 43 through a guide vane locking sheet 431 and a guide vane compression nut 432, the outer ring of the guide vane ring 43 is arranged in the volute 2, and the axial direction of the guide vane ring has no limit requirement.

In the above embodiment, the number of the vanes of the vane ring is 3 to 6.

The pump impeller is replaced by a centrifugal pump with an inducer, the scheme of the invention can still be used, and the sizes and the shells of the inducer, the centrifugal wheel and the volute are designed according to requirements, or part of the internal structure is adjusted according to conventional requirements.

The liquid oxygen pre-pressurizing turbine pump is simple in structure, few in part number and light in weight, can be installed in the propellant storage tank, and reduces the production, manufacturing and assembly test cost of the liquid oxygen pre-pressurizing turbine pump.

According to the liquid oxygen pre-pressing turbine pump, the turbine cavity and the pump impeller cavity are sealed through the non-contact labyrinth sealing ring, the low-temperature liquid oxygen environment is faced, friction and explosion are not prone to occurring, excess materials are not prone to generating, and the liquid oxygen pre-pressing turbine pump can be guaranteed to work safely and reliably.

The above embodiments may be combined with each other with corresponding technical effects.

The invention also provides a turbopump, which comprises a main pump and a liquid oxygen pre-pressurizing turbopump arranged upstream of the main pump. The liquid oxygen pre-pressurizing turbine pump is arranged inside the liquid oxygen storage tank or at the outlet of the liquid oxygen storage tank. The hydraulic storage tank is connected with a volute inlet pipeline of the liquid oxygen pre-pressurizing turbine pump, a main pump inlet pipeline is connected with a volute outlet pipeline of the liquid oxygen pre-pressurizing turbine pump, and a main pump outlet pipeline is connected with a nozzle hole, close to a turbine disc, of the liquid oxygen pre-pressurizing turbine pump.

According to the turbo pump provided by the embodiment of the invention, the propellant for driving the turbine disc in the liquid oxygen pre-pressurizing turbo pump to rotate comes from the high-pressure liquid oxygen at the outlet of the main pump, and is introduced into the turbine cavity through the outlet of the main pump and the nozzle hole reserved in the volute to drive the turbine disc to rotate. The volute outlet is connected with the main pump inlet pipeline, and the volute inlet is connected with the liquid oxygen storage tank, so that the oxygen pre-pressing turbine pump can be installed inside the liquid oxygen storage tank or at the outlet of the liquid oxygen storage tank, liquid oxygen in the storage tank can be fully and effectively utilized, and propellant redundancy in the storage tank is reduced.

The turbine pump of the invention increases the inlet pressure of the main pump by separately installing a pre-pressing turbine pump at the upstream of the main pump. The precompression turbopump not only can improve the rotational speed of main pump to can alleviate the structure quality of storage tank quality and turbopump by a wide margin, can also improve the efficiency of turbopump, thereby improve the payload quality of carrier rocket.

According to the liquid oxygen pre-pressurizing turbo pump and the turbo pump, the main pump high-pressure liquid propellant is used for driving the turbine disc of the liquid oxygen pre-pressurizing turbo pump to rotate, and a rocket is not required to carry other media to drive the turbine. The prepressing pump of the traditional high-pressure afterburning closed system adopts high-temperature oxygen-enriched gas to drive the turbine disc, the working environment of the turbine disc is more superior than that of the traditional high-pressure afterburning closed system, the turbine disc is not easy to generate ablation deformation and fatigue damage, the service life of a bearing is long, the operation is reliable, and the safe and reliable operation of the liquid oxygen prepressing turbine pump can be ensured.

The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.

Claims

1. The utility model provides a liquid oxygen pre-compaction turbopump, installs the main pump upstream in the turbopump, its characterized in that includes: the turbine cover, the volute, the turbine disc, the pump impeller and the prepressing pump shaft are arranged on the turbine disc; the turbine disc inner ring is arranged at one end of the prepressing pump shaft, and the pump impeller inner rings are arranged at the other end of the prepressing pump shaft and are all arranged in the volute;

a volute inlet pipe and a volute outlet pipe are arranged at the position, close to the pump impeller, of the volute, the volute inlet pipe is connected with the liquid oxygen storage tank, and the volute outlet pipe is connected with a main pump inlet pipeline; a nozzle hole is formed in the position, close to the turbine disc, of the volute and used for being connected with an outlet of a main pump;

the volute has an extension towards the pre-pressure pump shaft; one side of the extension section of the volute and the turbine disc form a turbine cavity, the other side of the extension section of the volute and the pump impeller form a pump impeller cavity, the extension section of the volute and the pre-pressing pump shaft are arranged at intervals, and a labyrinth sealing ring installed on the pre-pressing pump shaft is arranged in the interval; the grate sealing ring is arranged in a non-contact way with the volute and is used for preventing generation of excess and friction explosion;

2. The liquid oxygen pre-compressed turbo pump according to claim 1, wherein a turbine end bearing is further provided in a space between the extension section of the volute and the pre-compressed pump shaft; the labyrinth sealing ring is axially attached and arranged between the pump impeller and the turbine end bearing.

3. The liquid oxygen pre-pressing turbo pump according to claim 2, wherein a first radial gap is formed between the outer ring of the turbine disc and the volute, a first axial gap communicated with the first radial gap is formed between the turbine disc and the extension section of the volute, a second radial gap is formed between the outer ring of the labyrinth seal ring and the extension section of the volute, and a second axial gap is formed between the extension section of the volute and the outer ring of the pump impeller;

high-pressure propellant entering from the nozzle hole flows into the volute through the first radial gap, the first axial gap, the gap between the inner ring and the outer ring of the turbine end bearing, the second radial gap and the second axial gap in sequence, and is used for cooling the turbine end bearing;

the second axial gap can be adjusted by adjusting the axial thickness of the labyrinth sealing ring.

4. The liquid oxygen pre-compressed turbine pump according to claim 3, wherein a third axial clearance is provided between the turbine blades and the turbine cover, and a fourth axial clearance is provided between a side of the turbine disc close to the pre-compressed pump shaft and the turbine cover;

and high-pressure propellant entering from the nozzle hole passes through the third axial gap and the fourth axial gap in sequence and is used for driving the turbine disc to rotate.

5. The liquid oxygen pre-compressed turbo pump according to claim 4, wherein an inner ring of the turbine end bearing is arranged on the pre-compressed pump shaft, and an outer ring is arranged at a bearing hole of the volute; one side of the turbine end bearing, which is far away from the labyrinth sealing ring, is attached to the turbine disc through an adjusting pad.

6. The liquid oxygen pre-compressed turbo pump of claim 5, wherein the first axial gap, the third axial gap, and the fourth axial gap are adjustable by adjusting an axial thickness of the adjustment pad.

7. The liquid oxygen pre-pressing turbo pump according to any one of claims 1 to 6, wherein the pump impeller is locked to the pre-pressing pump shaft by a pump impeller locking plate and a pump impeller fixing nut;

and a third radial gap is formed between the outer ring of the pump impeller and the inlet pipe of the volute, so that the outer ring of the pump impeller and the inlet pipe of the volute are prevented from rubbing by friction.

8. The liquid oxygen pre-pressing turbine pump as claimed in claim 7, wherein one end of the pump impeller, which is far away from the turbine disc, is provided with a pump end bearing and a guide vane ring arranged on an outer ring of the pump end bearing; the pump end bearing inner ring is locked and fixed on the pre-pressing pump shaft through a pump end bearing fixing locking plate and a pump end bearing fixing nut, the outer ring is installed in the guide vane ring through a guide vane locking plate and a guide vane compression nut, and the guide vane ring outer ring is arranged in the volute.

9. The liquid oxygen pre-stressed turbine pump of claim 7, wherein the first axial gap, the third axial gap, the fourth axial gap, and the first radial gap are each 0.5mm to 3mm, the second axial gap is 0.5mm to 3mm, the third radial gap is 0.5mm to 2mm, and the second radial gap is 0.3mm to 1 mm.

10. The turbopump is characterized by comprising a main pump and a liquid oxygen pre-pressurizing turbopump arranged at the upstream of the main pump; the liquid oxygen pre-pressing turbine pump is arranged in the liquid oxygen storage tank or at the outlet of the liquid oxygen storage tank; the hydraulic storage tank is connected with a volute inlet pipeline of the liquid-oxygen pre-pressurizing turbine pump, a main pump inlet pipeline is connected with a volute outlet pipeline of the liquid-oxygen pre-pressurizing turbine pump, and a main pump outlet pipeline is connected with a nozzle hole, close to the turbine disc, of the liquid-oxygen pre-pressurizing turbine pump.