CN218293881U - Liquid oxygen pre-compaction turbopump and turbopump - Google Patents
Liquid oxygen pre-compaction turbopump and turbopump Download PDFInfo
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- CN218293881U CN218293881U CN202220318299.5U CN202220318299U CN218293881U CN 218293881 U CN218293881 U CN 218293881U CN 202220318299 U CN202220318299 U CN 202220318299U CN 218293881 U CN218293881 U CN 218293881U
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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 by one side of the extension section and the turbine disc, a pump impeller cavity is formed by 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 arranged 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
Technical Field
The utility model relates to a space launch vehicle engine technical field especially relates to a liquid oxygen pre-compaction turbopump and turbopump.
Background
Space vehicles need to operate in high altitude or in space, far from the ground, and the structural dimensions and mass of the propellant supply system are therefore 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 an object of the present invention to provide a liquid oxygen pre-compressed turbo pump capable of increasing the inlet pressure of the main pump.
SUMMERY OF THE UTILITY MODEL
For solving the above-mentioned technical problem among the correlation technique, the utility model provides a liquid oxygen pre-compaction turbopump and turbopump is applicable to the pumping pressure formula liquid rocket engine of high thrust, high specific impulse, has advantages such as the structure is retrencied, spare part is small in quantity and reliability height, has reduced the manufacturing and assembly test cost of liquid oxygen pre-compaction 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 structure layout of a power system, and meanwhile, the high-efficiency and high-reliability work of the liquid oxygen pre-pressurizing turbine pump is also guaranteed.
The utility model discloses an aspect provides a liquid oxygen pre-compaction turbopump installs the main pump upper reaches in the turbopump, including turbine cover, spiral case, turbine dish, pump impeller and pre-compaction 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 is provided with an extension section facing the pre-pressing 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 gap is formed between the turbine blade and the turbine cover, and a fourth axial gap is formed between one side of the turbine disc close to the pre-pressing 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.
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 pump impeller outer ring and the volute inlet pipe, so that the pump impeller outer ring and the volute inlet pipe are prevented from being rubbed and rubbed.
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 1mm.
The utility model discloses an on the other hand still provides a turbopump, including the main pump with set up in the liquid oxygen pre-compaction turbopump at main pump upper reaches. 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.
The utility model discloses liquid oxygen pre-compaction turbopump and turbopump utilizes the turbine dish of main pump high pressure liquid propellant drive liquid oxygen pre-compaction turbopump rotatory, does not need the rocket to carry other medium drive turbines in addition. The precompression pump of traditional high pressure afterburning closed system adopts high temperature oxygen boosting gas drive turbine dish, the utility model discloses a turbine dish operational environment is more superior than the environment of traditional high pressure afterburning closed system, and ablation deformation and fatigue failure are difficult to appear in the turbine dish, and bearing long service life, reliable operation can guarantee the safe and reliable work of liquid oxygen precompression turbine pump.
The utility model discloses liquid oxygen pre-compaction turbopump, sealed through the labyrinth sealing ring of non-contact between turbine chamber and the pump impeller chamber, in low temperature liquid oxygen environment, the explosion of being difficult for rubbing is difficult for producing the surplus thing, can guarantee liquid oxygen pre-compaction turbopump safe and reliable work.
The utility model discloses bearing cooling circuit is simple, and the high-pressure propellant in turbine chamber flows through the bearing from the clearance of turbine end bearing inner and outer lane, then through the radial clearance of second and the second axial clearance of labyrinth sealing ring, flows into the spiral case from the pump impeller chamber at last.
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 to be used in the embodiments 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 an overall structure schematic diagram of the liquid oxygen pre-pressurizing turbine pump of 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 a liquid oxygen pre-compressed turbo pump according to an embodiment of the present invention.
Detailed Description
The technical solution of the present invention is further explained by the following embodiments with reference to the accompanying drawings. Spatial relationship terms such as "below," "at \8230," "lower," "above," "at \8230," "upper," "higher," and the like are used for convenience in description to explain the positioning of one element relative to a second element, indicating that the terms are intended to encompass different orientations of the device in addition to orientations different from those shown 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, an aspect of the present invention provides 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 utility model discloses a liquid oxygen pre-compaction turbopump is a coaxial-type liquid rocket engine turbopump structure, turbine dish 3 and pump impeller 4 coaxial set up in pre-compaction pump shaft 5, liquid oxygen pre-compaction turbopump axial feed liquor, tangential flowing back, turbine dish 3 adopt impacted style structure, tangential feed liquor, axial flowing back. 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 disk 3 are respectively connected with the prepressing pump shaft 5 in a key connection mode.
Further, the liquid oxygen pre-pressurizing turbo pump may 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, may be set at appropriate positions according to the operation requirements) are provided at a 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) close to the turbine disc 3, and the nozzle hole is used for being connected with the outlet of the main pump. 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.
The utility model discloses liquid oxygen pre-compaction turbopump, the high-pressure liquid propellant drive turbine dish that utilizes the main pump to produce after the acting pressure boost is rotatory, does not need the rocket to carry other media in addition and drives the turbine, and liquid oxygen pre-compaction turbopump can install in the propellant storage tank, and the structure is retrencied, simple to operate, and the reliability is high.
The utility model discloses sealed through the labyrinth sealing ring of non-contact between the turbine chamber of liquid oxygen pre-compaction turbopump and the pump chamber, than traditional contact end face seal and the sealed safe and reliable more of floating ring, in the face of low temperature liquid oxygen environment, the difficult friction explosion is difficult for producing the surplus thing, can guarantee liquid oxygen pre-compaction turbopump safe and reliable work.
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 utility model discloses liquid oxygen pre-compaction turbopump and spiral case cooperation block the mutual leakage of propellant in turbine chamber 300 and the pump impeller chamber 400 to improve the volumetric efficiency of liquid oxygen pre-compaction turbopump.
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 sequentially 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, 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 utility model discloses a bearing cooling circuit is simple, and the high-pressure propellant in turbine chamber flows through the bearing from the clearance of turbine end bearing inner and outer lane, then through the radial clearance of second and the second axial clearance of labyrinth sealing ring, flows into the spiral case from the pump impeller chamber at last.
Further, a third axial gap X5 is provided between the turbine blade 31 and the turbine cover 1, and a fourth axial gap X6 is provided between the turbine disc 3 and the turbine cover 1 on the side close to the pre-pressing pump shaft 5. High-pressure propellant from the outlet of the main pump enters the volute 2 through the nozzle hole, and passes through the third axial gap X5 and the fourth axial gap X6 in sequence to drive 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 prepressing 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 an optimal 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 1mm. Specifically, the utility model discloses liquid oxygen pre-compaction turbopump can use the engine cavitation phenomenon of elimination as the purpose, selects the optimum interval in each clearance.
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. 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, one 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 an 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 plate 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 plate 431 and a guide vane gland 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 does not have a limit requirement.
In the above embodiment, the number of the vanes of the vane ring is 3 to 6.
With the centrifugal pump of above-mentioned pump impeller change for taking the inducer, the utility model discloses a scheme is still available, only needs size and the shell of inducer, centrifugal wheel and spiral case of design as required, or according to conventional demand adjustment part inner structure can.
The utility model discloses a liquid oxygen pre-compaction turbopump simple structure, part is small in quantity, and the quality is light, and can install in the propellant storage tank, has reduced the manufacturing and assembly test cost of liquid oxygen pre-compaction turbopump.
The utility model discloses a liquid oxygen pre-compaction turbopump, sealed through the labyrinth sealing ring of non-contact between turbine chamber and the pump impeller chamber, in the face of low temperature liquid oxygen environment, the difficult friction explosion is difficult for producing the surplus thing, can guarantee liquid oxygen pre-compaction turbopump safe and reliable work.
The above embodiments may be combined with each other with corresponding technical effects.
The utility model discloses an on the other hand still provides a turbopump, include the main pump and set up in the liquid oxygen pre-compaction turbopump in the main pump upper reaches. 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 formed in the liquid oxygen pre-pressurizing turbine pump and close to the turbine disc.
The utility model discloses turbo pump, the rotatory propellant of vortex wheel comes from the high-pressure liquid oxygen of main pump export in the drive liquid oxygen pre-compaction turbo pump, draws through the main pump export and introduces the turbine chamber with the nozzle bore that the spiral case left and drive the turbine dish rotation. 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 utility model discloses a turbopump is through installing a pre-compaction turbopump alone at the main pump upper reaches to improve the inlet pressure of 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.
The utility model discloses a liquid oxygen pre-compaction turbopump and turbopump, the turbine dish that utilizes main pump high pressure liquid propellant drive liquid oxygen pre-compaction turbopump is rotatory, does not need the rocket to carry other media in addition and drives the turbine. The precompression pump of traditional high pressure afterburning closed system adopts high temperature oxygen boosting gas drive turbine dish, the utility model discloses a turbine dish operational environment is more superior than the environment of traditional high pressure afterburning closed system, and ablation deformation and fatigue failure are difficult to appear in the turbine dish, and bearing long service life, reliable operation can guarantee the safe and reliable work of liquid oxygen precompression turbine pump.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
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 is 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;
the turbine cover is arranged at one end, close to the turbine disc, of the volute, and meanwhile, an accommodating space is formed by matching the turbine disc, 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.
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-pressurizing 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 extension section of the volute and the turbine disc, a second radial gap is formed between the outer ring of the labyrinth sealing 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 sequentially through the first radial gap, the first axial gap, gaps of the inner ring and the outer ring of the turbine end bearing, a second radial gap and a second axial gap to realize cooling of 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 blade 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 6, 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, and the second radial gap is 0.3mm to 1mm.
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220318299.5U CN218293881U (en) | 2022-02-17 | 2022-02-17 | Liquid oxygen pre-compaction turbopump and turbopump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220318299.5U CN218293881U (en) | 2022-02-17 | 2022-02-17 | Liquid oxygen pre-compaction turbopump and turbopump |
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|---|---|
| CN218293881U true CN218293881U (en) | 2023-01-13 |
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|---|---|---|---|
| CN202220318299.5U Active CN218293881U (en) | 2022-02-17 | 2022-02-17 | Liquid oxygen pre-compaction turbopump and turbopump |
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| CN (1) | CN218293881U (en) |
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- 2022-02-17 CN CN202220318299.5U patent/CN218293881U/en active Active
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