CN116576158A - Bearing cooling structure for turbine pump and turbine pump - Google Patents
Bearing cooling structure for turbine pump and turbine pump Download PDFInfo
- Publication number
- CN116576158A CN116576158A CN202310634999.4A CN202310634999A CN116576158A CN 116576158 A CN116576158 A CN 116576158A CN 202310634999 A CN202310634999 A CN 202310634999A CN 116576158 A CN116576158 A CN 116576158A
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- Prior art keywords
- flow
- bearing
- cooling structure
- hole
- pump housing
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- 238000001816 cooling Methods 0.000 title claims abstract description 37
- 239000003380 propellant Substances 0.000 claims abstract description 59
- 238000007789 sealing Methods 0.000 claims description 15
- 230000001105 regulatory effect Effects 0.000 description 9
- 239000007788 liquid Substances 0.000 description 5
- 230000001276 controlling effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/586—Cooling; Heating; Diminishing heat transfer specially adapted for liquid pumps
- F04D29/5886—Cooling; Heating; Diminishing heat transfer specially adapted for liquid pumps cooling by injection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/04—Shafts or bearings, or assemblies thereof
- F04D29/046—Bearings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application discloses a bearing cooling structure for a turbine pump and the turbine pump, relates to the technical field of space engines, and aims to solve the problem that the performance and service life of a bearing are affected when too little or too much propellant exists. The bearing cooling structure for the turbine pump comprises a rotating shaft, a centrifugal wheel, a bearing, a pump shell and a flow limiting nozzle, wherein the bearing and the centrifugal wheel are sequentially arranged on the rotating shaft along the axial direction of the rotating shaft, the pump shell is arranged on the outer side of the centrifugal wheel and the bearing in a surrounding mode, a flow channel for circulating propellant is arranged on the pump shell, two ends of the flow channel face the centrifugal wheel and the bearing respectively, the flow limiting nozzle is detachably connected with the pump shell and is communicated with the flow channel, and the propellant flows to the bearing through the flow limiting nozzle and the flow channel; the flow limiting nozzle is internally provided with a flow limiting hole, and the aperture of the flow limiting hole is smaller than that of the flow passage. The turbine pump comprises the bearing cooling structure for the turbine pump.
Description
Technical Field
The application relates to the technical field of space engines, in particular to a bearing cooling structure for a turbine pump and the turbine pump.
Background
The liquid rocket engine is a chemical rocket engine adopting liquid propellant, the liquid rocket engine comprises a turbine pump for pressurizing the propellant, when the liquid rocket engine works, the propellant with certain pressure and flow is conveyed to a thrust chamber through the turbine pump, the propellant forms high-pressure high-temperature fuel gas after being combusted in the thrust chamber, and the high-pressure high-temperature fuel gas is sprayed out through a spray head to reversely push the liquid rocket engine to realize flying.
In general, a turbo pump is composed of a centrifugal pump for outputting energy and a turbine for delivering a propellant having a certain pressure and flow rate by means of the energy output from the turbine, and is supported by bearings because the centrifugal pump is in a high-speed rotation state when operated.
When the centrifugal pump works, the bearing is required to bear axial force and radial force from the centrifugal pump, and also is required to bear the vibration action of the turbine pump, so that a large amount of heat is generated when the bearing works, and therefore, the bearing needs to be cooled. However, when the structure is adopted, the flow of the propellant conveyed to the bearing cannot be controlled, and when the propellant is too little, the heat generated by friction of the bearing cannot be taken away in time, so that the cooling effect of the bearing is reduced; when the propellant is too much, the lubrication effect of the bearing is increased, the performance loss of the bearing is increased, and the self performance and the service life of the bearing are further affected.
Disclosure of Invention
The application aims to provide a bearing cooling structure for a turbine pump and the turbine pump, so as to regulate the flow of propellant to be delivered to the bearing, improve the self-performance and service life of the bearing.
In order to achieve the above object, in a first aspect, the present application provides a bearing cooling structure for a turbine pump, including a rotating shaft, a centrifugal wheel, a bearing, and a pump housing, wherein the bearing and the centrifugal wheel are sequentially mounted on the rotating shaft along an axial direction of the rotating shaft, the pump housing is disposed around the centrifugal wheel and outside the bearing, and the rotating shaft and the pump housing are rotatably connected through the bearing;
the pump shell is provided with a runner for circulating propellant, two ends of the runner face the centrifugal wheel and the bearing respectively, the bearing cooling structure further comprises a flow limiting nozzle for limiting the flow of the propellant, the flow limiting nozzle is detachably connected with the pump shell and communicated with the runner, and the propellant flows to the bearing through the flow limiting nozzle and the runner;
the flow limiting nozzle is internally provided with a flow limiting hole, and the aperture of the flow limiting hole is smaller than that of the flow passage.
Under the condition of adopting the technical scheme, the bearing cooling structure comprises a rotating shaft, a centrifugal wheel, a bearing, a pump shell and a flow limiting nozzle, wherein a flow channel for circulating propellant is arranged on the pump shell, two ends of the flow channel face the centrifugal wheel and the bearing respectively, the flow limiting nozzle is detachably connected with the pump shell and is communicated with the flow channel, the propellant flows to the bearing through the flow limiting nozzle and the flow channel, a flow limiting hole is formed in the flow limiting nozzle, and the aperture of the flow limiting hole is smaller than that of the flow channel. By adopting the structure, the flow rate of the propellant can be limited through the flow limiting hole of the flow limiting nozzle, the flow rate of the propellant which is conveyed to the bearing can be regulated through controlling the aperture of the flow limiting hole, when the flow rate of the propellant is overlarge, the flow limiting nozzle with the small aperture flow limiting hole can be adopted, when the flow rate of the propellant is overlarge, the flow limiting nozzle with the large aperture flow limiting hole can be adopted, and the flow rate of the propellant which is conveyed to the bearing can be regulated through adopting the flow limiting nozzle with the flow limiting holes with different sizes, so that the self performance and the service life of the bearing are improved, and the service life of the turbine pump is further improved.
In some possible implementations, a positioning groove for axially positioning and radially positioning the flow-limiting nozzle is arranged on the pump housing, and an opening communicated with the flow channel is arranged at the bottom of the positioning groove;
the flow limiting nozzle comprises a first section and a tail section, the tail section is clamped in the positioning groove, a through hole is formed in the tail section, a flow limiting hole is formed in the first section, and the flow limiting hole, the through hole, the opening and the flow channel are communicated in sequence;
the flow limiting nozzle is communicated with one end of the flow channel far away from the bearing.
In some possible implementations, the first section is formed with an annular protrusion extending outward along a radial direction of the first section, and the pump housing is provided with a first limit groove, and the annular protrusion is clamped in the first limit groove to limit the axial movement of the flow-limiting nozzle in the direction of the flow channel.
In some possible implementations, the flow-limiting nozzle further comprises a baffle, wherein the baffle is detachably connected with the pump housing and abuts against the end surface of the head section, which is far away from the tail section, so as to limit the axial movement of the flow-limiting nozzle in the direction far away from the flow channel;
the pump shell is provided with a second limit groove, and the baffle is clamped in the second limit groove.
In some possible implementations, a seal ring is also included, the seal ring being disposed between the head section and the pump housing.
In some possible implementations, the centrifugal wheel further comprises a floating ring, wherein the floating ring is sleeved outside the centrifugal wheel, and the end face of the floating ring is abutted with the end face of the baffle to realize end face sealing.
In some possible implementations, the pump further includes a stop nut sleeved outside the floating ring and connected to the pump housing, and a gap is formed between the floating ring and the stop nut to form a flow path for the propellant to circulate, and the flow path is communicated with the flow limiting hole.
In some possible implementations, the pump further comprises a threaded fastener, the limit nut is provided with a through hole, the pump housing is provided with a threaded hole, and the threaded fastener passes through the through hole to be in threaded connection with the threaded hole.
In some possible implementations, the flow-restricting nozzles are provided in a plurality, and the aperture of the flow-restricting orifice in the plurality of flow-restricting nozzles sequentially increases.
In a second aspect, the present application also provides a turbine pump comprising a bearing cooling structure for a turbine pump as provided in any one of the above aspects.
Under the condition of adopting the technical scheme, as the turbine pump adopts the bearing cooling structure for the turbine pump, the flow of the propellant conveyed to the bearing can be regulated, and the self performance and the service life of the bearing are improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application and do not constitute a limitation on the application. In the drawings:
FIG. 1 is a schematic view of a bearing cooling structure according to the present application.
Reference numerals:
the centrifugal pump comprises a 1-bearing, a 2-pump shell, a 3-runner, a 4-flow limiting nozzle, a 5-sealing ring, a 6-baffle, a 7-floating ring, an 8-limit nut and a 9-centrifugal wheel.
Detailed Description
In order to make the technical problems, technical schemes and beneficial effects to be solved more clear, the application is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application.
It will be understood that when an element is referred to as being "mounted" or "disposed" on another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise. The meaning of "a number" is one or more than one unless specifically defined otherwise.
In the description of the present application, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", "left", "right", etc., are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present application.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
Referring to fig. 1, an embodiment of the application provides a bearing cooling structure for a turbine pump, which comprises a rotating shaft, a centrifugal wheel 9, a bearing 1 and a pump housing 2, wherein the bearing 1 and the centrifugal wheel 9 are sequentially arranged on the rotating shaft along the axial direction of the rotating shaft, the pump housing 2 is arranged outside the centrifugal wheel 9 and the bearing 1 in a surrounding manner, and the rotating shaft and the pump housing 2 are rotationally connected through the bearing 1; the pump housing 2 is provided with a flow channel 3 for flowing propellant, two ends of the flow channel 3 face the centrifugal wheel 9 and the bearing 1 respectively, the bearing cooling structure further comprises a flow limiting nozzle 4 for limiting the flow of the propellant, the flow limiting nozzle 4 is detachably connected with the pump housing 2 and is communicated with the flow channel 3, and the propellant flows to the bearing 1 through the flow limiting nozzle 4 and the flow channel 3; a limiting hole is arranged in the limiting nozzle 4, and the aperture of the limiting hole is smaller than that of the flow passage 3.
Under the condition of adopting the technical scheme, the bearing cooling structure comprises a rotating shaft, a centrifugal wheel 9, a bearing 1, a pump housing 2 and a flow limiting nozzle 4, wherein the pump housing 2 is provided with a flow channel 3 for circulating propellant, two ends of the flow channel 3 face the centrifugal wheel 9 and the bearing 1 respectively, the flow limiting nozzle 4 is detachably connected with the pump housing 2 and is communicated with the flow channel 3, the propellant flows to the bearing 1 through the flow limiting nozzle 4 and the flow channel 3, a flow limiting hole is arranged in the flow limiting nozzle 4, and the aperture of the flow limiting hole is smaller than that of the flow channel 3. With this structure, the flow rate of the propellant can be restricted by the flow restricting hole of the flow restricting nozzle 4, the flow rate of the propellant to be delivered to the bearing 1 can be regulated by controlling the aperture of the flow restricting hole, when the flow rate of the propellant is too large, the flow restricting nozzle 4 with a small aperture flow restricting hole can be adopted, when the flow rate of the propellant is too small, the flow rate of the propellant to be delivered to the bearing 1 can be regulated by adopting the flow restricting nozzle 4 with a large aperture flow restricting hole, thereby improving the self performance and the service life of the bearing 1 and further improving the service life of the turbine pump. In addition, when the flow rate of the propellant is required to be changed, the flow-limiting nozzles 4 with different apertures can be replaced, and other parts are not required to be changed, so that the flow rate of the propellant can be adjusted more conveniently.
In some embodiments, the pump housing 2 is provided with a positioning groove for axially positioning and radially positioning the flow-limiting nozzle 4, and the bottom of the positioning groove is provided with an opening communicated with the flow channel 3; the flow limiting nozzle 4 comprises a first section and a tail section, the tail section is clamped in the positioning groove, a through hole is formed in the tail section, a flow limiting hole is formed in the first section, and the flow limiting hole, the through hole, the opening and the flow channel 3 are communicated in sequence; the restrictor nozzle 4 communicates with the end of the flow channel 3 remote from the bearing 1. Illustratively, the flow channel 3 includes a direct current portion and an inclined flow portion, the direct current portion and the inclined flow portion are communicated, the tail section is communicated with the direct current portion, one end of the inclined flow portion faces the bearing 1, and the propellant sequentially flows to the bearing 1 through the direct current portion and the inclined flow portion for cooling. Illustratively, the aperture of the through hole is equal to the aperture of the direct current part, the axial movement of the flow-limiting nozzle 4 can be limited by the bottom of the positioning groove, and the radial movement of the flow-limiting nozzle 4 can be limited by the groove wall of the positioning groove, so that the flow-limiting nozzle 4 can be positioned in the positioning groove. With this structure, the flow-limiting nozzle 4 is positioned by the positioning groove, so that the flow-limiting nozzle 4 can be positioned more stably.
As shown in fig. 1, further, an annular protrusion is formed on the first section and extends outwards along the radial direction of the first section, a first limit groove is formed on the pump housing 2, and the annular protrusion is clamped in the first limit groove to limit the axial movement of the flow limiting nozzle 4 towards the direction of the flow channel 3. By adopting the structure, the stability of the flow-limiting nozzle 4 can be further improved by mutually limiting the annular bulge and the first limiting groove, the leakage of the propellant caused by the deviation of the flow-limiting nozzle 4 is avoided, and the sealing performance between the flow-limiting nozzle 4 and the pump housing 2 can be improved.
In some alternatives, the bearing cooling structure further comprises a baffle 6, wherein the baffle 6 is detachably connected with the pump housing 2 and abuts against the end surface of the head section, which is far away from the tail section, so as to limit the axial movement of the flow limiting nozzle 4 in the direction far away from the flow channel 3; the pump housing 2 is provided with a second limit groove, and the baffle 6 is clamped in the second limit groove. With this structure, one end of the flow-limiting nozzle 4 in the axial direction is positioned by the positioning groove, and the other end is positioned by the baffle 6, so that the flow-limiting nozzle 4 can be mounted and fixed on the pump housing 2, and the sealing performance between the flow-limiting nozzle 4 and the pump housing 2 can be further improved.
As shown in fig. 1, further, the bearing cooling structure further comprises a sealing ring 5, the sealing ring 5 being arranged between the head section and the pump housing 2, and the sealing ring 5 being in clearance fit with both the head section and the pump housing 2. Illustratively, a seal groove is provided outside the head section of the flow restricting nozzle 4, and a seal ring 5 is provided in the seal groove. By adopting the structure, the first sections of the pump housing 2 and the flow-limiting nozzle 4 are sealed by the sealing ring 5, so that the sealing performance between the flow-limiting nozzle 4 and the pump housing 2 can be further improved, the leakage of the propellant is prevented, and meanwhile, the stability of the flow-limiting nozzle 4 is improved.
As shown in fig. 1, the bearing cooling structure further comprises a floating ring 7, the floating ring 7 is sleeved on the outer side of the centrifugal wheel 9, and the end face of the floating ring 7 abuts against the end face of the baffle 6 to realize end face sealing. Illustratively, the floating ring 7 rotates coaxially with the centrifugal wheel 9, and the sealing performance of the turbine pump can be improved by sealing the centrifugal wheel 9 by the floating ring 7. Illustratively, the end surface of the baffle 6 is located on the same plane with the end surface of the flow limiting nozzle 4, the floating ring 7 includes an annular protrusion formed by extending towards the baffle 6, and the end surface of the annular protrusion abuts against the end surface of the baffle 6 to realize end surface sealing. With this structure, the end face between the floating ring 7 and the baffle 6 is sealed, and the sealing performance of the turbine pump can be improved.
As shown in fig. 1, the bearing cooling structure further comprises a limit nut 8, wherein the limit nut 8 is sleeved outside the floating ring 7 and is connected with the pump housing 2, a gap exists between the floating ring 7 and the limit nut 8 to form a flow path for propellant to circulate, and the flow path is communicated with the limit hole. Illustratively, the limit nut 8 has an annular structure, and the pump housing 2 includes an annular positioning plate extending along the axial direction of the rotating shaft, and the limit nut 8 abuts against the end surface of the baffle 6. The limit nut 8 comprises, for example, an annular plate coaxially arranged with the rotary shaft and a positioning plate extending in the radial direction of the annular plate, the positioning plate being connected to the annular plate. With this structure, when the centrifugal wheel 9 drives the floating ring 7 to rotate, the propellant can be driven to flow into the flow limiting hole of the flow limiting nozzle 4 from the flow path between the floating ring 7 and the limiting nut 8, so as to optimize the flow path of the propellant, and the propellant can flow into the flow limiting nozzle 4 and flow to the bearing 1 for cooling through the flow channel 3.
When the bearing 1 is cooled, the centrifugal wheel 9 rotates and a high-pressure propellant is led out from the outlet of the centrifugal wheel, the propellant overcomes the resistance in the inner return flow path of the centrifugal pump, flows into the flow limiting hole of the flow limiting nozzle 4 from the flow path between the floating ring 7 and the limiting nut 8, flows into the flow channel 3 of the pump housing 2 through the flow limiting hole, and flows into the bearing 1 through the flow channel 3 to cool the bearing 1.
In some embodiments, the bearing cooling structure further comprises a threaded fastener, wherein the limit nut 8 is provided with a through hole, and the pump housing 2 is provided with a threaded hole, and the threaded fastener passes through the through hole and is in threaded connection with the threaded hole. Illustratively, the threaded fastener is a screw, and the positioning plate of the limit nut 8 is provided with a through hole, and the screw passes through the through hole to be in threaded connection with the threaded hole of the pump housing 2. By adopting the structure, the limit nut 8 is further fixed through the threaded fastener, so that the connection reliability of the limit nut 8 can be improved, and the limit nut 8 is prevented from loosening.
In some alternatives, the flow restricting nozzles 4 are provided in plural, and the aperture of the flow restricting orifice in the plural flow restricting nozzles 4 is sequentially increased. With the adoption of the structure, when the flow of the propellant is required to be regulated, the flow regulating of the flow limiting nozzle 4 is more convenient by changing the flow limiting nozzle 4 with different aperture limiting holes.
The embodiment of the application also provides a turbine pump, which comprises the bearing cooling structure for the turbine pump.
Under the condition of adopting the technical scheme, the bearing cooling structure comprises a rotating shaft, a centrifugal wheel 9, a bearing 1, a pump housing 2 and a flow limiting nozzle 4, wherein the pump housing 2 is provided with a flow channel 3 for circulating propellant, two ends of the flow channel 3 face the centrifugal wheel 9 and the bearing 1 respectively, the flow limiting nozzle 4 is detachably connected with the pump housing 2 and is communicated with the flow channel 3, the propellant flows to the bearing 1 through the flow limiting nozzle 4 and the flow channel 3, a flow limiting hole is arranged in the flow limiting nozzle 4, and the aperture of the flow limiting hole is smaller than that of the flow channel 3. With this structure, the flow rate of the propellant can be restricted by the flow restricting hole of the flow restricting nozzle 4, the flow rate of the propellant to be delivered to the bearing 1 can be regulated by controlling the aperture of the flow restricting hole, when the flow rate of the propellant is too large, the flow restricting nozzle 4 with a small aperture flow restricting hole can be adopted, when the flow rate of the propellant is too small, the flow rate of the propellant to be delivered to the bearing 1 can be regulated by adopting the flow restricting nozzle 4 with a large aperture flow restricting hole, thereby improving the self performance and the service life of the bearing 1 and further improving the service life of the turbine pump. In addition, when the flow rate of the propellant is required to be changed, the flow-limiting nozzles 4 with different apertures can be replaced, and other parts are not required to be changed, so that the flow rate of the propellant can be adjusted more conveniently.
In the description of the above embodiments, particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The bearing cooling structure for the turbine pump is characterized by comprising a rotating shaft, a centrifugal wheel, a bearing and a pump housing, wherein the bearing and the centrifugal wheel are sequentially arranged on the rotating shaft along the axial direction of the rotating shaft, the pump housing surrounds and is arranged on the outer sides of the centrifugal wheel and the bearing, and the rotating shaft and the pump housing are rotationally connected through the bearing;
the centrifugal wheel is characterized in that a flow passage for circulating propellant is arranged on the pump housing, two ends of the flow passage face the centrifugal wheel and the bearing respectively, the bearing cooling structure further comprises a flow limiting nozzle for limiting the flow of the propellant, the flow limiting nozzle is detachably connected with the pump housing and communicated with the flow passage, and the propellant flows to the bearing through the flow limiting nozzle and the flow passage;
and a limiting hole is arranged in the limiting nozzle, and the aperture of the limiting hole is smaller than that of the flow passage.
2. The bearing cooling structure for a turbo pump according to claim 1, wherein a positioning groove for axially positioning and radially positioning the flow-limiting nozzle is provided on the pump housing, and an opening communicating with the flow passage is provided at a bottom of the positioning groove;
the flow limiting nozzle comprises a first section and a tail section, the tail section is clamped in the positioning groove, a through hole is formed in the tail section, the flow limiting hole is formed in the first section, and the flow limiting hole, the through hole, the opening and the flow channel are communicated in sequence;
the flow-limiting nozzle is communicated with one end of the flow channel far away from the bearing.
3. The bearing cooling structure for a turbo pump according to claim 2, wherein an annular protrusion is formed on the head section to extend outward in a radial direction thereof, a first limit groove is provided on the pump housing, and the annular protrusion is engaged in the first limit groove to limit axial movement of the flow-restricting nozzle toward the flow passage side.
4. A bearing cooling structure for a turbo pump according to claim 3, further comprising a baffle detachably connected to the pump housing and pressing an end face of the head section away from the tail section to restrict axial movement of the flow restricting nozzle in a direction away from the flow path;
the pump housing is provided with a second limit groove, and the baffle is clamped in the second limit groove.
5. The bearing cooling structure for a turbo pump of claim 4, further comprising a seal ring disposed between the head section and the pump housing.
6. The bearing cooling structure for a turbo pump according to claim 4, further comprising a floating ring, the floating ring being fitted outside the centrifugal wheel, an end face of the floating ring being abutted against an end face of the baffle to achieve end face sealing.
7. The bearing cooling structure for a turbo pump of claim 6, further comprising a check nut sleeved outside the floating ring and connected to the pump housing, a gap being provided between the floating ring and the check nut to form a flow path for the propellant to flow, the flow path being in communication with the check hole.
8. The bearing cooling structure for a turbo pump of claim 7, further comprising a threaded fastener, wherein the retainer nut is provided with a through hole, and wherein the pump housing is provided with a threaded hole, and wherein the threaded fastener is threadedly coupled with the threaded hole through the through hole.
9. The bearing cooling structure for a turbo pump according to claim 1, wherein a plurality of the flow restricting nozzles are provided, and the aperture of the flow restricting hole in the plurality of the flow restricting nozzles is sequentially increased.
10. A turbopump comprising a bearing cooling structure for a turbopump according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310634999.4A CN116576158A (en) | 2023-05-31 | 2023-05-31 | Bearing cooling structure for turbine pump and turbine pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310634999.4A CN116576158A (en) | 2023-05-31 | 2023-05-31 | Bearing cooling structure for turbine pump and turbine pump |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116576158A true CN116576158A (en) | 2023-08-11 |
Family
ID=87539585
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310634999.4A Pending CN116576158A (en) | 2023-05-31 | 2023-05-31 | Bearing cooling structure for turbine pump and turbine pump |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116576158A (en) |
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2023
- 2023-05-31 CN CN202310634999.4A patent/CN116576158A/en active Pending
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