CN214741729U - Low-temperature rocket engine and bearing cooling structure of turbopump thereof - Google Patents
Low-temperature rocket engine and bearing cooling structure of turbopump thereof Download PDFInfo
- Publication number
- CN214741729U CN214741729U CN202021881892.8U CN202021881892U CN214741729U CN 214741729 U CN214741729 U CN 214741729U CN 202021881892 U CN202021881892 U CN 202021881892U CN 214741729 U CN214741729 U CN 214741729U
- Authority
- CN
- China
- Prior art keywords
- turbopump
- precooling
- rocket engine
- cooling
- bearing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model belongs to the technical field of liquid engines, and discloses a bearing cooling structure of a turbopump of a low-temperature rocket engine, which is used for a multi-shaft turbopump; the method comprises the following steps: the device comprises a circulating connecting pipe, an inner cooling flow path arranged in a turbine pump and a precooling discharge port; a plurality of precooling discharge ports are formed in the turbine pump corresponding to the plurality of shafts of the turbine pump, and the plurality of precooling discharge ports are communicated with the inner cooling flow path; two ends of the circulating connecting pipe are respectively connected with two adjacent precooling discharge ports, and a precooling discharge port is formed in the circulating connecting pipe. The utility model provides a low temperature rocket engine and turbopump and bearing cooling structure thereof can realize the unified cooling of multiaxis turbopump, simplify cooling structure.
Description
Technical Field
The utility model relates to a liquid engine technical field, in particular to bearing cooling structure of low temperature rocket engine and turbopump thereof.
Background
The turbopump is a core component of the liquid rocket engine and provides high-pressure propellant for the thrust chamber. The bearing is used as a core component of rotating machinery such as a turbine pump and the like, and needs to be well cooled in the working process, so that the damage to products caused by mechanical friction and overheating in the running process is prevented. Because the propellant used by the low-temperature liquid rocket engine is low-temperature propellant, and the working environment of the turbine pump bearing is low-temperature environment; the low-temperature propellant is used for precooling the bearing before the engine is started, and is also used for continuously cooling the bearing in the working process of the engine. The traditional turbine pump bearing uses propellant for cooling/precooling, but the flow path of cooling and precooling of the bearing is separated; the bearing cooling usually adopts an inner loop, the precooling adopts discharge precooling, and the propellant after precooling is independently discharged to the outside through a discharge port. However, the conventional precooling/cooling scheme is only suitable for the single-shaft turbine pump scheme, and in the case of multiple shafts, the precooling and the cooling can be carried out independently, so that the use limitation is large.
SUMMERY OF THE UTILITY MODEL
The utility model provides a bearing cooling structure of low temperature rocket engine and turbopump thereof solves among the prior art the bearing of each axle of multiaxis turbopump and only can carry out independent precooling and cooling, leads to using the big technical problem of limitation.
In order to solve the technical problem, the utility model provides a bearing cooling/precooling structure of a low-temperature rocket engine turbopump, which is used for a multi-shaft turbopump or a long-span bearing turbopump; the method comprises the following steps: the device comprises a circulating connecting pipe, an inner cooling flow path arranged in a turbine pump and a precooling discharge port;
a plurality of precooling discharge ports are formed in the turbine pump corresponding to the plurality of shafts of the turbine pump, and the plurality of precooling discharge ports are communicated with the inner cooling flow path;
two ends of the circulating connecting pipe are respectively connected with two adjacent precooling discharge ports, and a precooling discharge port is formed in the circulating connecting pipe.
A cryogenic rocket engine turbopump comprising: the bearing cooling structure comprises a multi-shaft turbopump body and a bearing cooling structure of the low-temperature rocket engine turbopump arranged on the multi-shaft turbopump body.
A low-temperature rocket engine adopts the turbopump of the low-temperature rocket engine.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
according to the low-temperature rocket engine and the turbopump and bearing cooling structure thereof provided by the embodiment of the application, under the condition that an internal cooling flow path and a precooling loop of the turbopump are not changed, the external circulating connecting pipes are arranged to be respectively connected with the adjacent precooling external discharge ports, so that connecting pipelines are established among a plurality of shafts; on one hand, the discharged cooling medium can be uniformly discharged during precooling, so that excessive precooling discharge structures are avoided; meanwhile, when the turbine pump works, the propellant can be subjected to internal circulation cooling among the bearings of the multiple shafts through the pipeline formed among the multiple shaft structures, independent cooling is not needed, the cooling structure is greatly simplified, and the application range is expanded.
Drawings
Fig. 1 is a schematic diagram of a precooling process of a wheel pump bearing cooling structure of a low-temperature rocket engine provided by an embodiment of the present invention;
fig. 2 is a schematic view of a cooling process of a wheel pump bearing cooling structure of a low-temperature rocket engine provided by an embodiment of the present invention.
Detailed Description
The embodiment of the application solves the technical problem that in the prior art, the bearings of all shafts of a multi-shaft turbopump can only be independently pre-cooled and cooled, so that the use limitation is large.
In order to better understand the technical solutions, the technical solutions will be described in detail below with reference to the drawings and the specific embodiments of the present disclosure, and it should be understood that the specific features in the embodiments and examples of the present disclosure are detailed descriptions of the technical solutions of the present disclosure, but not limitations of the technical solutions of the present disclosure, and the technical features in the embodiments and examples of the present disclosure may be combined with each other without conflict.
The embodiment provides a structure capable of meeting the requirement of unified pre-cooling and cooling of a multi-shaft turbine pump based on the pre-cooling structure and the internal cooling loop structure of the conventional turbine pump, so that the complexity is greatly reduced, and the application range is expanded; of course, the present embodiment is not limited to a multi-shaft, and is applicable to a turbo pump that cannot be realized by a long-span bearing or an inner circuit.
As will be described in detail below.
Referring to fig. 1 and 2, a bearing cooling/precooling structure of a turbopump of a low-temperature rocket engine is used for a multi-shaft turbopump provided with a plurality of shafts 3 and a plurality of pairs of bearings 4; the method comprises the following steps: a circulation connection pipe 1, an internal cooling flow path opened in the turbo pump, and a pre-cooling discharge port. A plurality of precooling discharge ports are formed in the turbine pump corresponding to the plurality of shafts of the turbine pump, and the plurality of precooling discharge ports are communicated with the inner cooling flow path; two ends of the circulating connecting pipe are respectively connected with two adjacent precooling discharge ports, and a precooling discharge port 2 is formed in the circulating connecting pipe.
That is, the bearing cooling circuits of the shafts are communicated through the circulation connecting pipe 1, and the precooling discharge port is utilized without changing to other structures, so that the structure of the existing turbine pump is not influenced too much; on the contrary, the pre-cooling structure and the cooling structure are greatly simplified, and the adaptability is improved.
The operation will be described in detail below.
Referring to fig. 1, in a turbo pump pre-cooling operation, a cryogenic propellant pre-cools the bearing flow path; propellant enters the centrifugal pump through a pump inlet and then is divided into two paths to be respectively sent to the bearings at the two precooling ends, and the precooled propellant is uniformly discharged out of the centrifugal pump through the circulating connecting pipe.
Referring to fig. 2, during operation of the turbo pump, continuous inner loop cooling is required; the propellant enters the centrifugal pump to be pressurized, the split flow is divided into two paths to cool the bearing, one path of the propellant returns to the front of the pump after cooling the bearing, and the other path of the propellant returns to the front of the pump after cooling the bearing through the circulating connecting pipe.
Typically, to accommodate the switching between pre-cooling and cooling, a control valve is provided at the pre-cooling drain.
It can be found that the precooling and the cooling adopt the same external loop, the overall layout of the turbopump is simplified, the defects of a plurality of discharge ports of different shafts, a plurality of return pipes and the like are avoided, and the complexity of the overall layout of the turbopump is reduced.
The embodiment also provides an implementation scheme of a turbopump and a low-temperature rocket engine on the basis of the embodiment.
A cryogenic rocket engine turbopump comprising: the bearing cooling structure comprises a multi-shaft turbopump body and a bearing cooling structure of the low-temperature rocket engine turbopump arranged on the multi-shaft turbopump body.
A low-temperature rocket engine adopts the turbopump of the low-temperature rocket engine.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
according to the low-temperature rocket engine and the turbopump and bearing cooling structure thereof provided by the embodiment of the application, under the condition that an internal cooling flow path and a precooling loop of the turbopump are not changed, the external circulating connecting pipes are arranged to be respectively connected with the adjacent precooling external discharge ports, so that connecting pipelines are established among a plurality of shafts; on one hand, the discharged cooling medium can be uniformly discharged during precooling, so that excessive precooling discharge structures are avoided; meanwhile, when the turbine pump works, the propellant can be subjected to internal circulation cooling among the bearings of the multiple shafts through the pipeline formed among the multiple shaft structures, independent cooling is not needed, the cooling structure is greatly simplified, and the application range is expanded.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and not for limiting, and although the present invention has been described in detail with reference to the examples, those skilled in the art should understand that the technical solutions of the present invention can be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention, which should be covered by the scope of the claims of the present invention.
Claims (3)
1. A bearing cooling structure of a low-temperature rocket engine turbopump is used for a multi-shaft turbopump or a long-span bearing turbopump; it is characterized by comprising: the device comprises a circulating connecting pipe, an inner cooling flow path arranged in a turbine pump and a precooling discharge port;
a plurality of precooling discharge ports are formed in the turbine pump corresponding to the plurality of shafts of the turbine pump, and the plurality of precooling discharge ports are communicated with the inner cooling flow path;
two ends of the circulating connecting pipe are respectively connected with two adjacent precooling discharge ports, and a precooling discharge port is formed in the circulating connecting pipe.
2. A cryogenic rocket engine turbopump, comprising: a multi-axis turbopump body and a bearing cooling structure of a cryogenic rocket engine turbopump as claimed in claim 1 provided thereon.
3. A cryogenic rocket engine, characterized by: use of a low temperature rocket engine turbopump as claimed in claim 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021881892.8U CN214741729U (en) | 2020-09-02 | 2020-09-02 | Low-temperature rocket engine and bearing cooling structure of turbopump thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021881892.8U CN214741729U (en) | 2020-09-02 | 2020-09-02 | Low-temperature rocket engine and bearing cooling structure of turbopump thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214741729U true CN214741729U (en) | 2021-11-16 |
Family
ID=78573397
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021881892.8U Withdrawn - After Issue CN214741729U (en) | 2020-09-02 | 2020-09-02 | Low-temperature rocket engine and bearing cooling structure of turbopump thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214741729U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112360646A (en) * | 2020-09-02 | 2021-02-12 | 航天科工火箭技术有限公司 | Low-temperature rocket engine and turbopump and bearing cooling structure thereof |
-
2020
- 2020-09-02 CN CN202021881892.8U patent/CN214741729U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112360646A (en) * | 2020-09-02 | 2021-02-12 | 航天科工火箭技术有限公司 | Low-temperature rocket engine and turbopump and bearing cooling structure thereof |
| CN112360646B (en) * | 2020-09-02 | 2023-06-23 | 航天科工火箭技术有限公司 | Low-temperature rocket engine, turbine pump and bearing cooling structure thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11077949B2 (en) | Dual turbine thermal management system (TMS) | |
| DK2225501T3 (en) | METHOD AND DEVICE FOR CRYOGEN COOLING | |
| US8756910B2 (en) | Gas turbine engine and cooling system | |
| CN214741729U (en) | Low-temperature rocket engine and bearing cooling structure of turbopump thereof | |
| CN107429954A (en) | The method of operation of refrigerator and refrigerator | |
| CN112360646B (en) | Low-temperature rocket engine, turbine pump and bearing cooling structure thereof | |
| JPH11503223A (en) | Cooling system | |
| CN111412030A (en) | Supercritical carbon dioxide expander based on integrated cooling system | |
| US6523366B1 (en) | Cryogenic neon refrigeration system | |
| CN111425414A (en) | Special gas high-speed centrifugal compressor adopting gas suspension bearing | |
| CN109184824B (en) | Reverse Brayton cycle low-temperature refrigeration expander with air bearing structure | |
| US3158002A (en) | Operation of a thermal power plant with nuclear reactor | |
| CN214501885U (en) | Full low temperature circulation hydrogen liquefier | |
| CN114501921A (en) | Vapor circulation system for cooling components and related method | |
| CN112856891A (en) | Vertical ultra-low temperature freezer | |
| US3201941A (en) | Assembly of turbomachines | |
| CN212959283U (en) | Closed circulation coupling device | |
| US5042970A (en) | Fast recharge compressor | |
| CN103673371A (en) | Four-wheel-coaxial two-level expansion turbine cooler | |
| CN114763961A (en) | Full low temperature circulation hydrogen liquefier | |
| US3516756A (en) | Sealing device with leakage gas recovery for cyrogenic gas expansion turbine | |
| CN117469187A (en) | Airborne electric control air cooling system based on counter-rotating compressor | |
| KR102529655B1 (en) | Ventilation system for bearing sump | |
| WO2023201220A1 (en) | Cryogenic expansion turbine with magnetic bearings | |
| CN113375892B (en) | Wind tunnel test method based on reverse Brayton cycle of turboexpander |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20211116 Effective date of abandoning: 20230623 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20211116 Effective date of abandoning: 20230623 |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |