A bearing cooling structure for a turbopump and a turbopump

Abstract

This invention discloses a bearing cooling structure and a turbopump for a turbopump, relating to the field of aerospace engine technology, to address the problem of insufficient or excessive propellant affecting bearing performance and service life. The bearing cooling structure for the turbopump includes a shaft, a centrifugal impeller, a bearing, a pump housing, and a flow-limiting nozzle. The bearing and centrifugal impeller are sequentially mounted on the shaft along its axial direction. The pump housing surrounds the centrifugal impeller and bearing, and has a flow channel for propellant flow. The two ends of the flow channel face the centrifugal impeller and the bearing, respectively. The flow-limiting nozzle is detachably connected to the pump housing and communicates with the flow channel. Propellant flows to the bearing through the flow-limiting nozzle and the flow channel. The flow-limiting nozzle contains a flow-limiting orifice, the diameter of which is smaller than the diameter of the flow channel. The turbopump includes the bearing cooling structure described above.

Description

Technical Field

[0001] This invention relates to the field of aerospace engine technology, and in particular to a bearing cooling structure for a turbopump and a turbopump. Background Technology

[0002] A liquid rocket engine is a chemical rocket engine that uses liquid propellant. A liquid rocket engine includes a turbopump for pressurizing the propellant. When the liquid rocket engine is working, the turbopump delivers propellant with a certain pressure and flow rate to the thrust chamber. After the propellant burns in the thrust chamber, it forms high-pressure and high-temperature gas. The high-pressure and high-temperature gas is ejected through the nozzle to propel the liquid rocket engine in the opposite direction to achieve flight.

[0003] Typically, a turbopump consists of a centrifugal pump and a turbine. The turbine is used to output energy, and the centrifugal pump relies on the energy output by the turbine to transport propellant with a certain pressure and flow rate. Since the centrifugal pump is in a high-speed rotating state when it is working, it needs to be supported by bearings.

[0004] When a centrifugal pump is operating, the bearings not only need to withstand the axial and radial forces from the centrifugal pump itself, but also the vibrations from the turbine pump. This results in a significant amount of heat being generated during bearing operation, necessitating bearing cooling. Typically, a flow channel is installed within the pump casing, through which the propellant from the turbine pump flows to cool the bearing and reduce its temperature. However, with this structure, the propellant flow rate delivered to the bearing cannot be controlled. If there is too little propellant, the heat generated by bearing friction cannot be dissipated in time, reducing the cooling effect; if there is too much propellant, it increases the lubrication effect on the bearing, increasing performance losses and ultimately affecting the bearing's performance and service life. Summary of the Invention

[0005] The purpose of this invention is to provide a bearing cooling structure and a turbopump for use in a turbopump, so as to regulate the propellant flow rate delivered to the bearing and improve the bearing's performance and service life.

[0006] To achieve the above objectives, in a first aspect, the present invention provides a bearing cooling structure for a turbopump, comprising a rotating shaft, a centrifugal wheel, a bearing, and a pump housing. The bearing and the centrifugal wheel are sequentially mounted on the rotating shaft along the axial direction of the rotating shaft, and the pump housing surrounds the centrifugal wheel and the bearing. The rotating shaft and the pump housing are rotatably connected by the bearing.

[0007] The pump housing is provided with a flow channel for the propellant to flow. The two ends of the flow channel are respectively facing the centrifugal wheel and the bearing. The bearing cooling structure also includes a flow-limiting nozzle for limiting the propellant flow. The flow-limiting nozzle is detachably connected to the pump housing and communicates with the flow channel. The propellant flows to the bearing through the flow-limiting nozzle and the flow channel.

[0008] A flow-limiting orifice is provided inside the flow-limiting nozzle, and the diameter of the flow-limiting orifice is smaller than the diameter of the flow channel.

[0009] With the above technical solution, the bearing cooling structure includes a shaft, a centrifugal impeller, a bearing, a pump housing, and a flow-limiting nozzle. The pump housing has a flow channel for propellant flow, with its two ends facing the centrifugal impeller and the bearing, respectively. The flow-limiting nozzle is detachably connected to the pump housing and communicates with the flow channel. The propellant flows to the bearing through the flow-limiting nozzle and the flow channel. The flow-limiting nozzle contains a flow-limiting orifice, the diameter of which is smaller than the diameter of the flow channel. Using this structure, the flow-limiting orifice of the flow-limiting nozzle can limit the propellant flow rate. By controlling the orifice diameter, the propellant flow rate delivered to the bearing can be adjusted. When the propellant flow rate is too high, a flow-limiting nozzle with a small-diameter orifice can be used; when the propellant flow rate is too low, a flow-limiting nozzle with a large-diameter orifice can be used. By using flow-limiting nozzles with different orifice sizes, the propellant flow rate delivered to the bearing can be adjusted, thereby improving the bearing's performance and service life, and consequently, extending the service life of the turbopump.

[0010] In some possible implementations, the pump housing is provided with a positioning groove for axial and radial positioning of the flow-limiting nozzle, and the bottom of the positioning groove is provided with an opening that communicates with the flow channel.

[0011] The flow-limiting nozzle includes a first section and a tail section. The tail section is snapped into a positioning groove and has a through hole. The flow-limiting hole is located in the first section. The flow-limiting hole, through hole, opening and flow channel are connected in sequence.

[0012] The flow-limiting nozzle is connected to the end of the flow channel furthest from the bearing.

[0013] In some possible implementations, an annular protrusion extends outward along its radial direction on the first segment, and a first limiting groove is provided on the pump housing. The annular protrusion is engaged in the first limiting groove to restrict the axial movement of the flow-limiting nozzle toward the flow channel.

[0014] In some possible implementations, a baffle is also included, which is detachably connected to the pump housing and presses against the end face of the first section away from the tail section to limit the axial movement of the flow-limiting nozzle away from the flow channel.

[0015] A second limiting groove is provided on the pump housing, and the baffle is engaged in the second limiting groove.

[0016] In some possible implementations, a sealing ring is also included, which is disposed between the head section and the pump housing.

[0017] In some possible implementations, a floating ring is also included, which is fitted around the outside of the centrifugal wheel, with the end face of the floating ring abutting against the end face of the baffle to achieve an end face seal.

[0018] In some possible implementations, a limiting nut is also included, which is fitted around the outside of the floating ring and connected to the pump housing. There is a gap between the floating ring and the limiting nut to form a flow path for propellant flow, and the flow path is connected to the flow restriction orifice.

[0019] In some possible implementations, threaded fasteners are also included, with a through hole on the limit nut and a threaded hole on the pump housing, and the threaded fastener passing through the through hole and threadedly connected to the threaded hole.

[0020] In some possible implementations, multiple flow-limiting nozzles are provided, and the diameter of the flow-limiting orifices in the multiple flow-limiting nozzles increases sequentially.

[0021] In a second aspect, the present invention also provides a turbopump, including a bearing cooling structure for a turbopump as provided in any of the above embodiments.

[0022] With the above technical solution, since the turbopump adopts the bearing cooling structure for turbopumps in this application, the propellant flow rate delivered to the bearing can be adjusted, thereby improving the bearing's performance and service life. Attached Figure Description

[0023] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0024] Figure 1 This is a schematic diagram of the bearing cooling structure in this invention.

[0025] Figure label:

[0026] 1-Bearing, 2-Pump housing, 3-Flow channel, 4-Flow limiting nozzle, 5-Sealing ring, 6-Baffle, 7-Floating ring, 8-Limit nut, 9-Centrifugal wheel. Detailed Implementation

[0027] To make the technical problems to be solved, the technical solutions, and the beneficial effects of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0028] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0029] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. "Several" means one or more, unless otherwise explicitly specified.

[0030] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0031] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0032] Please see Figure 1 This invention provides a bearing cooling structure for a turbopump, comprising a shaft, a centrifugal wheel 9, a bearing 1, and a pump housing 2. The bearing 1 and the centrifugal wheel 9 are sequentially mounted on the shaft along its axial direction. The pump housing 2 surrounds the centrifugal wheel 9 and the bearing 1. The shaft and the pump housing 2 are rotatably connected via the bearing 1. The pump housing 2 is provided with a flow channel 3 for propellant flow, with both ends of the flow channel 3 facing the centrifugal wheel 9 and the bearing 1, respectively. The bearing cooling structure also includes a flow-limiting nozzle 4 for limiting the propellant flow rate. The flow-limiting nozzle 4 is detachably connected to the pump housing 2 and communicates with the flow channel 3. The propellant flows to the bearing 1 through the flow-limiting nozzle 4 and the flow channel 3. The flow-limiting nozzle 4 is provided with a flow-limiting orifice, the diameter of which is smaller than the diameter of the flow channel 3.

[0033] With the above technical solution, the bearing cooling structure includes a rotating shaft, a centrifugal wheel 9, a bearing 1, a pump housing 2, and a flow-limiting nozzle 4. The pump housing 2 has a flow channel 3 for propellant flow, with both ends of the flow channel 3 facing the centrifugal wheel 9 and the bearing 1, respectively. The flow-limiting nozzle 4 is detachably connected to the pump housing 2 and communicates with the flow channel 3. The propellant flows to the bearing 1 through the flow-limiting nozzle 4 and the flow channel 3. The flow-limiting nozzle 4 has a flow-limiting orifice, the diameter of which is smaller than the diameter of the flow channel 3. Using this structure, the flow rate of the propellant can be limited by the flow-limiting orifice of the flow-limiting nozzle 4. By controlling the orifice diameter, the flow rate of the propellant delivered to the bearing 1 can be adjusted. When the propellant flow rate is too high, a flow-limiting nozzle 4 with a small-diameter orifice can be used; when the propellant flow rate is too low, a flow-limiting nozzle 4 with a large-diameter orifice can be used. By using flow-limiting nozzles 4 with different sized orifices, the flow rate of the propellant delivered to the bearing 1 can be adjusted, thereby improving the performance and service life of the bearing 1, and consequently, extending the service life of the turbopump. Furthermore, when it is necessary to change the propellant flow rate, it can be done by replacing the flow-limiting nozzle 4 with one of different orifice diameters without changing other parts, thus making it easier to adjust the propellant flow rate.

[0034] In some embodiments, the pump housing 2 is provided with a positioning groove for axial and radial positioning of the flow-limiting nozzle 4. The bottom of the positioning groove has an opening communicating with the flow channel 3. The flow-limiting nozzle 4 includes a head section and a tail section. The tail section is engaged in the positioning groove. A through hole is provided in the tail section. The flow-limiting hole is located in the head section. The flow-limiting hole, the through hole, the opening, and the flow channel 3 are sequentially connected. The flow-limiting nozzle 4 is connected to the end of the flow channel 3 away from the bearing 1. Exemplarily, the flow channel 3 includes a direct flow section and a diagonal flow section. The direct flow section and the diagonal flow section are connected. The tail section is connected to the direct flow section. One end of the diagonal flow section faces the bearing 1. The propellant flows to the bearing 1 sequentially through the direct flow section and the diagonal flow section for cooling. Exemplarily, the diameter of the through hole is equal to the diameter of the direct flow section. The bottom of the positioning groove can restrict the axial movement of the flow-limiting nozzle 4. The groove wall of the positioning groove and the restriction of the radial movement of the flow-limiting nozzle 4 allow the flow-limiting nozzle 4 to be positioned within the positioning groove. This structure, which positions the flow-limiting nozzle 4 using a positioning groove, makes the positioning of the flow-limiting nozzle 4 more stable.

[0035] like Figure 1 As shown, further, an annular protrusion extends outward along its radial direction on the first section, and a first limiting groove is provided on the pump housing 2. The annular protrusion engages within the first limiting groove to restrict the axial movement of the flow-limiting nozzle 4 toward the flow channel 3. This structure, with the annular protrusion and the first limiting groove mutually limiting each other, further improves the stability of the flow-limiting nozzle 4, preventing propellant leakage due to nozzle deviation, and also improves the sealing performance between the flow-limiting nozzle 4 and the pump housing 2.

[0036] In some alternative configurations, the bearing cooling structure further includes a baffle 6, which is detachably connected to the pump housing 2 and presses against the end face of the first section away from the tail section to restrict the axial movement of the flow-limiting nozzle 4 away from the flow channel 3. A second limiting groove is provided on the pump housing 2, and the baffle 6 is engaged in the second limiting groove. With this structure, one end of the flow-limiting nozzle 4 is positioned by the positioning groove along the axial direction, and the other end is positioned by the baffle 6, so that the flow-limiting nozzle 4 can be installed and fixed on the pump housing 2, while further improving the sealing performance between the flow-limiting nozzle 4 and the pump housing 2.

[0037] like Figure 1 As shown, the bearing cooling structure further includes a sealing ring 5, which is disposed between the first section and the pump housing 2, and the sealing ring 5 is clearance-fitted with both the first section and the pump housing 2. For example, a sealing groove is provided on the outer side of the first section of the flow-limiting nozzle 4, and the sealing ring 5 is disposed within the sealing groove. With this structure, the pump housing 2 and the first section of the flow-limiting nozzle 4 are sealed by the sealing ring 5, which further improves the sealing performance between the flow-limiting nozzle 4 and the pump housing 2, prevents propellant leakage, and improves the stability of the flow-limiting nozzle 4.

[0038] like Figure 1 As shown, the bearing cooling structure further includes a floating ring 7, which is sleeved on the outside of the centrifugal wheel 9. The end face of the floating ring 7 abuts against the end face of the baffle 6 to achieve an end face seal. For example, the floating ring 7 rotates coaxially with the centrifugal wheel 9, and sealing the centrifugal wheel 9 with the floating ring 7 improves the sealing performance of the turbopump. For example, the end face of the baffle 6 and the end face of the flow-limiting nozzle 4 are located on the same plane. The floating ring 7 includes an annular protrusion extending towards the baffle 6, and the end face of the annular protrusion abuts against the end face of the baffle 6 to achieve an end face seal. With this structure, the end face seal between the floating ring 7 and the baffle 6 improves the sealing performance of the turbopump.

[0039] like Figure 1 As shown, the bearing cooling structure further includes a limiting nut 8, which is sleeved on the outside of the floating ring 7 and connected to the pump housing 2. A gap exists between the floating ring 7 and the limiting nut 8 to form a flow path for propellant flow, and this flow path communicates with the flow-limiting orifice. For example, the limiting nut 8 is an annular structure, and the pump housing 2 includes an annular positioning plate extending along the axis of rotation. The limiting nut 8 presses against the end face of the baffle 6. For example, the limiting nut 8 includes an annular plate coaxial with the rotating shaft and a positioning plate extending radially along the annular plate, with the positioning plate connected to the annular plate. With this structure, when the centrifugal wheel 9 drives the floating ring 7 to rotate, it can drive the propellant from the flow path between the floating ring 7 and the limiting nut 8 into the flow-limiting orifice of the flow-limiting nozzle 4, optimizing the propellant flow path and facilitating the propellant to flow into the flow-limiting nozzle 4 and through the flow channel 3 to the bearing 1 for cooling.

[0040] When the bearing 1 is cooled, the centrifugal wheel 9 rotates and draws out a high-pressure propellant from its outlet. The propellant overcomes the resistance in the internal return path of the centrifugal pump and flows from the flow path between the floating ring 7 and the limiting nut 8 to the flow limiting orifice of the flow limiting nozzle 4. Then it flows through the flow limiting orifice to the flow channel 3 of the pump housing 2, and then through the flow channel 3 to the bearing 1 to cool the bearing 1.

[0041] In some embodiments, the bearing cooling structure further includes a threaded fastener. The limiting nut 8 has a through hole, and the pump housing 2 has a threaded hole. The threaded fastener passes through the through hole and is threadedly connected to the threaded hole. For example, the threaded fastener is a screw. The positioning plate of the limiting nut 8 has a through hole, and the screw passes through the through hole and is threadedly connected to the threaded hole of the pump housing 2. This structure, by further securing the limiting nut 8 with the threaded fastener, improves the connection reliability of the limiting nut 8 and prevents it from loosening.

[0042] In some alternative configurations, multiple flow-limiting nozzles 4 are provided, with the orifice diameters of the flow-limiting nozzles 4 increasing sequentially. With this structure, when it is necessary to adjust the propellant flow rate, the flow-limiting nozzles 4 can be replaced with those having different orifice diameters, making flow rate adjustment of the flow-limiting nozzles 4 more convenient.

[0043] This invention also provides a turbopump, including a bearing cooling structure for the turbopump as provided in the above embodiments.

[0044] With the above technical solution, the bearing cooling structure includes a rotating shaft, a centrifugal wheel 9, a bearing 1, a pump housing 2, and a flow-limiting nozzle 4. The pump housing 2 has a flow channel 3 for propellant flow, with both ends of the flow channel 3 facing the centrifugal wheel 9 and the bearing 1, respectively. The flow-limiting nozzle 4 is detachably connected to the pump housing 2 and communicates with the flow channel 3. The propellant flows to the bearing 1 through the flow-limiting nozzle 4 and the flow channel 3. The flow-limiting nozzle 4 has a flow-limiting orifice, the diameter of which is smaller than the diameter of the flow channel 3. Using this structure, the flow rate of the propellant can be limited by the flow-limiting orifice of the flow-limiting nozzle 4. By controlling the orifice diameter, the flow rate of the propellant delivered to the bearing 1 can be adjusted. When the propellant flow rate is too high, a flow-limiting nozzle 4 with a small-diameter orifice can be used; when the propellant flow rate is too low, a flow-limiting nozzle 4 with a large-diameter orifice can be used. By using flow-limiting nozzles 4 with different sized orifices, the flow rate of the propellant delivered to the bearing 1 can be adjusted, thereby improving the performance and service life of the bearing 1, and consequently, extending the service life of the turbopump. Furthermore, when it is necessary to change the propellant flow rate, it can be done by replacing the flow-limiting nozzle 4 with one of different orifice diameters without changing other parts, thus making it easier to adjust the propellant flow rate.

[0045] In the description of the above embodiments, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0046] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A bearing cooling structure for a turbopump, characterized by, The device includes a rotating shaft, a centrifugal wheel, a bearing, and a pump housing. The bearing and the centrifugal wheel are sequentially mounted on the rotating shaft along its axial direction. The pump housing surrounds the centrifugal wheel and the bearing. The rotating shaft and the pump housing are rotatably connected by the bearing. The pump housing is provided with a flow channel for the propellant to flow through. The two ends of the flow channel are respectively facing the centrifugal wheel and the bearing. The bearing cooling structure also includes a flow-limiting nozzle for limiting the flow rate of the propellant. The flow-limiting nozzle is detachably connected to the pump housing and communicates with the flow channel. The propellant flows to the bearing through the flow-limiting nozzle and the flow channel. The flow-limiting nozzle is provided with a flow-limiting orifice, the diameter of which is smaller than the diameter of the flow channel. The pump housing is provided with a positioning groove for axial and radial positioning of the flow limiting nozzle, and the bottom of the positioning groove is provided with an opening that communicates with the flow channel. The flow-limiting nozzle includes a first section and a last section. The last section is snapped into the positioning groove. A through hole is provided in the last section. The flow-limiting hole is located in the first section. The flow-limiting hole, the through hole, the opening, and the flow channel are connected in sequence. The flow-limiting nozzle is connected to the end of the flow channel furthest from the bearing; The first section has an annular protrusion extending outward along its radial direction. A first limiting groove is provided on the pump housing. The annular protrusion is engaged in the first limiting groove to restrict the axial movement of the flow-limiting nozzle toward the flow channel side.

2. The bearing cooling structure for a turbo pump according to claim 1, characterized by, It also includes a baffle plate, which is detachably connected to the pump housing and presses against the end face of the first section away from the tail section to restrict the axial movement of the flow-limiting nozzle away from the flow channel; The pump housing is provided with a second limiting groove, and the baffle is engaged in the second limiting groove.

3. The bearing cooling structure for a turbopump according to claim 2, characterized in that, It also includes a sealing ring, which is disposed between the first section and the pump housing.

4. The bearing cooling structure for a turbopump according to claim 2, characterized in that, It also includes a floating ring, which is sleeved on the outside of the centrifugal wheel, and the end face of the floating ring abuts against the end face of the baffle to achieve end face sealing.

5. The bearing cooling structure for a turbopump according to claim 4, characterized in that, It also includes a limiting nut, which is sleeved on the outside of the floating ring and connected to the pump housing. There is a gap between the floating ring and the limiting nut to form a flow path for the propellant to flow through, and the flow path is connected to the flow-limiting orifice.

6. The bearing cooling structure for a turbopump according to claim 5, characterized in that, It also includes threaded fasteners, wherein the limiting nut is provided with a through hole and the pump housing is provided with a threaded hole, and the threaded fastener passes through the through hole and is threadedly connected to the threaded hole.

7. The bearing cooling structure for a turbopump according to claim 1, characterized in that, The flow-limiting nozzles are provided in multiple ways, and the diameter of the flow-limiting orifices in the multiple flow-limiting nozzles increases sequentially.

8. A turbopump, characterized in that, Includes the bearing cooling structure for a turbopump as described in any one of claims 1-7.

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