CN116576158A - Bearing cooling structure for turbine pump and turbine pump - Google Patents

Abstract

The invention discloses a bearing cooling structure for a turbo pump and the turbo pump, which relate to the technical field of aerospace engines and solve the problem that the performance and service life of the bearing itself are affected when the propellant is too little or too much. The bearing cooling structure for a turbo pump includes a rotating shaft, a centrifugal wheel, a bearing, a pump housing and a flow-limiting nozzle. The bearing and the centrifugal wheel are sequentially installed on the rotating shaft along the axial direction of the rotating shaft, and the pump housing is surrounded by the centrifugal wheel and the On the outer side of the bearing, the pump casing is provided with a flow channel for circulating the propellant. The two ends of the flow channel face the centrifugal wheel and the bearing respectively. The flow nozzle and the flow channel flow to the bearing; the flow limiting nozzle is provided with a flow limiting hole, and the aperture of the flow limiting hole is smaller than the hole diameter of the flow channel. The turbo pump includes the bearing cooling structure for the turbo pump mentioned in the solution above.

Description

Bearing cooling structure for turbopump and turbopump

technical field

The invention relates to the technical field of aerospace engines, in particular to a bearing cooling structure for a turbopump and the turbopump.

Background technique

The liquid rocket engine is a chemical rocket engine using liquid propellant. The liquid rocket engine includes a turbopump used to pressurize the propellant. Propellant, the propellant is burned in the thrust chamber to form high-pressure and high-temperature gas, which is sprayed out through the nozzle to reversely propel the liquid rocket engine to achieve flight.

Generally, a turbo pump is composed of a centrifugal pump and a turbine. The turbine is used to output energy. The centrifugal pump relies on the energy output by the turbine to deliver a propellant with a certain pressure and flow rate. Since the centrifugal pump is in a high-speed rotating state, it needs to be supported by bearings. .

When the centrifugal pump is working, the bearing not only needs to bear the axial force and radial force from the centrifugal pump, but also needs to bear the vibration of the turbo pump, which will cause a lot of heat to be generated when the bearing is working, so the bearing needs to be cooled. Usually, A flow channel is arranged in the pump casing, and the propellant in the turbo pump passes through the flow channel to cool the bearing, so as to reduce the temperature of the bearing itself. However, when this structure is adopted, the propellant flow rate delivered to the bearing cannot be controlled. When the propellant is too small, the heat generated by the friction of the bearing cannot be taken away in time, which reduces the cooling effect of the bearing; when the propellant is too much, the increase It reduces the lubrication effect of the bearing, increases the performance loss of the bearing, and then affects the performance and service life of the bearing itself.

Contents of the invention

The object of the present invention is to provide a bearing cooling structure for a turbopump and the turbopump, so as to adjust the propellant flow delivered to the bearing and improve the performance and service life of the bearing itself.

In order to achieve the above object, in the first aspect, the present invention provides a bearing cooling structure for a turbo pump including a rotating shaft, a centrifugal wheel, a bearing and a pump casing, the bearing and the centrifugal wheel are sequentially installed on the rotating shaft along the axial direction of the rotating shaft, and the pump The casing is surrounded by the centrifugal wheel and the bearing, and the shaft and the pump casing are connected through the rotation of the bearing;

The pump casing is provided with flow passages for propellant circulation, and the two ends of the flow passages face the centrifugal wheel and the bearing respectively. The bearing cooling structure also includes a flow-limiting nozzle for restricting the flow of propellant. The flow-limiting nozzle and the pump casing can be Disassemble the connection and communicate with the flow channel, and the propellant flows to the bearing through the flow-limiting nozzle and the flow channel;

A flow-limiting hole is arranged in the flow-limiting nozzle, and the aperture of the flow-limiting hole is smaller than the aperture of the flow channel.

In the case of adopting the above technical solution, the bearing cooling structure includes a rotating shaft, a centrifugal wheel, a bearing, a pump housing and a flow-limiting nozzle. The pump housing is provided with a flow channel for circulating propellant, and the two ends of the flow channel are respectively facing the centrifugal wheel. and the bearing, the flow-limiting nozzle is detachably connected with the pump casing and communicated 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 hole, and the diameter of the flow-limiting hole is smaller than that of the flow channel aperture. With this structure, the flow rate of propellant can be restricted through the flow restriction hole of the flow restriction nozzle, and the flow rate of propellant delivered to the bearing can be adjusted by controlling the diameter of the flow restriction hole. When the flow rate of propellant is too large, a Flow-limiting nozzles with flow-restricting holes. When the flow rate of propellant is too small, flow-limiting nozzles with large-diameter flow-limiting holes can be used. By using flow-limiting nozzles with flow-limiting holes of different sizes, the propellant delivered to the bearing can be adjusted. flow, thereby improving the bearing's own performance and service life, thereby increasing the service life of the turbo pump.

In some possible implementations, the pump casing is provided with a positioning groove for axially and radially positioning the flow-limiting nozzle, and the bottom of the positioning groove is provided with an opening communicating with the flow channel;

The flow-limiting nozzle includes a first section and a tail section, the tail section is clamped in the positioning groove, and a through hole is arranged in the tail section, the flow-limiting hole is located in the first section, and the flow-limiting hole, the through hole, the opening and the flow channel are connected in sequence;

The flow-limiting nozzle communicates with the end of the flow channel away from the bearing.

In some possible implementations, an annular protrusion is formed on the first section extending outward along its radial direction, and a first limiting groove is provided on the pump casing, and the annular protrusion is snapped into the first limiting groove, so as to Restricts the axial movement of the restrictor nozzle toward the flow path.

In some possible implementations, it also includes a baffle, which is detachably connected to the pump housing and presses against the end surface of the first section away from the tail section, so as to limit the axial movement of the flow-restricting nozzle away from the flow channel;

A second limiting groove is arranged on the pump casing, and the baffle plate is clamped in the second limiting groove.

In some possible implementation manners, a sealing ring is also included, and the sealing ring is arranged between the first section and the pump housing.

In some possible implementation manners, a floating ring is further included, and the floating ring is sleeved on the outside of the centrifugal wheel, and the end surface of the floating ring is in contact with the end surface of the baffle to realize end surface sealing.

In some possible implementations, a limit nut is also included, the limit nut is sleeved on the outside of the floating ring and connected to the pump housing, and there is a gap between the floating ring and the limit nut to form a flow path for propellant circulation , the flow path communicates with the restrictor hole.

In some possible implementation manners, a threaded fastener is further included, the limit nut is provided with a through hole, the pump casing is provided with a threaded hole, and the threaded fastener passes through the through hole and is threadedly connected with the threaded hole.

In some possible implementation manners, there are multiple flow-limiting nozzles, and the diameters of the flow-limiting holes in the multiple flow-limiting nozzles increase sequentially.

In a second aspect, the present invention also provides a turbo pump, including the bearing cooling structure for a turbo pump provided in any one of the above solutions.

In the case of adopting the above technical solution, since the turbo pump adopts the bearing cooling structure for the turbo pump of the present application, the flow of propellant delivered to the bearing can be adjusted, and the performance and service life of the bearing can be improved.

Description of drawings

The accompanying drawings described here are used to provide a further understanding of the present invention, and constitute a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention, and do not constitute improper limitations to the present invention. In the attached picture:

Fig. 1 is a schematic diagram of a bearing cooling structure in the present invention.

Reference signs:

1-bearing, 2-pump casing, 3-flow channel, 4-limiting flow nozzle, 5-sealing ring, 6-baffle plate, 7-floating ring, 8-limit nut, 9-centrifugal wheel.

Detailed ways

In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

It should be noted that when an element is referred to as being “fixed” or “disposed on” another element, it may 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 indirectly connected to the other element.

In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be interpreted as indicating or implying relative importance or implicitly specifying the quantity of indicated technical features. Thus, a feature defined as "first" and "second" may explicitly or implicitly include one or more of these features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined. "Several" means one or more than one, unless otherwise clearly and specifically defined.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right" etc. are based on those shown in the accompanying drawings. Orientation or positional relationship is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention.

In the description of the present invention, it should be noted that unless otherwise specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection or a detachable connection. Connection, or integral connection; can be mechanical connection or electrical connection; can be direct connection or indirect connection through an intermediary, and can be the internal communication of two elements or the interaction relationship between two elements. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention according to specific situations.

Please refer to Fig. 1, an embodiment of the present invention provides a bearing cooling structure for a turbo pump including a rotating shaft, a centrifugal wheel 9, a bearing 1 and a pump housing 2, and the bearing 1 and the centrifugal wheel 9 are sequentially installed on the rotating shaft along the axial direction of the rotating shaft Above, the pump housing 2 is surrounded by the centrifugal wheel 9 and the outer side of the bearing 1, and the rotating shaft and the pump housing 2 are rotationally connected by the bearing 1; The two ends of the pump are respectively facing the centrifugal wheel 9 and the bearing 1. The bearing cooling structure also includes a flow-limiting nozzle 4 for limiting the flow rate of the propellant. The flow-limiting nozzle 4 is detachably connected to the pump housing 2 and communicated with the flow channel 3. The agent 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 hole, and the diameter of the flow-limiting hole is smaller than the hole diameter of the flow channel 3.

In the case of adopting 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, and the pump housing 2 is provided with a flow channel 3 for circulating propellant, and the flow channel 3 The two ends of the pump face the centrifugal wheel 9 and the bearing 1 respectively, the flow-limiting nozzle 4 is detachably connected with the pump casing 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, and the flow-limiting nozzle 4 is provided with a flow-limiting hole, and the diameter of the flow-limiting hole is smaller than that of the flow channel 3 . With this structure, the propellant flow rate can be restricted through the flow restriction hole of the flow restriction nozzle 4, and the propellant flow rate delivered to the bearing 1 can be adjusted by controlling the diameter of the flow restriction hole. When the propellant flow rate is too large, a The flow-limiting nozzle 4 of the small-diameter flow-limiting hole, when the flow rate of the propellant is too small, the flow-limiting nozzle 4 with the large-diameter flow-limiting hole can be used, and the delivery can be adjusted by using the flow-limiting nozzle 4 with different sizes of flow-limiting holes. The flow of propellant to the bearing 1 is improved, thereby improving the performance and service life of the bearing 1, thereby increasing the service life of the turbo pump. In addition, when it is necessary to change the flow rate of the propellant, it is sufficient to replace the flow-limiting nozzle 4 with a different aperture without changing other parts, so it is more convenient to adjust the flow rate of the propellant.

In some embodiments, the pump casing 2 is provided with a positioning groove for axially and radially positioning the flow-limiting nozzle 4, and the bottom of the positioning groove is provided with an opening communicating with the flow channel 3; the flow-limiting nozzle 4. It includes the first section and the tail section. The tail section is clamped in the positioning groove. A through hole is arranged in the tail section. The flow limiting hole is located in the first section. The nozzle 4 communicates with the end of the flow channel 3 away from the bearing 1 . Exemplarily, the flow channel 3 includes a straight part and an oblique part, the straight part and the oblique part are connected, the tail section is connected with the straight part, one end of the oblique part faces the bearing 1, and the propellant passes through the straight part and the oblique flow in sequence part of the flow to the bearing 1 for cooling. Exemplarily, the aperture of the through hole is equal to the aperture of the straight section, the axial movement of the restrictor nozzle 4 can be restricted by the groove bottom of the positioning groove, and the radial movement of the restrictor nozzle 4 can be restricted by the groove wall of the positioning groove, so that The flow-restricting nozzle 4 can be positioned in the positioning groove. With this structure, the flow-limiting nozzle 4 is positioned through the positioning groove, so that the positioning of the flow-limiting nozzle 4 can be made more stable.

As shown in Figure 1, further, the first section extends outward along its radial direction to form an annular protrusion, and the pump housing 2 is provided with a first limiting groove, and the annular protrusion is snapped into the first limiting groove , to limit the axial movement of the restrictor nozzle 4 toward the flow channel 3 . By adopting this structure, the stability of the flow-limiting nozzle 4 can be further improved through the mutual limitation of the annular protrusion and the first limiting groove, so as to avoid the propellant leakage caused by the deviation of the flow-limiting nozzle 4 and improve the stability of the flow-limiting nozzle. 4 and the sealing performance between the pump housing 2.

In some optional ways, the bearing cooling structure also includes a baffle 6, which is detachably connected to the pump housing 2, and presses against the end surface of the first section away from the tail section to limit the movement of the flow-limiting nozzle 4 away from the flow path. Axial movement in 3 directions; the pump casing 2 is provided with a second limiting groove, and the baffle plate 6 is clamped in the second limiting groove. With this structure, one end of the flow-limiting nozzle 4 along 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 installed and fixed on the pump housing 2, and at the same time, the flow-limiting nozzle 4 can be further improved. The sealing performance between the nozzle 4 and the pump housing 2.

As shown in FIG. 1 , further, the bearing cooling structure further includes a sealing ring 5 , which is arranged between the first section and the pump housing 2 , and the sealing ring 5 is in clearance fit with the first section and the pump housing 2 at the same time. Exemplarily, a sealing groove is provided on the outside of the first section of the flow-limiting nozzle 4, and the sealing ring 5 is arranged in the sealing groove. With this structure, the sealing ring 5 is used to seal between the pump casing 2 and the first section of the flow-limiting nozzle 4, which can further improve the sealing performance between the flow-limiting nozzle 4 and the pump casing 2, and prevent propellant from leaking. Improve the stability of the restrictor nozzle 4.

As shown in FIG. 1 , further, the bearing cooling structure further includes a floating ring 7 sleeved on the outside of the centrifugal wheel 9 , and the end surface of the floating ring 7 abuts against the end surface of the baffle plate 6 to realize end surface sealing. Exemplarily, the floating ring 7 rotates coaxially with the centrifugal wheel 9, and the centrifugal wheel 9 is sealed by the floating ring 7, which can improve the sealing performance of the turbo pump. Exemplarily, the end surface of the baffle plate 6 is located on the same plane as the end surface of the restrictor nozzle 4 , the floating ring 7 includes an annular protrusion extending toward the baffle plate 6 , and the end surface of the annular protrusion abuts against the end surface of the baffle plate 6 To achieve end face sealing. With this structure, the end face between the floating ring 7 and the baffle plate 6 is sealed, which can improve the sealing performance of the turbo pump.

As shown in Figure 1, further, the bearing cooling structure also includes a limit nut 8, which is sleeved on the outside of the floating ring 7 and connected to the pump housing 2, and there is a gap between the floating ring 7 and the limit nut 8 To form a flow path for propellant circulation, the flow path communicates with the flow-restricting hole. Exemplarily, the limit nut 8 has an annular structure, the pump housing 2 includes an annular positioning plate extending along the axis of the rotating shaft, and the limit nut 8 presses against the end surface of the baffle plate 6 . Exemplarily, the limit nut 8 includes an annular plate coaxially arranged with the rotating shaft and a positioning plate extending along the radial direction of the annular plate, and the positioning plate is connected with the annular plate. With this structure, when the centrifugal wheel 9 drives the floating ring 7 to rotate, it can drive the propellant to flow from the flow path between the floating ring 7 and the stop nut 8 into the flow-limiting hole of the flow-limiting nozzle 4, optimizing the flow path of the propellant , so that the propellant flows into the flow-limiting nozzle 4 and flows to the bearing 1 through the flow channel 3 for cooling.

Wherein, when the bearing 1 is cooled, the centrifugal wheel 9 rotates and draws out a stream of high-pressure propellant from its outlet. The flow flows into the restrictor hole of the restrictor nozzle 4 , then flows through the restrictor hole to the flow channel 3 of the pump housing 2 , and then flows to the bearing 1 through the flow channel 3 to cool the bearing 1 .

In some embodiments, the bearing cooling structure further includes a threaded fastener, the limit nut 8 is provided with a through hole, the pump casing 2 is provided with a threaded hole, and the threaded fastener passes through the through hole and is threadedly connected with the threaded hole. Exemplarily, the threaded fastener is a screw, and a through hole is provided on the positioning plate of the limit nut 8 , and the screw passes through the through hole and is threadedly connected with the threaded hole of the pump housing 2 . With this structure, the limit nut 8 is further fixed by threaded fasteners, which can improve the connection reliability of the limit nut 8 and prevent the limit nut 8 from loosening.

In some optional manners, there are multiple flow-limiting nozzles 4 , and the diameters of the flow-limiting holes in the multiple flow-limiting nozzles 4 increase sequentially. With this structure, when the flow rate of the propellant needs to be adjusted, it is sufficient to replace the flow-limiting nozzle 4 with flow-limiting holes of different diameters, which makes the flow adjustment of the flow-limiting nozzle 4 more convenient.

An embodiment of the present invention also provides a turbo pump, including the bearing cooling structure for the turbo pump provided in the above embodiments.

In the case of adopting 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, and the pump housing 2 is provided with a flow channel 3 for circulating propellant, and the flow channel 3 The two ends of the pump face the centrifugal wheel 9 and the bearing 1 respectively, the flow-limiting nozzle 4 is detachably connected with the pump casing 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, and the flow-limiting nozzle 4 is provided with a flow-limiting hole, and the diameter of the flow-limiting hole is smaller than that of the flow channel 3 . With this structure, the propellant flow rate can be restricted through the flow restriction hole of the flow restriction nozzle 4, and the propellant flow rate delivered to the bearing 1 can be adjusted by controlling the diameter of the flow restriction hole. When the propellant flow rate is too large, a The flow-limiting nozzle 4 of the small-diameter flow-limiting hole, when the flow rate of the propellant is too small, the flow-limiting nozzle 4 with the large-diameter flow-limiting hole can be used, and the delivery can be adjusted by using the flow-limiting nozzle 4 with different sizes of flow-limiting holes. The flow of propellant to the bearing 1 is improved, thereby improving the performance and service life of the bearing 1, thereby increasing the service life of the turbo pump. In addition, when it is necessary to change the flow rate of the propellant, it is sufficient to replace the flow-limiting nozzle 4 with a different aperture without changing other parts, so it is more convenient to adjust the flow rate of the propellant.

In the description of the above embodiments, specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in an appropriate manner.

The above is only a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Anyone skilled in the art can easily think of changes or substitutions within the technical scope disclosed in the present invention. Should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by 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.