A combined seal structure and liquid rocket engine for a turbopump

Abstract

The application discloses a combined sealing structure for a turbine pump and a liquid rocket engine, and relates to the technical field of liquid rocket engines, and aims to solve the problem of poor sealing effect of the dynamic sealing device of the existing turbine pump. The combined sealing structure for the turbine pump comprises a first-stage liquid sealing wheel and a second-stage liquid sealing wheel for being installed on a rotor, the first-stage liquid sealing wheel and the second-stage liquid sealing wheel are sequentially arranged along the axial direction of the rotor, the first-stage liquid sealing wheel, the second-stage liquid sealing wheel and the rotor synchronously rotate, and the first-stage liquid sealing wheel and the second-stage liquid sealing wheel are used for liquid sealing of the turbine pump. The liquid rocket engine comprises the combined sealing structure for the turbine pump.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of liquid rocket engine, and particularly relates to a combined sealing structure for a turbine pump and a liquid rocket engine. BACKGROUND

[0002] The liquid rocket engine is a chemical rocket engine using liquid propellant, and generally comprises a turbine pump for pressurizing the propellant. The turbine pump needs to be dynamically sealed to ensure that two propellant media do not contact each other during normal operation of the turbine pump, thereby ensuring good engine performance.

[0003] The turbine pump in the existing liquid rocket engine generally adopts an end face sealing mode. The dynamic sealing device of the turbine pump comprises a dynamic ring and a static ring, and the end faces of the dynamic ring and the static ring are in contact to seal. With this structure, the end face sealing of the dynamic ring and the static ring can avoid the mutual contact of the two propellant media, but the sealing effect of this dynamic sealing device is poor, and the propellant is prone to leakage, which can cause the two propellant media to contact each other and cause combustion or explosion. SUMMARY

[0004] The present application aims to provide a combined sealing structure for a turbine pump and a liquid rocket engine to improve the sealing effect of the dynamic sealing in the turbine pump and avoid combustion or explosion caused by leakage of the propellant.

[0005] To achieve the above-mentioned purpose, in a first aspect, the present application provides a combined sealing structure for a turbine pump, comprising a primary liquid seal wheel and a secondary liquid seal wheel for being installed on a rotor. The primary liquid seal wheel and the secondary liquid seal wheel are arranged in sequence along the axial direction of the rotor, and the primary liquid seal wheel, the secondary liquid seal wheel and the rotor rotate synchronously. The primary liquid seal wheel and the secondary liquid seal wheel are both used for liquid sealing of the turbine pump.

[0006] In the technical scheme, the first-stage liquid seal wheel and the second-stage liquid seal wheel are sequentially arranged on the rotor along the axial direction of the rotor, and the first-stage liquid seal wheel, the second-stage liquid seal wheel and the rotor rotate synchronously, and the first-stage liquid seal wheel and the second-stage liquid seal wheel are used for liquid sealing of the turbine pump. With the structure, firstly, the rotor can drive the first-stage liquid seal wheel and the second-stage liquid seal wheel to rotate synchronously when the rotor rotates, and the first-stage liquid seal wheel and the second-stage liquid seal wheel can drive the liquid in the turbine pump cavity to be thrown out along the radial direction when the first-stage liquid seal wheel and the second-stage liquid seal wheel rotate, thereby liquid sealing of the turbine pump is realized, the sealing effect of the dynamic seal in the turbine pump is improved, and combustion or explosion caused by leakage of the propellant is avoided; secondly, the first-stage liquid seal wheel can seal the nitrogen tetroxide medium at the inlet of the oxidant pump, and when the liquid sealing of the first-stage liquid seal wheel leaks, the second-stage liquid seal wheel can further throttle and depressurize the leaked medium to realize sealing, the sealing effect of the dynamic seal in the turbine pump is further improved through the two-stage liquid sealing structure, combustion or explosion caused by leakage of the propellant is avoided, and the combined sealing structure can meet the sealing performance requirements of high pressure, high linear velocity, high stability and zero leakage.

[0007] In some possible implementation manners, the static ring assembly further includes a graphite ring, a static ring seat, an anti-rotation pin, a spring, a spring seat and a static ring shell;

[0008] The graphite ring is sealed with the end face of the first-stage liquid seal wheel, the static ring seat is used for pressing the graphite ring against the end face of the first-stage liquid seal wheel, the spring seat is arranged between the static ring shell and the static ring seat, and the spring is arranged between the static ring seat and the spring seat;

[0009] The spring seat is provided with a pin hole, the static ring seat is provided with an anti-rotation hole, one end of the anti-rotation pin is inserted into the pin hole, and the other end of the anti-rotation pin is inserted into the anti-rotation hole.

[0010] In some possible implementation manners, the static ring assembly further includes a first sealing ring, the static ring shell, the static ring seat and the spring seat jointly form a first annular clamping groove, the first sealing ring is arranged in the first annular clamping groove, and the first sealing ring is in interference fit with the static ring seat and the static ring shell.

[0011] In some possible implementation manners, the first sealing ring is a C-shaped sealing ring, a side of the C-shaped sealing ring close to the spring seat is provided with a groove, the spring seat is provided with a protrusion extending into the groove, and the protrusion is provided with a through hole extending along the radial direction of the rotor.

[0012] In some possible implementation manners, the static ring assembly further includes a second sealing ring, the static ring shell includes a convex ring extending towards the spring seat, the spring seat, the convex ring and the static ring shell jointly form a second annular clamping groove, the second annular clamping groove is open to a side of the spring seat away from the rotor along the radial direction of the rotor, the second sealing ring is arranged in the second annular clamping groove, and the second sealing ring is in interference fit with the spring seat and the static ring shell.

[0013] In some possible implementation manners, the turbine pump further comprises a first compression nut, the turbine pump comprises a first pump shell surrounding the first-stage liquid seal wheel and the second-stage liquid seal wheel, the first compression nut is threadedly connected with the first pump shell of the turbine pump, and the first compression nut is sleeved outside the static ring shell to compress the static ring shell.

[0014] In some possible implementation manners, the turbine pump further comprises a first compression nut, the turbine pump comprises a first pump shell surrounding the first-stage liquid seal wheel and the second-stage liquid seal wheel, the first compression nut is threadedly connected with the first pump shell of the turbine pump, and the first compression nut is sleeved outside the static ring shell to compress the static ring shell.

[0015] In some possible implementation manners, the turbine pump further comprises a third sealing ring, the first-stage liquid seal wheel is provided with a third annular clamping groove with an opening facing the rotor, the third sealing ring is arranged in the third annular clamping groove, and the third sealing ring is in interference fit with the first-stage liquid seal wheel and the rotor.

[0016] In some possible implementation manners, the turbine pump further comprises a second compression nut, the second compression nut is sleeved on the rotor and threadedly connected with the rotor, the rotor is provided with a shaft shoulder, the second compression nut is arranged on the second-stage liquid seal wheel and away from the first-stage liquid seal wheel, and the first-stage liquid seal wheel and the second-stage liquid seal wheel are axially positioned between the shaft shoulder and the second compression nut.

[0017] In some possible implementation manners, the turbine pump further comprises a second locking washer, the second locking washer is locked between the end surface of the second-stage liquid seal wheel and the second compression nut.

[0018] In some possible implementation manners, the turbine pump further comprises a fourth sealing ring, the turbine pump further comprises a second pump shell sleeved on the rotor, the second pump shell is located on the axial side of the second-stage liquid seal wheel away from the first-stage liquid seal wheel, the second pump shell and the rotor jointly form a fourth annular clamping groove, the fourth sealing ring is arranged in the fourth annular clamping groove, and the fourth sealing ring is in interference fit with the rotor and the second pump shell.

[0019] The fourth sealing ring is a lip-shaped sealing ring.

[0020] In some possible implementation manners, the turbine pump further comprises a clamping ring clamped on the rotor, the second pump shell comprises an annular baffle portion extending towards the rotor in the radial direction of the rotor, and the annular baffle portion and the clamping ring are respectively located on the two axial sides of the lip-shaped sealing ring to axially position the lip-shaped sealing ring.

[0021] In some possible implementation manners, the turbine pump further comprises an annular separation cover sleeved on the rotor, the lip-shaped sealing ring is provided with at least two lip-shaped sealing rings, the at least two lip-shaped sealing rings are sequentially arranged in the axial direction of the rotor, and the annular separation cover is arranged between adjacent two lip-shaped sealing rings.

[0022] In some possible implementation manners, the turbine pump further comprises a fifth sealing ring, the second pump shell is provided with a fifth annular clamping groove, the fifth annular clamping groove is open on the side away from the rotor in the radial direction of the rotor, and the fifth sealing ring is arranged in the fifth annular clamping groove.

[0023] In a second aspect, the present application further provides a liquid rocket engine comprising a turbine pump and the combined sealing structure for the turbine pump according to any one of the above solutions.

[0024] In the above technical solution, the liquid rocket engine comprises the combined sealing structure for the turbine pump according to the above solutions, so that the sealing effect of the dynamic seal in the turbine pump can be improved, and leakage of the propellant can be avoided to cause combustion or explosion. BRIEF DESCRIPTION OF DRAWINGS

[0025] The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:

[0026] Figure 1 Fig. 1 is a schematic view of the combined sealing structure according to the present application;

[0027] Figure 2 Fig. 2 is a schematic view of the static ring assembly according to the present application;

[0028] Figure 3 Fig. 3 is a schematic view of the primary liquid seal wheel according to the present application;

[0029] Figure 4 Fig. 4 is a schematic view of the secondary liquid seal wheel according to the present application;

[0030] Figure 5 Fig. 5 is a schematic view of the lip seal ring assembly according to the present application.

[0031] Reference Signs List:

[0032] 1 - rotor, 2 - primary liquid seal wheel, 3 - annular stress release groove, 4 - static ring seat, 5 - anti-rotation pin, 6 - second sealing ring, 7 - static ring housing, 8 - second locking washer, 9 - second compression nut, 10 - fifth sealing ring, 11 - second pump housing, 12 - third sealing ring, 13 - graphite ring, 14 - secondary liquid seal wheel, 15 - spring, 16 - spring seat, 17 - first sealing ring, 18 - first locking washer, 19 - first compression nut, 20 - first lip seal ring, 21 - annular partition cover, 22 - second lip seal ring, 23 - snap ring. DETAILED DESCRIPTION

[0033] In order to make the technical problems to be solved by the present application, the technical solutions and the beneficial effects more clearly understood, the present application 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 only used to explain the present application, and do not limit the present application.

[0034] It should be noted that when an element is referred to as being "fixed" or "set" on another element, it can be directly on the other element or 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.

[0035] In addition, the terms "first", "second", "third", etc. are used only for descriptive purposes and should not be construed as indicating or implying relative importance or an indicated number of technical features. Therefore, the features defined as "first", "second", etc. can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise explicitly specified and limited.

[0036] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", etc. indicate the orientation or positional relationship shown in the drawings, and are only for the 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 particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0037] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integral connection; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0038] Please refer to Figures 1 to 5 The embodiment of the present application provides a combined sealing structure for a turbine pump, which comprises a first liquid seal wheel 2 and a second liquid seal wheel 14 for being mounted on a rotor 1. The first liquid seal wheel 2 and the second liquid seal wheel 14 are arranged in sequence along the axial direction of the rotor 1, and the first liquid seal wheel 2, the second liquid seal wheel 14 and the rotor 1 rotate synchronously. The first liquid seal wheel 2 and the second liquid seal wheel 14 are both used for liquid sealing of the turbine pump.

[0039] In the technical scheme, the first liquid seal wheel 2 and the second liquid seal wheel 14 are sequentially arranged on the rotor 1 along the axial direction of the rotor 1, and the first liquid seal wheel 2, the second liquid seal wheel 14 and the rotor 1 rotate synchronously. The first liquid seal wheel 2 and the second liquid seal wheel 14 are used for liquid sealing of the turbine pump. With the structure, firstly, when the rotor 1 rotates, the first liquid seal wheel 2 and the second liquid seal wheel 14 can rotate synchronously, and when the first liquid seal wheel 2 and the second liquid seal wheel 14 rotate, the liquid in the turbine pump cavity can be thrown out along the radial direction, thereby liquid sealing of the turbine pump is realized, the sealing effect of the dynamic seal in the turbine pump is improved, and combustion or explosion caused by leakage of the propellant is avoided. Secondly, the first liquid seal wheel 2 can seal the dinitrogen tetroxide medium at the inlet of the oxidant pump. When the liquid sealing of the first liquid seal wheel 2 leaks, the second liquid seal wheel 14 can further throttle and depressurize the leaked medium to seal, the sealing effect of the dynamic seal in the turbine pump is further improved through the two-stage liquid sealing structure, combustion or explosion caused by leakage of the propellant is avoided, and the combined sealing structure can meet the sealing performance requirements of high pressure, high linear velocity, high stability, zero leakage and the like.

[0040] As Figures 1 to 3As shown, further, the combined sealing structure further comprises a static ring assembly, the static ring assembly comprising a graphite ring 13, a static ring seat 4, an anti-rotation pin 5, a spring 15, a spring seat 16 and a static ring housing 7; the graphite ring 13 is sealed with the end face of the primary liquid seal wheel 2, the static ring seat 4 is used to press the graphite ring 13 against the end face of the primary liquid seal wheel 2, the spring seat 16 is arranged between the static ring housing 7 and the static ring seat 4, and the spring 15 is arranged between the static ring seat 4 and the spring seat 16; the spring seat 16 is provided with a pin hole, the static ring seat 4 is provided with an anti-rotation hole, one end of the anti-rotation pin 5 is inserted into the pin hole, and the other end is inserted into the anti-rotation hole. As an example, the sealing end face of the primary liquid seal wheel 2 is provided with an annular stress release groove 3, and the stress is released through the annular stress release groove 3, so that the end face stress of the primary liquid seal wheel 2 during rotation can be avoided to be too large to damage the primary liquid seal wheel 2. As an example, the end face of the graphite ring 13 is in frictional contact with the end face of the primary liquid seal wheel 2, and the mating surface of the primary liquid seal wheel 2 and the graphite ring 13 needs to be ground to improve the sealing capacity, and the roughness of the ground mating surface needs to be less than or equal to 0.1 μm. As an example, the inner side of the static ring seat 4 is provided with an annular groove for process disassembly, the static ring seat 4 is provided with 7-15 through holes along the circumferential direction thereof, the through holes on the static ring seat 4 and the pin holes on the spring seat 16 have the same radial distance from the axis of the rotor 1, and the plurality of through holes on the static ring seat 4 and the plurality of pin holes are uniformly distributed along the circumferential direction of the static ring seat 4 to improve the stress load distribution of the static ring seat 4 and improve the strength and service life of the static ring seat 4. As an example, the spring seat 16 is further provided with a pin hole in communication with the pin hole, the diameter of the pin hole can be 0.8-1.4 mm, the spring 15 is provided in plurality, and the plurality of springs 15 are uniformly distributed in the spring 15 holes of the spring seat 16 along the circumferential direction of the rotor 1, and the number of the springs 15 can be 8-16. With this structure, the graphite ring 13 can realize dynamic sealing with the primary liquid seal wheel 2 under the elastic action of the spring 15; the end face sealing of the graphite ring 13 with the primary liquid seal wheel 2 through the spherical structure can further improve the sealing effect of the dynamic sealing in the turbine pump, and avoid leakage of the propellant to cause combustion or explosion; the static ring assembly can adapt to and compensate the deformation and deflection of the part structure and the shaft runout, and improve the stability and sealing property of the combined sealing structure as a whole.

[0041] As Figure 1 and Figure 2As shown, further, the combined sealing structure further comprises a first sealing ring 17, the static ring shell 7, the static ring seat 4 and the spring seat 16 jointly enclose a first annular clamping groove, the first sealing ring 17 is arranged in the first annular clamping groove, and the first sealing ring 17 is in interference fit with the static ring seat 4 and the static ring shell 7. As an example, the static ring shell 7 comprises an annular plate coaxially arranged with the rotor 1 and a baffle plate, one end of the baffle plate is connected with the annular plate, and the other end extends along the radial direction of the annular plate, an L-shaped groove can be enclosed between the baffle plate and the annular plate, the first sealing ring 17 is clamped in the L-shaped groove, and the two sides of the first sealing ring 17 along the radial direction are limited between the annular plate and the static ring seat 4, and the two sides of the first sealing ring 17 along the axial direction are limited between the spring seat 16 and the baffle plate. With this structure, the first sealing ring 17 is sealed between the static ring shell 7 and the static ring seat 4, which can prevent the propellant outside the static ring shell 7 from entering the inside of the static ring seat 4, thereby further improving the sealing effect of the dynamic seal in the turbine pump and avoiding combustion or explosion caused by leakage of the propellant.

[0042] In some embodiments, the first sealing ring 17 is a C-shaped sealing ring, one side of the C-shaped sealing ring close to the spring seat 16 has a groove, the spring seat 16 is provided with a protrusion extending into the groove, and the protrusion is provided with a perforation extending along the radial direction of the rotor 1. As an example, 4-6 perforations can be provided on the protrusion; the groove is a ring groove with a V-shaped cross section, the protrusion is a ring-shaped protrusion with a triangular cross section, and a gap exists between the protrusion and the groove. With this structure, the flow path is formed through the gap between the protrusion and the groove and the plurality of perforations, which can ensure smooth flow between the inner side and the outer side of the spring seat 16.

[0043] As shown in Figure 1 and Figure 2 , further, the combined sealing structure further comprises a second sealing ring 6, the static ring shell 7 comprises a convex ring extending towards the spring seat 16, the spring seat 16, the convex ring and the static ring shell 7 jointly enclose a second annular clamping groove, the second annular clamping groove is open to the side away from the rotor 1 along the radial direction of the rotor 1, the second sealing ring 6 is arranged in the second annular clamping groove, and the second sealing ring 6 is in interference fit with the spring seat 16 and the static ring shell 7. As an example, the second sealing ring 6 is an O-shaped sealing ring, the end surface of the spring seat 16, the outer ring surface of the convex ring and the end surface of the static ring shell 7 jointly enclose the second annular clamping groove. With this structure, the second sealing ring 6 seals between the inside and the outside of the static ring shell 7, which can prevent the propellant outside the static ring shell 7 from entering the inside of the static ring shell 7 and causing leakage, thereby further improving the sealing effect of the dynamic seal in the turbine pump and avoiding combustion or explosion caused by leakage of the propellant.

[0044] As shown in Figure 1As shown, further, the combined sealing structure further comprises a first compression nut 19, the turbine pump comprises a first pump shell surrounding the first liquid seal wheel 2 and the second liquid seal wheel 14 outside, the first compression nut 19 is threadedly connected with the first pump shell of the turbine pump, and the first compression nut 19 is sleeved outside the static ring shell 7 to compress the static ring shell 7. Illustratively, the first pump shell comprises an annular connecting plate extending in the radial direction, the inner side of the annular connecting plate is provided with an internal thread, and the outer surface of the first compression nut 19 is provided with an external thread, and the first compression nut 19 is threadedly connected with the annular connecting plate of the first pump shell through the internal thread and the external thread to realize locking. With this structure, the static ring shell 7 is locked by the first compression nut 19, which can prevent the static ring assembly from rotating circumferentially.

[0045] Illustratively, the combined sealing structure further comprises a first locking gasket 18 locked between the first compression nut 19 and the first pump shell. With this structure, the first compression nut 19 and the first pump shell are locked through the first locking gasket 18, which can prevent the connection between the first compression nut 19 and the first pump shell from loosening, thereby improving the stability of the connection between the first compression nut 19 and the first pump shell, and further improving the overall stability of the combined sealing structure.

[0046] As shown in Figure 1 and Figure 3 Further, the combined sealing structure further comprises a third sealing ring 12, the first liquid seal wheel 2 is provided with a third annular clamping groove with an opening facing the rotor 1, the third sealing ring 12 is arranged in the third annular clamping groove, and the third sealing ring 12 is in interference fit with the first liquid seal wheel 2 and the rotor 1. Illustratively, the third sealing ring 12 is an O-shaped sealing ring. With this structure, the first liquid seal wheel 2 and the rotor 1 are sealed by the third sealing ring 12, which can prevent the propellant from leaking from the gap between the first liquid seal wheel 2 and the rotor 1, thereby further improving the sealing effect of the dynamic seal in the turbine pump and avoiding combustion or explosion caused by leakage of the propellant.

[0047] As shown in Figure 1 and Figure 4As shown, further, the combined sealing structure further comprises a second compression nut 9, the second compression nut 9 is sleeved on the rotor 1 and is in threaded connection with the rotor 1, the rotor 1 is provided with a shaft shoulder, the second compression nut 9 is arranged on the two-stage liquid seal wheel 14 away from the one-stage liquid seal wheel 2, and the one-stage liquid seal wheel 2 and the two-stage liquid seal wheel 14 are axially positioned between the shaft shoulder and the second compression nut 9. Illustratively, the surface of the rotor 1 is provided with an outer nut, the inner surface of the second compression nut 9 is provided with an inner thread, and the second compression nut 9 is in threaded connection with the rotor 1 through the inner thread and the outer thread to realize locking. Illustratively, the end surface of the two-stage liquid seal wheel 14 away from the one-stage liquid seal wheel 2 is a groove surface, the groove surface comprises a plurality of grooves, the grooves are in rectangular or elliptical shape, and the number of the grooves can be 8-16. With this structure, the end surface of the one-stage liquid seal wheel 2 abuts against the shaft shoulder, the one-stage liquid seal wheel 2 and the two-stage liquid seal wheel 14 abut against each other in the axial direction, and the second compression nut 9 is in threaded connection with the rotor 1 to press the two-stage liquid seal wheel 14 against the end surface of the one-stage liquid seal wheel 2, so as to axially position the one-stage liquid seal wheel 2 and the two-stage liquid seal wheel 14.

[0048] Illustratively, the combined sealing structure further comprises a second locking washer 8, the second locking washer 8 is locked between the end surface of the two-stage liquid seal wheel 14 and the second compression nut 9. With this structure, the second compression nut 9 and the rotor 1 are locked through the second locking washer 8, which can prevent the connection between the second compression nut 9 and the rotor 1 from loosening, thereby improving the stability of the connection between the second compression nut 9 and the rotor 1, and further improving the overall stability of the combined sealing structure.

[0049] As shown in Figure 1 and Figure 5 As shown, further, the combined sealing structure further comprises a fourth sealing ring, and the turbine pump further comprises a second pump housing 11 sleeved on the rotor 1, the second pump housing 11 is located on the axial side of the two-stage liquid seal wheel 14 away from the one-stage liquid seal wheel 2, the second pump housing 11 and the rotor 1 jointly enclose a fourth annular clamping groove, the fourth sealing ring is arranged in the fourth annular clamping groove, and the fourth sealing ring is in interference fit with the rotor 1 and the second pump housing 11, and the fourth sealing ring is a lip-shaped sealing ring. With this structure, the second pump housing 11 and the rotor 1 are sealed through the lip-shaped sealing ring, which can prevent the liquid outside the second pump housing 11 from leaking through the gap between the second pump housing 11 and the rotor 1, thereby further improving the sealing effect of the dynamic seal in the turbine pump and avoiding combustion or explosion caused by leakage of propellant.

[0050] As shown in Figure 1 and Figure 5Further, the combined sealing structure further comprises a snap ring 23 which is snapped onto the rotor 1, and the second pump housing 11 comprises an annular baffle portion which extends along the radial direction of the rotor 1 and towards the rotor 1, and the annular baffle portion and the snap ring 23 are respectively located on the two axial sides of the lip-shaped sealing ring to axially position the lip-shaped sealing ring. With this structure, the lip-shaped sealing ring can be positioned between the annular baffle portion and the snap ring 23 in the axial direction, thereby improving the stability of the positioning of the lip-shaped sealing ring, and meanwhile, the lip-shaped sealing ring can be more conveniently disassembled and assembled.

[0051] In some optional modes, the combined sealing structure further comprises an annular separation cover 21 which is sleeved on the rotor 1, and the lip-shaped sealing ring is provided with at least two lip-shaped sealing rings which are sequentially arranged along the axial direction of the rotor 1, and the annular separation cover 21 is arranged between the adjacent two lip-shaped sealing rings. For example, the lip-shaped sealing ring is provided with two lip-shaped sealing rings which are a first lip-shaped sealing ring 20 and a second lip-shaped sealing ring 22, and the first lip-shaped sealing ring 20 and the second lip-shaped sealing ring 22 are sequentially arranged along the axial direction thereof, and the first lip-shaped sealing ring 20 and the second lip-shaped sealing ring 22 are separated and positioned by the annular separation cover 21, and the annular separation cover 21 comprises a main annular plate and two side annular plates, the main annular plate is sleeved on the rotor 1, and the two side annular plates are respectively located on the two axial sides of the main annular plate, and the two side annular plates are used for abutting against the first lip-shaped sealing ring 20 and the second lip-shaped sealing ring 22 respectively.

[0052] As shown in the figure, Figure 1 Further, the combined sealing structure further comprises a fifth sealing ring 10, and the second pump housing 11 is provided with a fifth annular snap groove which is open along the radial direction of the rotor 1 and away from the rotor 1, and the fifth sealing ring 10 is arranged in the fifth annular snap groove. For example, the fifth sealing ring 10 is an O-shaped sealing ring. With this structure, the fifth sealing ring 10 is used for sealing the connecting position between the second pump housing 11 and the first pump housing, thereby preventing the propellant from leaking from the gap between the second pump housing 11 and the first pump housing, so that the sealing effect of the dynamic seal in the turbine pump can be further improved, and the leakage of the propellant can be avoided to cause combustion or explosion.

[0053] The embodiment of the present application further provides a liquid rocket engine which comprises a turbine pump and the combined sealing structure for the turbine pump provided in the above embodiment, and the turbine pump comprises a rotor 1, a first pump housing and a second pump housing 11.

[0054] In the technical scheme, the first liquid seal wheel 2 and the second liquid seal wheel 14 are sequentially arranged on the rotor 1 along the axial direction of the rotor 1, and the first liquid seal wheel 2, the second liquid seal wheel 14 and the rotor 1 rotate synchronously, and the first liquid seal wheel 2 and the second liquid seal wheel 14 are used for liquid sealing of the turbine pump. With the structure, firstly, when the rotor 1 rotates, the first liquid seal wheel 2 and the second liquid seal wheel 14 can rotate synchronously, and when the first liquid seal wheel 2 and the second liquid seal wheel 14 rotate, the liquid in the turbine pump cavity can be thrown out along the radial direction, so as to seal the turbine pump, improve the sealing effect of the dynamic seal in the turbine pump, and avoid combustion or explosion caused by leakage of the propellant; secondly, the first liquid seal wheel 2 can seal the dinitrogen tetroxide medium at the inlet of the oxidant pump, and when the liquid seal of the first liquid seal wheel 2 leaks, the second liquid seal wheel 14 can further throttle and depressurize the leaked medium to seal, so as to further improve the sealing effect of the dynamic seal in the turbine pump, avoid combustion or explosion caused by leakage of the propellant, and make the combined sealing structure meet the sealing performance requirements of high pressure, high linear velocity, high stability and zero leakage.

[0055] In the description of the above-described embodiments, specific features, structures, materials or characteristics can be combined in any one or more embodiments or examples in a suitable manner.

[0056] The above describes only specific embodiments of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A combined seal structure for a turbopump, characterized in that, The application relates to a liquid seal structure for a turbine pump, which comprises a primary liquid seal wheel and a secondary liquid seal wheel for being mounted on a rotor, the primary liquid seal wheel and the secondary liquid seal wheel are sequentially arranged along the axial direction of the rotor, the primary liquid seal wheel and the secondary liquid seal wheel abut each other along the axial direction, the primary liquid seal wheel, the secondary liquid seal wheel and the rotor rotate synchronously, the primary liquid seal wheel and the secondary liquid seal wheel form a two-stage liquid seal structure, the secondary liquid seal wheel further throttles, depressurizes and seals the leaked medium, and the primary liquid seal wheel and the secondary liquid seal wheel are used for liquid sealing of the turbine pump. The application further comprises a static ring assembly, which comprises a graphite ring, a static ring seat, an anti-rotation pin, a spring, a spring seat and a static ring shell. The graphite ring is sealed with the end surface of the primary liquid seal wheel, the static ring seat is used for pressing the graphite ring against the end surface of the primary liquid seal wheel, the spring seat is arranged between the static ring shell and the static ring seat, and the spring is arranged between the static ring seat and the spring seat. A pin hole is arranged on the spring seat, an anti-rotation hole is arranged on the static ring seat, one end of the anti-rotation pin is inserted into the pin hole, and the other end of the anti-rotation pin is inserted into the anti-rotation hole. The application further comprises a first sealing ring, the static ring shell, the static ring seat and the spring seat jointly form a first annular clamping groove, the first sealing ring is arranged in the first annular clamping groove, and the first sealing ring is in interference fit with the static ring seat and the static ring shell; the first sealing ring is a C-shaped sealing ring, one side of the C-shaped sealing ring close to the spring seat is provided with a groove, the spring seat is provided with a protrusion extending into the groove, and the protrusion is provided with a through hole extending along the radial direction of the rotor.

2. The combined seal structure for a turbopump of claim 1, wherein, The application further comprises a second sealing ring, the static ring shell comprises a convex ring extending towards the spring seat, the spring seat, the convex ring and the static ring shell jointly form a second annular clamping groove, the second annular clamping groove is open to the side away from the rotor along the radial direction of the rotor, the second sealing ring is arranged in the second annular clamping groove, and the second sealing ring is in interference fit with the spring seat and the static ring shell.

3. The combination seal structure for a turbopump of claim 1, wherein, The application further comprises a first pressing nut, the turbine pump comprises a first pump shell arranged outside the primary liquid seal wheel and the secondary liquid seal wheel, the first pressing nut is in threaded connection with the first pump shell of the turbine pump, and the first pressing nut is sleeved outside the static ring shell to press the static ring shell.

4. The combination seal structure for a turbopump of claim 3, wherein, The application further comprises a first locking gasket, which is locked between the first pressing nut and the first pump shell.

5. The combination seal structure for a turbopump of claim 1, wherein, The application further comprises a third sealing ring, the primary liquid seal wheel is provided with a third annular clamping groove with an opening facing the rotor, the third sealing ring is arranged in the third annular clamping groove, and the third sealing ring is in interference fit with the primary liquid seal wheel and the rotor.

6. The combination seal structure for a turbopump of claim 1, wherein, The application further comprises a second pressing nut, the second pressing nut is sleeved on the rotor and is in threaded connection with the rotor, the rotor is provided with a shaft shoulder, the second pressing nut is arranged at the end of the secondary liquid seal wheel away from the primary liquid seal wheel, and the primary liquid seal wheel and the secondary liquid seal wheel are axially positioned between the shaft shoulder and the second pressing nut.

7. The combination seal structure for a turbopump of claim 6, wherein, The second locking gasket is locked between the end face of the secondary liquid seal wheel and the second compression nut.

8. The combination seal structure for a turbopump of claim 1, wherein, The turbine pump further comprises a second pump housing sleeved on the rotor, the second pump housing is located on the axial side of the secondary liquid seal wheel away from the primary liquid seal wheel, the second pump housing and the rotor jointly form a fourth annular clamping groove, and the fourth sealing ring is arranged in the fourth annular clamping groove and is in interference fit with the rotor and the second pump housing. The fourth sealing ring is a lip-shaped sealing ring.

9. The combination seal structure for a turbopump of claim 8, wherein, The second pump housing comprises an annular baffle part extending towards the rotor in the radial direction of the rotor, and the annular baffle part and the clamping ring are respectively located on the two axial sides of the lip-shaped sealing ring to axially position the lip-shaped sealing ring.

10. The combination seal structure for a turbopump of claim 9, wherein, The turbine pump further comprises an annular separation cover sleeved on the rotor, and the lip-shaped sealing ring is provided in at least two, the at least two lip-shaped sealing rings are sequentially arranged in the axial direction of the rotor, and the annular separation cover is arranged between adjacent two lip-shaped sealing rings.

11. The combination seal structure for a turbopump of claim 10, wherein, The second pump housing is provided with a fifth annular clamping groove, the fifth annular clamping groove is opened to the side away from the rotor in the radial direction of the rotor, and the fifth sealing ring is arranged in the fifth annular clamping groove.

12. A liquid rocket engine, characterized in that The turbine pump comprises a rotor, a first pump housing and a second pump housing.

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