A rocket engine turbopump mounting device

Abstract

This application relates to the field of liquid rocket engine technology and discloses a rocket engine turbopump fixing device, comprising: a connector, at least two connecting plates, a first telescopic rod, and a second telescopic rod. The connector has a notch adapted to avoid the turbopump and is adapted to connect to the rocket engine. The two connecting plates are adapted to be fixed to the turbopump, and the portions of the two connecting plates corresponding to the periphery of the notch are detachably connected. One end of the first telescopic rod is hinged to the connector, and the other end is adapted to connect to the turbopump. One end of the second telescopic rod is hinged to the connector, and the other end is adapted to connect to the turbopump. The first and second telescopic rods are located on opposite sides of the connecting plates along a first direction. This rocket engine turbopump fixing device discloses a solution to or improvement of the problems of complex assembly and disassembly and difficult positioning of turbopumps.

Description

Technical Field

[0001] This application relates to the field of liquid rocket engine technology, specifically to a rocket engine turbopump mounting device. Background Technology

[0002] The turbopump is a core component of a liquid rocket engine, and its mounting method directly affects the engine's operation and vibration characteristics, making it a key factor in engine reliability. With the booming development of the commercial space market and the increasing demands for rocket payloads, the reliable operation of the turbopump is becoming increasingly important.

[0003] In related technologies, a rod-type support structure is used to connect the turbopump and the rocket engine. However, the rod-type support structure lacks rigidity and has low load-bearing capacity, making it prone to resonance with the high-speed rotating turbopump. The turbopump generates high temperatures during operation, and the rod-type support structure experiences uneven thermal expansion under the huge temperature difference. Stress concentration occurs at the joints between the rods, leading to fatigue cracks. Furthermore, the multiple rods make disassembly and assembly complex and positioning difficult. Utility Model Content

[0004] In view of this, this application provides a rocket engine turbopump fixing device to solve or improve the problems of complex disassembly and assembly and difficult positioning of turbopumps.

[0005] This application provides a rocket engine turbopump mounting device, comprising:

[0006] A connector having a notch adapted to allow passage of a turbopump, and the connector being adapted to be connected to a rocket engine;

[0007] At least two connecting plates, the two connecting plates being adapted to be fixed on the turbopump, and the portions of the two connecting plates corresponding to the periphery of the notch being detachably connected;

[0008] A first telescopic rod, one end of which is hinged to the connecting member, and the other end of which is adapted to be connected to the turbine pump;

[0009] The second telescopic rod has one end hinged to the connector and the other end adapted to be connected to the turbine pump.

[0010] The first telescopic rod and the second telescopic rod are located on both sides of the connecting plate along the first direction.

[0011] In this embodiment, the turbopump is embedded in the notch. Two connecting plates on the turbopump are arranged along the first direction corresponding to the connecting parts on the periphery of the notch and are detachably connected. The turbopump is positioned by fixing the connecting plates to the connecting parts. The first telescopic rod is shortened, one end of the first telescopic rod is hinged to the connecting parts, and the first telescopic rod is extended so that its other end is connected to the turbopump. The length of the first telescopic rod is adjusted to tighten the turbopump onto the connecting parts. The second telescopic rod is shortened, one end of the second telescopic rod is hinged to the connecting parts, and the second telescopic rod is extended so that its other end is connected to the turbopump. The length of the second telescopic rod is adjusted to tighten the turbopump onto the connecting parts. The first telescopic rod and the second telescopic rod are located on both sides of the connecting plate along the first direction. The turbopump is installed on the rocket engine together by the first telescopic rod, the second telescopic rod and the connecting parts, simplifying disassembly and assembly and facilitating positioning.

[0012] In one alternative embodiment, the connector includes:

[0013] A connecting pipe adapted to be connected to a rocket engine, the axis of the connecting pipe being parallel to the first direction, and one end of both the first telescopic rod and the second telescopic rod being hinged to the connecting pipe;

[0014] A support plate is connected to the periphery of the connecting pipe, and the support plate has the notch. The support plate is connected to the connecting plate.

[0015] In one optional embodiment, the support plate is provided with a plurality of first connecting holes, and each connecting plate is provided with a second connecting hole corresponding to the plurality of first connecting holes. The support plate and each connecting plate are connected by fasteners inserted into the first connecting holes and the second connecting holes.

[0016] In one optional embodiment, the connector further includes a reinforcing plate, wherein a first side of the reinforcing plate is connected to the periphery of the connecting pipe, and a second side adjacent to the first side is connected to the bottom surface of the support plate.

[0017] In one alternative implementation, the first telescopic rod includes:

[0018] The first pull rod has a first threaded hole and a second threaded hole respectively provided at both ends along its axial direction, and the thread directions of the first threaded hole and the second threaded hole are opposite.

[0019] The first connecting rod has one end connected to the first threaded hole and the other end hinged to the connecting tube;

[0020] The second connecting rod has one end connected to the second threaded hole and the other end adapted to be connected to the turbo pump.

[0021] In one alternative implementation, it further includes:

[0022] A first hinge seat is disposed on the connecting pipe, and a first hinge hole is provided on the first hinge seat. The end of the first connecting rod away from the first threaded hole is hinged to the first hinge hole through a first pin.

[0023] The second hinge seat is disposed on the turbine pump and has a second hinge hole. The end of the second connecting rod away from the second threaded hole is hinged to the second hinge hole by a second pin.

[0024] In one optional embodiment, at least two second telescopic rods are provided, and each of the two second telescopic rods includes:

[0025] The second pull rod has a third threaded hole and a fourth threaded hole respectively provided at both ends along its axial direction, and the threads of the third threaded hole and the fourth threaded hole are opposite in direction;

[0026] The third link, one end of which is connected to the third threaded hole, and the other end of which is hinged to the connecting pipe;

[0027] The fourth link has one end connected to the fourth threaded hole and the other end adapted to be connected to the turbine pump.

[0028] In one alternative implementation, it further includes:

[0029] At least two third hinge seats are provided on both sides of the connecting pipe. Each third hinge seat is provided with a third hinge hole. The end of the third connecting rod away from the third threaded hole is hinged to the third hinge hole through a third pin.

[0030] At least two fourth hinge seats are provided on both sides of the turbine pump. Each fourth hinge seat has a fourth hinge hole. The end of the fourth connecting rod away from the fourth threaded hole is hinged to the fourth hinge hole via a fourth pin.

[0031] In one alternative embodiment, the third hinge seat includes:

[0032] The third seat is disposed on the side wall of the connecting pipe, and the third seat has a third mounting hole, the axis of which intersects the first direction;

[0033] The third hinge component is provided with a third connecting rod and a third groove. The third groove is connected to the third connecting rod, and the third connecting rod is rotatably connected to the third mounting hole. The two ends of the third groove are open, and the two side walls are respectively provided with third through holes. The third pin passes through the third through holes and the third hinge hole.

[0034] And / or, the fourth hinge seat includes:

[0035] The fourth mounting body is disposed on the side walls on both sides of the turbine pump, and the fourth mounting body has a fourth mounting hole, the axis of which intersects the first direction;

[0036] The fourth hinge component is provided with a fourth connecting rod and a fourth groove. The fourth groove is connected to the fourth connecting rod, and the fourth connecting rod is rotatably connected to the fourth mounting hole. The fourth groove is open at both ends, and the two side walls are provided with corresponding fourth through holes. The fourth pin passes through the fourth through hole and the fourth hinge hole.

[0037] In one alternative embodiment, the reinforcing plate has multiple weight-reducing holes. Attached Figure Description

[0038] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0039] Figure 1 This is an exploded view of a rocket engine turbopump mounting device according to an embodiment of this application;

[0040] Figure 2 This is a front view of a rocket engine turbopump mounting device according to an embodiment of this application;

[0041] Figure 3 This is a top view of a rocket engine turbopump mounting device according to an embodiment of this application;

[0042] Figure 4 This is a schematic diagram of the connecting member, the first hinge seat, and the third hinge seat in a rocket engine turbopump fixing device according to an embodiment of this application.

[0043] Figure 5 This is a schematic diagram of the structure of the connecting plate and the first hinge seat on the turbopump in a rocket engine turbopump fixing device according to an embodiment of this application;

[0044] Figure 6This is an exploded view of the first telescopic rod in a rocket engine turbopump fixing device according to an embodiment of this application.

[0045] Figure 7 This is an exploded view of the second telescopic rod in a rocket engine turbopump fixing device according to an embodiment of this application.

[0046] Figure 8 This is a schematic diagram of the structure of the third hinge member in a rocket engine turbopump fixing device according to an embodiment of this application.

[0047] Explanation of reference numerals in the attached figures:

[0048] 1. Connector; 101. Notch; 102. Connecting pipe; 103. Support plate; 1031. First connecting hole; 104. Reinforcing plate; 1041. Weight reduction hole; 2. Turbine pump; 3. Connecting plate; 301. Second connecting hole; 4. First telescopic rod; 401. First pull rod; 402. First connecting rod; 403. Second connecting rod; 404. First bushing; 405. Second bushing; 406. First pin; 407. Second pin; 408. First locking element; 409. Second locking element; 5. Second telescopic rod; 501. Second pull rod; 502. Third connecting rod; 503. Fourth... 504. Connecting rod; 505. Third bushing; 506. Fourth bushing; 507. Third pin; 508. Third locking element; 509. Fourth locking element; 6. First hinge seat; 601. First hinge hole; 7. Second hinge seat; 702. Second hinge hole; 8. Third hinge seat; 801. Third hinge hole; 802. Third seat body; 8021. Third mounting hole; 803. Third hinge element; 8031. Third connecting rod; 8032. Third groove body; 9. Fourth hinge seat; 901. Fourth hinge hole; 10. Tripod; 11. Fixing element; X, First direction. Detailed Implementation

[0049] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0050] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application 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 application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0051] In the description of this application, it should be noted that, unless otherwise expressly 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; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0052] The turbopump is a core component of a liquid rocket engine, and its mounting method directly affects the engine's operation and vibration characteristics, making it a key factor in engine reliability. With the booming development of the commercial space market and the increasing demands for rocket payloads, the reliable operation of the turbopump is becoming increasingly important.

[0053] In related technologies, a rod-type support structure is used to connect the turbopump and the rocket engine. However, this rod-type support structure lacks rigidity and has low load-bearing capacity, making it prone to resonance with the high-speed rotating turbopump. The turbopump generates high temperatures during operation, causing uneven thermal expansion of the rod-type support structure under significant temperature differences. Stress concentration occurs at the joints between the rods, leading to fatigue cracks. Furthermore, the multiple rods result in complex assembly and disassembly, and difficult positioning. Therefore, this application provides a rocket engine turbopump fixing device to solve or improve the problems of complex assembly and disassembly and difficult positioning of the turbopump.

[0054] The following is combined with Figures 1 to 8 This describes an embodiment of the present application.

[0055] According to embodiments of this application, a rocket engine turbopump mounting device is provided, such as... Figures 1 to 3As shown, it includes: a connector 1, at least two connecting plates 3, a first telescopic rod 4, and a second telescopic rod 5. Specifically, the connector 1 is provided with a notch 101, which is adapted to avoid the turbopump 2, and the connector 1 is adapted to be connected to the rocket engine; the two connecting plates 3 are adapted to be fixed on the turbopump 2, and the portions of the two connecting plates 3 corresponding to the periphery of the notch 101 are detachably connected; one end of the first telescopic rod 4 is hinged to the connector 1, and the other end is adapted to be connected to the turbopump 2; one end of the second telescopic rod 5 is hinged to the connector 1, and the other end is adapted to be connected to the turbopump 2; the first telescopic rod 4 and the second telescopic rod 5 are located on both sides of the connecting plate 3 along the first direction X.

[0056] In this embodiment, such as Figures 1 to 3 As shown, the turbopump 2 is embedded in the notch 101. Two connecting plates 3 on the turbopump 2 are arranged along the first direction X and correspond to the connecting piece 1 on the periphery of the notch 101, and are detachably connected. The turbopump 2 is positioned by fixing the connecting plates 3 to the connecting piece 1. The first telescopic rod 4 is shortened, one end of the first telescopic rod 4 is hinged to the connecting piece 1, and the first telescopic rod 4 is extended so that its other end is connected to the turbopump 2. The length of the first telescopic rod 4 is adjusted to tighten the turbopump 2 onto the connecting piece 1. The second telescopic rod 5 is shortened, one end of the second telescopic rod 5 is hinged to the connecting piece 1, and the second telescopic rod 5 is extended so that its other end is connected to the turbopump 2. The length of the second telescopic rod 5 is adjusted to tighten the turbopump 2 onto the connecting piece 1. The first telescopic rod 4 and the second telescopic rod 5 are located on both sides of the connecting plate 3 along the first direction X. The turbopump 2 is installed on the rocket engine by the first telescopic rod 4, the second telescopic rod 5 and the connecting piece 1, which simplifies disassembly and assembly and facilitates positioning.

[0057] Specifically, such as Figure 3 As shown, two connecting plates 3 are arranged on opposite sides of the turbine pump 2, and the angle formed by the line connecting the two connecting plates 3 and the axis of the turbine pump 2 is 180°.

[0058] In one embodiment, such as Figure 2 and Figure 4 As shown, the connector 1 includes a connecting pipe 102 and a support plate 103. Specifically, the connecting pipe 102 is adapted to be connected to a rocket engine. The axial direction of the connecting pipe 102 is parallel to the first direction X. One end of the first telescopic rod 4 and the second telescopic rod 5 are both hinged to the connecting pipe 102. The support plate 103 is connected to the periphery of the connecting pipe 102. A notch 101 is provided on the support plate 103. The support plate 103 is connected to the connecting plate 3.

[0059] In this embodiment, such as Figures 2 to 4As shown, the connecting pipe 102 is fixedly connected to the rocket engine. The axis of the turbopump 2 is parallel to the first direction X, and the surface of the support plate 103 is perpendicular to the first direction X, so that part of the turbopump 2 can be inserted into the notch 101, so that the support plate 103 and the connecting plate 3 can correspond to each other in the first direction X. The connecting plate 3 is set above the support plate 103 to support the turbopump 2 and facilitate positioning. The connecting plate 3 and the support plate 103 are fixedly connected by the fastener 11, and the turbopump 2 is installed on the rocket engine through the connecting member 1.

[0060] In one embodiment, such as Figure 4 and Figure 5 As shown, the support plate 103 has a plurality of first connection holes 1031, and each connecting plate 3 has a second connection hole 301 corresponding to the plurality of first connection holes 1031. The support plate 103 and each connecting plate 3 are connected by a fastener 11 inserted into the first connection hole 1031 and the second connection hole 301.

[0061] In this embodiment, such as Figure 3 As shown, the fastener 11 consists of bolts and nuts. Multiple bolts pass through the first connecting hole 1031 and the second connecting hole 301 and are connected to the nuts to fix the support plate 103 and the connecting plate 3.

[0062] Specifically, such as Figure 4 and Figure 5 As shown, each connecting plate 3 has three second connecting holes 301.

[0063] In one embodiment, such as Figure 4 As shown, the connector 1 also includes a reinforcing plate 104, the first side of the reinforcing plate 104 being connected to the periphery of the connecting pipe 102, and the second side adjacent to the first side being connected to the bottom surface of the support plate 103.

[0064] In this embodiment, such as Figure 4 As shown, the reinforcing plate 104 enhances the strength of the support plate 103. Specifically, the reinforcing plate 104 is a triangular plate, and the two right-angled sides of the triangular plate are respectively connected and fixed to the periphery of the connecting pipe 102 and the bottom surface of the support plate 103. The fixing method can be bolt fixing or welding fixing.

[0065] Specifically, such as Figure 4 As shown, the support plate 103, the reinforcing plate 104 and the notch 101 form a tripod 10.

[0066] In one embodiment, such as Figure 2 and Figure 6As shown, the first telescopic rod 4 includes: a first pull rod 401, a first connecting rod 402, and a second connecting rod 403. Specifically, the first pull rod 401 has a first threaded hole and a second threaded hole respectively provided at both ends along its axial direction, and the threads of the first threaded hole and the second threaded hole are opposite in direction; one end of the first connecting rod 402 is connected to the first threaded hole, and the other end is hinged to the connecting pipe 102; one end of the second connecting rod 403 is connected to the second threaded hole, and the other end is adapted to be connected to the turbine pump 2.

[0067] In this embodiment, such as Figure 2 and Figure 6 As shown, rotating the first pull rod 401 causes the threads of the first threaded hole and the second threaded hole to be opposite in direction, which can adjust the axial distance between the first connecting rod 402 and the second connecting rod 403, so that the first connecting rod 402 and the second connecting rod 403 move closer or further away from each other at the same time, which can increase the adjustment speed and facilitate disassembly and assembly.

[0068] In one embodiment, such as Figure 6 As shown, it also includes: a first hinge seat 6 and a second hinge seat 7. The first hinge seat 6 is disposed on the connecting pipe 102 and is provided with a first hinge hole 601. The end of the first connecting rod 402 away from the first threaded hole is hinged to the first hinge hole 601 through a first pin 406. The second hinge seat 7 is disposed on the turbine pump 2 and is provided with a second hinge hole 702. The end of the second connecting rod 403 away from the second threaded hole is hinged to the second hinge hole 702 through a second pin 407.

[0069] Specifically, such as Figure 6 As shown, the first connecting rod 402 and the second connecting rod 403 are respectively provided with a first pin hole and a second pin hole at the ends away from the first pull rod 401. A first pin 406 and a second pin 407 are respectively inserted into the first pin hole and the second pin hole. A first bushing 404 is provided between the first pin 406 and the first pin hole. A second bushing 405 is provided between the second pin 407 and the second pin hole.

[0070] Specifically, such as Figure 6 As shown, the first pin 406 is locked by the first locking member 408, and the second pin 407 is locked by the second locking member 409. The first locking member 408 and the second locking member 409 can be nuts.

[0071] In one embodiment, such as Figure 7As shown, at least two second telescopic rods 5 are provided. Each second telescopic rod 5 includes a second tie rod 501, a third connecting rod 502, and a fourth connecting rod 503. Specifically, the two ends of the second tie rod 501 are respectively provided with a third threaded hole and a fourth threaded hole along its axial direction, and the threads of the third threaded hole and the fourth threaded hole are opposite in direction. One end of the third connecting rod 502 is connected to the third threaded hole, and the other end is hinged to the connecting pipe 102. One end of the fourth connecting rod 503 is connected to the fourth threaded hole, and the other end is adapted to be connected to the turbine pump 2.

[0072] In this embodiment, such as Figure 2 and Figure 7 As shown, rotating the second pull rod 501 reverses the thread direction of the third threaded hole and the fourth threaded hole, which can adjust the axial distance between the third connecting rod 502 and the fourth connecting rod 503, allowing the third connecting rod 502 and the fourth connecting rod 503 to move closer or further away from each other simultaneously, thereby increasing the adjustment speed and facilitating disassembly and assembly.

[0073] Two second telescopic rods 5 are set on both sides of the connecting pipe 102. One first telescopic rod 4 and two second telescopic rods 5 form a triangular connecting frame to improve the connection strength between the turbine pump 2 and the connecting piece 1.

[0074] In one embodiment, such as Figure 2 and Figure 7 As shown, it also includes: at least two third hinge seats 8 and at least two fourth hinge seats 9. Specifically, the two third hinge seats 8 are arranged on both sides of the connecting pipe 102, and the third hinge seats 8 are provided with third hinge holes 801. The end of the third connecting rod 502 away from the third threaded hole is hinged to the third hinge hole 801 through the third pin 506. The two fourth hinge seats 9 are arranged on both sides of the turbine pump 2, and the fourth hinge seats 9 are provided with fourth hinge holes 901. The end of the fourth connecting rod 503 away from the fourth threaded hole is hinged to the fourth hinge hole 901 through the fourth pin 507.

[0075] Specifically, such as Figure 7 As shown, the third connecting rod 502 and the fourth connecting rod 503 are respectively provided with a third pin hole and a fourth pin hole at the ends away from the second tie rod 501. The third pin hole and the fourth pin hole are respectively inserted with a third pin 506 and a fourth pin 507. A third bushing 504 is provided between the third pin 506 and the third pin hole, and a fourth bushing 505 is provided between the fourth pin 507 and the fourth pin hole.

[0076] Specifically, the third pin 506 is locked by the third locking member 508, and the fourth pin 507 is locked by the fourth locking member 509. The third locking member 508 and the fourth locking member 509 can be nuts.

[0077] In one embodiment, such as Figure 1 and Figure 8As shown, the third hinge seat 8 includes a third seat body 802 and a third hinge member 803. Specifically, the third seat body 802 is disposed on the side wall of the connecting pipe 102. The third seat body 802 has a third mounting hole 8021. The axial direction of the third mounting hole 8021 intersects with the first direction X. Specifically, the axial direction of the third mounting hole 8021 is perpendicular to the first direction X. The third hinge member 803 is provided with a third connecting rod 8031 ​​and a third groove 8032. The third groove 8032 is connected to the third connecting rod 8031. The third connecting rod 8031 ​​is rotatably connected to the third mounting hole 8021. The third groove 8032 is open at both ends, and the two side walls are respectively provided with third hinge holes 801. The third pin 506 passes through the third hinge hole 801 and the third pin hole.

[0078] The third connecting rod 8031 ​​is rotatably connected to the third mounting hole 8021, which can adjust the angle of the second telescopic rod 5, increase the degree of freedom of the connection between the second telescopic rod 5 and the connecting pipe 102, facilitate installation, and prevent installation failure due to angle problems.

[0079] In one embodiment, the fourth hinge seat 9 includes a fourth seat body and a fourth hinge member. Specifically, the fourth seat body is disposed on the side walls on both sides of the turbine pump 2. The fourth seat body has a fourth mounting hole. The axial direction of the fourth mounting hole intersects with the first direction X. Specifically, the axial direction of the fourth mounting hole is perpendicular to the first direction X. The fourth hinge member is provided with a fourth connecting rod and a fourth groove. The fourth groove is connected to the fourth connecting rod. The fourth connecting rod is rotatably connected to the fourth mounting hole. The two ends of the fourth groove are open, and the two side walls are provided with corresponding fourth through holes. The fourth pin 507 passes through the fourth through hole and the fourth hinge hole 901.

[0080] The fourth hinge seat 9 has the same structure as the third hinge seat 8.

[0081] The fourth connecting rod is rotatably connected to the fourth mounting hole, which can adjust the angle of the other second telescopic rod 5, increase the degree of freedom of the connection between the second telescopic rod 5 and the connecting pipe 102, facilitate installation, and prevent installation failure due to angle problems.

[0082] In one embodiment, the reinforcing plate 104 has a plurality of weight-reducing holes 1041.

[0083] In this embodiment, the weight of the reinforcing plate 104 is reduced, thereby reducing the total weight of the fixing device.

[0084] Overall, compared with the traditional planar and tie rod structure, the fixing device in this application using a tripod 10 and tie rods (first telescopic rod 4 and second telescopic rod 5) has the following advantages:

[0085] 1. The tripod 10 has strong stability and strong resistance to deformation, which can greatly improve rigidity. Compared with the planar structure, the deformation is reduced by 60%.

[0086] 2. The tripod 10 provides excellent control over the vibration of the turbine pump 2 and also has excellent vibration resistance.

[0087] 3. The tripod 10 is also very easy to install and maintain.

[0088] 4. For the structure of the tripod 10 product, finite element simulation analysis was used to optimize the topology while ensuring performance, achieving equal strength design, optimizing the structural scheme and reducing weight.

[0089] This application adopts a fixing scheme that primarily uses a tripod 10 for planar support, supplemented by three tie rods (one first telescopic rod 4 and two second telescopic rods 5) for upper and lower support. Its main innovations are as follows:

[0090] 1. The tripod 10 serves as the main support structure, and the mating surface is connected by bolts. The bolts allow for quick positioning and tightening, which effectively ensures the relative position of the turbo pump 2 and the engine, greatly simplifying the product assembly process.

[0091] 2. The tripod 10 supports utilize the geometric characteristics of the triangle's "three-sided closed loop" to form a stable static structure in three-dimensional space. Its stiffness is about 3 to 5 times higher than that of the traditional rod support structure, which can effectively avoid the resonance range of the high-speed rotation of the turbine pump 2.

[0092] 3. One first telescopic rod 4 and two second telescopic rods 5 can effectively distribute the centrifugal force and vibration force generated by the turbine pump 2 during operation, thereby improving the rigidity of the entire structure. At the same time, these forces can be evenly transmitted to the tripod 10, avoiding excessive local stress and reducing the risk of fatigue damage to components.

[0093] 4. The flexibility of the rod support (one first telescopic rod 4 and two second telescopic rods 5) complements the rigidity of the planar connection of the tripod 10, which greatly enhances the dynamic stability of the engine.

[0094] 5. Modular design: When it is necessary to repair or replace turbo pump 2, the work can be carried out independently without disassembling other engine parts, making local maintenance convenient and improving work efficiency.

[0095] Although embodiments of this application have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of this application, and such modifications and variations all fall within the scope defined by the appended application.

Claims

1. A rocket engine turbine pump fixture, comprising: include: A connector (1) having a notch (101) adapted to avoid a turbopump (2) and adapted to be connected to a rocket engine; At least two connecting plates (3), the two connecting plates (3) are adapted to be fixed on the turbine pump (2), and the portions of the two connecting plates (3) corresponding to the periphery of the notch (101) are detachably connected; The first telescopic rod (4) has one end hinged to the connector (1) and the other end adapted to be connected to the turbine pump (2); The second telescopic rod (5) has one end hinged to the connector (1) and the other end adapted to be connected to the turbine pump (2); The first telescopic rod (4) and the second telescopic rod (5) are located on both sides of the connecting plate (3) along the first direction (X).

2. The rocket engine turbopump fixing device according to claim 1, characterized in that, The connector (1) includes: A connecting pipe (102) is adapted to be connected to a rocket engine. The axial direction of the connecting pipe (102) is parallel to the first direction (X). One end of the first telescopic rod (4) and the second telescopic rod (5) are both hinged to the connecting pipe (102). A support plate (103) is connected to the periphery of the connecting pipe (102). The support plate (103) has the notch (101) and is connected to the connecting plate (3).

3. The rocket engine turbine pump fixture of claim 2, wherein, The support plate (103) has a plurality of first connecting holes (1031), and each of the connecting plates (3) has a second connecting hole (301) corresponding to the plurality of first connecting holes (1031). The support plate (103) and each of the connecting plates (3) are connected by a fastener (11) inserted into the first connecting hole (1031) and the second connecting hole (301).

4. The rocket engine turbine pump fixture of claim 3, wherein, The connector (1) further includes a reinforcing plate (104), the first side of which is connected to the periphery of the connecting pipe (102), and the second side adjacent to the first side is connected to the bottom surface of the support plate (103).

5. The rocket engine turbine pump fixture of claim 2, wherein, The first telescopic rod (4) includes: The first pull rod (401) has a first threaded hole and a second threaded hole respectively provided at both ends along its axial direction. The thread directions of the first threaded hole and the second threaded hole are opposite. The first connecting rod (402) has one end connected to the first threaded hole and the other end hinged to the connecting tube (102); The second connecting rod (403) has one end connected to the second threaded hole and the other end adapted to be connected to the turbine pump (2).

6. The rocket engine turbine pump fixture of claim 5, wherein, Also includes: The first hinge seat (6) is disposed on the connecting pipe (102). The first hinge seat (6) is provided with a first hinge hole (601). The end of the first connecting rod (402) away from the first threaded hole is hinged to the first hinge hole (601) through a first pin (406). The second hinge seat (7) is disposed on the turbine pump (2). The second hinge seat (7) is provided with a second hinge hole (702). The end of the second connecting rod (403) away from the second threaded hole is hinged to the second hinge hole (702) through the second pin (407).

7. The rocket engine turbine pump fixture of claim 2, wherein, At least two second telescopic rods (5) are provided, and each of the two second telescopic rods (5) includes: The second pull rod (501) has a third threaded hole and a fourth threaded hole respectively provided at both ends along its axial direction. The thread directions of the third threaded hole and the fourth threaded hole are opposite. The third link (502) has one end connected to the third threaded hole and the other end hinged to the connecting pipe (102); The fourth link (503) has one end connected to the fourth threaded hole and the other end adapted to be connected to the turbine pump (2).

8. The rocket engine turbine pump fixture of claim 7, wherein, Also includes: At least two third hinge seats (8) are provided on both sides of the connecting pipe (102). The third hinge seats (8) are provided with third hinge holes (801). The end of the third connecting rod (502) away from the third threaded hole is hinged to the third hinge hole (801) through a third pin (506). At least two fourth hinge seats (9) are provided on both sides of the turbine pump (2). The fourth hinge seats (9) are provided with fourth hinge holes (901). The end of the fourth connecting rod (503) away from the fourth threaded hole is hinged to the fourth hinge hole (901) through the fourth pin (507).

9. The rocket engine turbine pump fixture of claim 8, wherein, The third hinge seat (8) includes: The third seat (802) is disposed on the side wall of the connecting pipe (102), and the third seat (802) has a third mounting hole (8021), the axial direction of the third mounting hole (8021) intersecting the first direction (X); The third hinge (803) is provided with a third connecting rod (8031) and a third groove (8032). The third groove (8032) is connected to the third connecting rod (8031). The third connecting rod (8031) is rotatably connected to the third mounting hole (8021). The third groove (8032) is open at both ends and has corresponding third through holes on both side walls. The third pin (506) passes through the third through hole and the third hinge hole (801). And / or, the fourth hinge (9) includes: The fourth mounting body is disposed on the side walls on both sides of the turbine pump (2), and the fourth mounting body is provided with a fourth mounting hole, the axial direction of which intersects with the first direction (X); The fourth hinge is provided with a fourth connecting rod and a fourth groove. The fourth groove is connected to the fourth connecting rod. The fourth connecting rod is rotatably connected to the fourth mounting hole. The two ends of the fourth groove are open, and the two side walls are provided with corresponding fourth through holes. The fourth pin (507) passes through the fourth through hole and the fourth hinge hole (901).

10. The rocket engine turbine pump fixture of claim 4, wherein, The reinforcing plate (104) has multiple weight-reducing holes (1041).

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