Device and method for detecting rotor flexibility of a rocket engine turbine pump

Abstract

The application relates to a rotor flexibility detection device and method of a rocket engine turbine pump, and belongs to the technical field of liquid rocket engines. A side of a circumferential wall of a turbine exhaust pipe close to a turbine shell is provided with an openable and closable access hole; the rotor flexibility detection device comprises a shell, a rotating assembly and a rotating torque measuring meter; the shell is configured to be inserted into the access hole; the rotating assembly comprises a rotating shaft and a transmission assembly, the rotating shaft is rotatably arranged in the shell and comprises a first shaft segment and a second shaft segment arranged at an angle alpha, the first shaft segment is configured to be sleeved with a turbine rotor, the transmission assembly is arranged in the shell and is in transmission connection with the first shaft segment and the second shaft segment, and the transmission assembly can drive the first shaft segment to rotate when the second shaft segment rotates; the rotating torque measuring meter is arranged outside the shell and is connected with the second shaft segment and is configured to measure the rotating torque of the turbine rotor. The device can complete the detection operation without dismounting the whole exhaust pipe assembly and the heat exchanger pipeline.

Description

Technical Field

[0001] This application relates to the field of liquid rocket engine technology, and in particular to a device and method for detecting the rotor flexibility of a rocket engine turbopump. Background Technology

[0002] With the development of the commercial space economy, the launch cost per unit mass of payload needs to be significantly reduced, making rocket recovery and multiple reuse an inevitable technological path. Simultaneously, the demand for frequent launches places increasingly shorter requirements on the time intervals between multiple launches. After engine return and before re-flight, systematic health checks and fault repairs are necessary. Traditional technologies require engine return to the factory, disassembly for inspection, and reassembly, which is time-consuming. The goal of reusable engines is "no-fly-off" maintenance. For the turbopump, a core component of the engine, rotor flexibility checks can provide a direct and comprehensive assessment of the turbopump's health, especially the condition of critical vulnerable components such as bearings, seals, and impellers.

[0003] Rotor flexibility checks typically require measuring the rotor's rotational damping, i.e., the rotational torque, using tools. In practice, it's usually necessary to remove the exhaust pipe assembly outside the turbine disk near the turbine end to expose the turbine disk, and then use tools to connect the turbine rotor for a rotation test. The turbine exhaust pipe assembly usually contains embedded heat exchanger piping, which must also be disconnected from the engine. This disassembly and inspection requires removing the entire exhaust pipe assembly, involving dozens of fastening bolts, heat exchanger piping sealing flanges, and other connecting parts. It is time-consuming and labor-intensive, making it difficult to meet the needs of frequent launches and rapid maintenance of reusable rocket engines. Summary of the Invention

[0004] Therefore, it is necessary to provide a device and method for detecting the rotor flexibility of a rocket engine turbopump to address the aforementioned technical problems.

[0005] A rotor flexibility testing device for a rocket engine turbopump, wherein the rocket engine turbopump includes a turbine housing, a turbine rotor, and a turbine exhaust pipe, the turbine rotor being rotatably disposed within the turbine housing, the turbine exhaust pipe being connected to the turbine housing, and an openable and closable inspection hole being provided on the circumferential wall of the turbine exhaust pipe near the turbine housing; the rotor flexibility testing device includes:

[0006] The housing is configured to be inserted into the access hole;

[0007] A rotating assembly includes a rotating shaft and a transmission assembly. The rotating shaft is rotatably disposed within the housing and includes a first shaft segment and a second shaft segment positioned at an included angle α. The first shaft segment is configured to engage with the turbine rotor. The transmission assembly is disposed within the housing and is drively connected to the first shaft segment and the second shaft segment. The transmission assembly is capable of driving the first shaft segment to rotate when the second shaft segment rotates.

[0008] A rotational torque meter is located outside the housing and connected to the second shaft segment, the rotational torque meter being configured to measure the rotational torque of the turbine rotor.

[0009] In one embodiment, the central axis of the inspection hole is coplanar with the central axis of the turbine rotor and forms a 90° angle between them.

[0010] The included angle α is 90°.

[0011] In one embodiment, the housing includes a first sub-housing and a second sub-housing connected at the included angle α, the first shaft segment being rotatably disposed through the first sub-housing, and the second shaft segment being rotatably disposed through the second sub-housing.

[0012] In one embodiment, a slope is provided at the junction of the first sub-shell and the second sub-shell, and the slope is disposed opposite to the turbine shell.

[0013] In one embodiment, a first rolling bearing is provided inside the first sub-housing housing, and the first rolling bearing is rotatably passed through the first shaft segment.

[0014] And / or, the second sub-casing is provided with a second rolling bearing, through which the second shaft segment is rotatably inserted.

[0015] In one embodiment, the end of the second sub-shell away from the first sub-shell is provided with a handle.

[0016] In one embodiment, the transmission assembly includes a first bevel gear and a second bevel gear, the first bevel gear being mounted on the first shaft segment, and the second bevel gear being mounted on the second shaft segment and meshing with the first bevel gear.

[0017] In one embodiment, one of the ends of the turbine rotor near the turbine exhaust pipe and the end of the first shaft segment that is sleeved with the turbine rotor is provided with a non-circular insertion hole, and the other is provided with a plug fitting that is inserted into the insertion hole and whose outer contour is adapted to the insertion hole.

[0018] And / or, the second shaft segment is connected to the rotational torque meter via a quick-connect fitting.

[0019] In one embodiment, the rotor flexibility detection device further includes a monitoring module located on the side of the housing near the turbine rotor and configured to monitor whether the first shaft segment is properly fitted onto the turbine rotor.

[0020] A method for detecting the rotor flexibility of a rocket engine turbopump, implemented by a rotor flexibility detection device as described in any of the preceding claims, the rotor flexibility detection method comprising:

[0021] Open the access port on the turbine exhaust pipe and insert the housing of the rotor flexibility testing device into the turbine exhaust pipe through the access port;

[0022] The first shaft segment of the rotor flexibility detection device is fitted onto the turbine rotor;

[0023] The second shaft section of the rotor flexibility detection device is rotated, and during the rotation of the second shaft section, the rotational torque of the turbine rotor is measured using the rotational torque measuring meter of the rotor flexibility detection device.

[0024] The aforementioned rotor flexibility testing device and method for rocket engine turbopumps addresses the issue that existing turbopumps, designed for more compact mounting on the engine to reduce overall engine envelope size, typically employ an asymmetrical exhaust pipe structure with its central axis offset from the turbine rotor. This results in a recessed space within the exhaust pipe to accommodate the bell-shaped section of the engine thrust nozzle. However, the asymmetrical structure of the exhaust pipe and its internal heat exchanger prevent the rotor flexibility testing device from extending into the exhaust pipe and engaging the rotor shaft with the turbine rotor. Therefore, this application provides an inspection hole on the circumferential wall of the exhaust pipe near the turbine housing, and sets the shaft into a first and second shaft segment arranged at an angle α. In use, the first shaft segment extends into the exhaust pipe through the inspection hole and engages with the turbine rotor. The operator simply rotates the second shaft segment, which drives the turbine rotor to rotate via a transmission assembly, allowing the rotational torque to be measured using a torque meter. Since the inspection operation can be completed simply by opening and closing the inspection port, there is no need to dismantle the entire exhaust pipe assembly and heat exchanger piping. This eliminates the need to disassemble and install dozens of fastening bolts and sealing flanges, resulting in a shorter time consumption and less workload. This meets the actual needs of intensive launches and rapid maintenance of reusable rocket engines. Attached Figure Description

[0025] Figure 1 A schematic diagram of the structure of a rocket engine turbopump provided by existing technology.

[0026] Figure 2 A schematic diagram of the structure of a rotor flexibility testing device for a rocket engine turbopump provided in an embodiment of this application.

[0027] Figure 3 A schematic diagram illustrating the interaction between a rotor flexibility testing device and a rocket engine turbopump, as provided in an embodiment of this application.

[0028] The labels in the attached diagram are explained as follows:

[0029] Existing rocket engine turbopump: 20', turbopump; 21', turbine casing; 22', turbine disk; 23', turbine rotor; 24', turbine exhaust pipe; 25', heat exchanger;

[0030] The rocket engine turbopump of this application includes: 20, turbopump; 21, turbine housing; 22, turbine disk; 23, turbine rotor; 24, turbine exhaust pipe; 241, inspection port; 25, heat exchanger;

[0031] The rotor flexibility testing device of this application includes: 10, rotor flexibility testing device; 100, housing; 110, first sub-housing; 120, second sub-housing; 130, inclined plane; 140, first rolling bearing; 150, second rolling bearing; 160, handle; 200, rotating shaft; 210, first shaft section; 220, second shaft section; 300, transmission assembly; 310, first bevel gear; 320, second bevel gear; and 400, rotational torque measuring instrument. Detailed Implementation

[0032] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0033] In the description of this application, it should be understood that if terms such as "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" appear, these terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are 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, and therefore should not be construed as a limitation of this application.

[0034] Furthermore, where the terms "first" and "second" appear, these terms are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, where the term "multiple" appears, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0035] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0036] In this application, unless otherwise expressly specified and limited, the use of descriptions such as "above" or "below" the second feature indicates that the first and second features are in direct contact, or indirect contact via an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. Similarly, "below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0037] It should be noted that if an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. If an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. If so, the terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used in this application are for illustrative purposes only and do not represent the only possible implementation.

[0038] Liquid rocket engines typically use turbopumps to pressurize and deliver cryogenic liquid propellants. For example... Figure 1As shown, the turbopump 20' includes a pump assembly (not shown in the figure), a turbine, and a turbine exhaust pipe assembly. The pump assembly is used to pressurize the cryogenic liquid propellant and deliver it to the thrust chamber; the turbine is used to receive high-temperature and high-pressure gas and convert its thermal energy into rotational mechanical energy to generate the torque to drive the pump assembly; and the turbine exhaust pipe assembly is used to guide and discharge the gas after driving the turbine.

[0039] The turbine includes a turbine housing 21' and a rotor assembly. The rotor assembly is rotatably disposed within the turbine housing 21' and includes a connected turbine disk 22' and turbine rotor 23'. Blades are mounted on the turbine disk 22'. The high-temperature, high-pressure gas generated by the gas generator impacts the blades on the turbine disk 22', driving the turbine disk 22' and the coaxial turbine rotor 23' to rotate at high speed. This, in turn, drives the pump impeller of the pump assembly to rotate, thereby pressurizing the propellant. The turbine exhaust pipe assembly includes a turbine exhaust pipe 24' and a heat exchanger 25'. The turbine exhaust pipe 24' is bolted to the turbine housing 21' via a flange. The heat exchanger 25' is disposed within the turbine exhaust pipe 24' and is used to utilize the waste heat of the gas to heat the cryogenic medium to pressurize the storage tank.

[0040] With rocket recovery and reuse becoming an important development direction in the aerospace field, systematic health diagnosis and fault repair are required after engine return and before re-flight. For the core component of the engine, the turbopump 20', the flexibility check of the turbine rotor 23' can intuitively and comprehensively assess the health of the turbopump 20', especially the condition of key vulnerable parts such as bearings, seals, and impellers. The flexibility check of the turbine rotor 23' usually requires the use of tools to measure the rotational damping, i.e., the torque value, of the turbine rotor 23'. In practice, it is usually necessary to remove the exhaust pipe assembly outside the turbine disk 22' near the turbine end to expose the turbine disk 22', and then use tools to connect the turbine rotor 23' for a rotation test. The turbine exhaust pipe assembly contains heat exchanger piping, which must also be disconnected from the engine. The above disassembly and inspection requires the removal of the entire exhaust pipe assembly, involving dozens of fastening bolts, heat exchanger piping sealing flanges, and other connecting parts, which is time-consuming and labor-intensive, and can no longer meet the needs of intensive launches and rapid maintenance of reusable rocket engines.

[0041] In this regard, such as Figure 2 and Figure 3 As shown, one embodiment of this application provides a rotor flexibility testing device 10 for a rocket engine turbopump. Simultaneously, this application also improves the structure of the turbine exhaust pipe 24 so that it can be used in conjunction with the rotor flexibility testing device 10, thereby enabling the inspection of the turbine rotor 23's flexibility without disassembling the exhaust pipe assembly.

[0042] Specifically, such as Figure 3As shown, the circumferential wall of the turbine exhaust pipe 24 has an openable and closable access hole 241 on the side near the turbine housing 21. As an example, the access hole 241 is provided with an openable and closable sealing cover (not shown in the figure). When it is necessary to test the flexibility of the turbine rotor 23, the sealing cover is removed, and the rotor flexibility testing device 10 is inserted through the access hole 241 and engaged with the turbine rotor 23 for testing; after the test is completed, the rotor flexibility testing device 10 is removed and the sealing cover is reset.

[0043] like Figure 2 and Figure 3 As shown, the rotor flexibility testing device 10 includes a housing 100, a rotating assembly, and a rotational torque meter 400. The housing 100 is configured to be inserted into the inspection hole 241. The rotating assembly includes a rotating shaft 200 and a transmission assembly 300. The rotating shaft 200 is rotatably inserted through the housing 100 and includes a first shaft section 210 and a second shaft section 220 arranged at an included angle α. The first shaft section 210 is configured to be sleeved with the turbine rotor 23. The transmission assembly 300 is disposed in the housing 100 and is connected to the first shaft section 210 and the second shaft section 220. The transmission assembly 300 can drive the first shaft section 210 to rotate when the second shaft section 220 rotates. The rotational torque meter 400 is disposed outside the housing 100 and connected to the second shaft section 220. The rotational torque meter 400 is configured to measure the rotational torque of the turbine rotor 23.

[0044] When a flexibility test of the turbine rotor 23 is required, open the access hole 241, insert the housing 100 of the rotor flexibility testing device 10 into the turbine exhaust pipe 24 through the access hole 241, and adjust the position of the housing 100 until the first shaft section 210 engages with the mating hole on the end face of the turbine rotor 23; then rotate the second shaft section 220, and the transmission assembly 300 drives the first shaft section 210 to rotate as the second shaft section 220 rotates, thereby driving the turbine rotor 23 to rotate. At the same time, the rotational torque of the turbine rotor 23 is measured using the rotational torque measuring meter 400. After the test is completed, remove the rotor flexibility testing device 10 and close the access hole 241.

[0045] Considering that existing turbopumps 20' are designed to be more compactly mounted on the engine to reduce the overall engine envelope size, the turbine exhaust pipe 24 is typically designed as an asymmetrical pipe structure with its central axis offset from the turbine rotor 23, creating a recessed space within the turbine exhaust pipe 24 to accommodate the bell-shaped section of the engine thrust nozzle. However, the asymmetrical structure of the turbine exhaust pipe 24 and its internal heat exchanger 25 prevent the rotor flexibility detection device 10 from extending into the inlet of the turbine exhaust pipe 24 and engaging the shaft 200 with the turbine rotor 23. Therefore, this application provides an access hole 241 on the circumferential wall of the turbine exhaust pipe 24 near the turbine housing 21, and sets the shaft 200 as a first shaft section 210 and a second shaft section 220 arranged at an angle α. In use, the first shaft section 210 extends into the turbine exhaust pipe 24 through the inspection hole 241 and can be fitted with the turbine rotor 23. The operator only needs to rotate the second shaft section 220, which will drive the turbine rotor 23 to rotate through the transmission assembly 300, and then use the rotational torque measuring meter 400 to measure its rotational torque. Since the inspection operation can be completed by simply opening and closing the inspection hole 241, it is not necessary to disassemble the entire exhaust pipe assembly and heat exchanger piping, saving the process of disassembling and assembling dozens of fastening bolts and sealing flanges. It is time-saving and labor-saving, which can meet the actual needs of intensive launches and rapid maintenance of reusable rocket engines.

[0046] In some embodiments of this application, the central axis of the inspection hole 241 is coplanar with the central axis of the turbine rotor 23 and forms a 90° angle between them, and the angle α between the first shaft segment 210 and the second shaft segment 220 is 90°. This arrangement allows the first shaft segment 210 to be directly aligned with the center of the end face of the turbine rotor 23 along the axial direction of the turbine exhaust pipe 24 after the rotor flexibility detection device 10 is inserted through the inspection hole 241, facilitating the connection of the turbine rotor 23. The second shaft segment 220 extends radially outward along the turbine exhaust pipe 24, allowing the operator to radially rotate the second shaft segment 220 on the outside of the turbine exhaust pipe 24, driving the turbine rotor 23 to rotate via the transmission assembly 300. This provides ample operating space and convenient force application.

[0047] In some embodiments of this application, such as Figure 2As shown, the outer casing 100 includes a first sub-outer casing 110 and a second sub-outer casing 120 connected at an included angle α. A first shaft segment 210 is rotatably disposed through the first sub-outer casing 110, and a second shaft segment 220 is rotatably disposed through the second sub-outer casing 120. During installation, the first sub-outer shell 110 (together with the first shaft section 210 inside it) of the outer shell 100 is first inserted into the turbine exhaust pipe 24 radially along the turbine exhaust pipe 24 through the inspection hole 241. After the first sub-outer shell 110 is fully inserted into the inner cavity of the turbine exhaust pipe 24, the entire outer shell 100 is rotated around the axis of the inspection hole 241 by a certain angle (e.g., 90°) so that the axial direction of the first shaft section 210 is parallel to the axial direction of the turbine rotor 23. Then, the second sub-outer shell 120 (together with the second shaft section 220 inside it) is inserted radially along the inspection hole 241 until the first shaft section 210 is aligned with the end face of the turbine rotor 23. Then, the second sub-outer shell 120 is translated along the axial direction of the turbine exhaust pipe 24 until the first shaft section 210 is fitted with the turbine rotor 23.

[0048] Since the outer casing 100 can be adjusted in stages according to the installation progress, the opening size of the inspection hole 241 only needs to be slightly larger than the cross-sectional size of a single sub-outer casing 100 to meet the installation requirements, without having to reserve a large-diameter opening to accommodate the outer shape of the entire device. This reduces the structural weakening of the turbine exhaust pipe 24 and helps to maintain the pressure-bearing capacity and sealing reliability of the turbine exhaust pipe 24.

[0049] The first sub-shell 110 and the second sub-shell 120 can be connected by welding, screwing, or other methods, or they can be connected into a single structure by casting.

[0050] Optionally, see Figure 2 A ramp 130 is provided at the junction of the first sub-shell 110 and the second sub-shell 120, with the ramp 130 facing away from the turbine shell 21. This ramp 130 serves as a guide during the process of the shell 100 penetrating the turbine exhaust pipe 24 through the inspection hole 241. Specifically, during the penetration process, the first sub-shell 110 and the second sub-shell 120 need to change their orientation at the inspection hole 241. Since the first sub-shell 110 needs to rotate a certain angle to align with the turbine rotor 23 after it is fully inserted into the turbine exhaust pipe 24, the ramp 130 located at the bend can effectively reduce the jamming or scraping between the outer wall of the shell 100 and the wall of the inspection hole 241, allowing the shell 100 to pass smoothly through the inspection hole 241 during rotation and orientation adjustment, avoiding damage to the hole wall from sharp edges or obstruction of penetration due to interference.

[0051] Optionally, such as Figure 2As shown, a first rolling bearing 140 is provided inside the first sub-shell 110, through which the first shaft segment 210 rotatably passes; a second rolling bearing 150 is provided inside the second sub-shell 120, through which the second shaft segment 220 rotatably passes. By providing the first rolling bearing 140 for the first shaft segment 210 to rotatably pass through in the first sub-shell 110, and the second rolling bearing 150 for the second shaft segment 220 to rotatably pass through in the second sub-shell 120, rotational support can be provided for the first shaft segment 210 and the second shaft segment 220 by means of rolling friction. Compared with the use of sliding bearings or direct shaft-hole fit schemes without bearings, the starting torque of rolling bearings is extremely low, and the dynamic friction torque during rotation is very small and stable. Rolling bearings have extremely small rotational damping, typically less than 0.1 N·m. In the scenario of rotor flexibility testing, the smaller the additional resistance of the rotor flexibility testing device 10 to the rotational motion, the closer the value measured by the rotational torque measuring meter 400 is to the actual rotational torque of the turbine rotor 23. This effectively avoids the problem of measurement deviation caused by excessive frictional resistance of the rotor flexibility testing device 10 itself, leading to the misjudgment of a healthy turbine pump 20 as a fault. At the same time, the rolling bearing has good coaxiality retention capability, which can ensure that the first shaft section 210, the second shaft section 220 and their respective corresponding transmission components 300 maintain a precise fit position, avoiding transmission efficiency fluctuations caused by the wobbling or axial movement of the first and second shaft sections 220, further improving the repeatability and reliability of the test results. Of course, in some other embodiments, one of the first rolling bearing 140 and the second rolling bearing 150 can be used.

[0052] The number of first rolling bearings 140 can be one, two, three, or more. This application embodiment does not impose a specific limitation, as long as they can effectively provide rotational support to the first shaft segment 210 through rolling friction. For example, two first rolling bearings 140 can be provided inside the first sub-housing 110, and these two first rolling bearings 140 are located at the two ends of the first sub-shaft segment.

[0053] Similarly, the embodiments of this application do not impose a specific limitation on the number of second rolling bearings, as long as they can effectively provide rotational support for the second shaft segment 220 by means of rolling friction. For example, two second rolling bearings 150 are provided in the second sub-housing 120, and these two second rolling bearings 150 are located at the two ends of the second sub-shaft segment.

[0054] See also Figure 2A handle 160 is provided at the end of the second sub-shell 120 away from the first sub-shell 110. By providing a handle 160 at the end of the second sub-shell 120 away from the first sub-shell 110, the operator can hold the handle 160 with one hand to fix the shell 100 while rotating the second shaft segment 220, thereby effectively preventing the shell 100 from rotating along with the second shaft segment 220 due to the reaction force of the transmission component 300. This ensures that the first shaft segment 210 and the turbine rotor 23 maintain a stable engagement posture during the measurement process, eliminating measurement errors caused by the shell 100 rotating along with the first shaft segment 220, thereby improving the accuracy of the test results and the ease of operation.

[0055] As an example, the handle 160 may include multiple grip portions spaced circumferentially along the second sub-housing 120, and each grip portion extending radially along the second sub-housing 120. The outer surface of the grip portion may be provided with an anti-slip structure (e.g., knurled or fitted with a rubber sleeve) to increase grip friction and facilitate the application of force. The grip portions may be fixedly connected to the second sub-housing 120 by means of integral molding, welding, or threaded fastening to ensure that the handle 160 does not rotate or loosen relative to each other when subjected to a reaction torque, ensuring long-term reliability.

[0056] Regarding the number of gripping parts, there may be two, three, or more; this application does not impose a specific limitation, as long as they facilitate gripping. For example, two gripping parts are provided at circumferential intervals along the second sub-shell 120.

[0057] like Figure 2 As shown, in some embodiments of this application, the transmission assembly 300 includes a first bevel gear 310 and a second bevel gear 320. The first bevel gear 310 is mounted on a first shaft segment 210, and the second bevel gear 320 is mounted on a second shaft segment 220 and meshes with the first bevel gear 310. During operation, the operator rotates the second shaft segment 220, which drives the second bevel gear 320 to rotate synchronously. The second bevel gear 320 transmits power and rotational motion to the first bevel gear 310 through its meshing relationship with the first bevel gear 310. The first bevel gear 310 then drives the first shaft segment 210 to rotate synchronously. Since the first shaft segment 210 is engaged with the turbine rotor 23, it ultimately drives the turbine rotor 23 to rotate. The second shaft segment 220 is the power input end, and the first shaft segment 210 is the power output end. A pair of bevel gears achieves steering transmission between them, allowing the rotational motion at the input end to be output to the turbine rotor 23 after a 90° reversal. Of course, in some other embodiments, the transmission component 300 may also be a worm gear structure.

[0058] The first bevel gear 310 and the first shaft segment 210, and the second bevel gear 320 and the second shaft segment 220 can be fixedly connected by means of interference fit, key fit, pin connection or screw fastening, so as to ensure that the gear and the shaft segment do not rotate relative to each other when transmitting torque.

[0059] Optionally, the transmission ratio between the first bevel gear 310 and the second bevel gear 320 is set to 1, meaning they have the same number of teeth. This setting has several advantages. First, the two gears have the same number of teeth and pitch circle diameter, eliminating the need for asymmetrical space within the housing 100 for gears with significantly different sizes. This minimizes the radial envelope dimension of the entire transmission assembly 300 at the bend, further reducing the volume of the housing 100 and making the rotor flexibility detection device 10 more compact. Second, a transmission ratio of 1 means the output torque is equal to the input torque. The torque applied by the operator on the second shaft segment 220 remains unchanged after being transmitted through the gear pair to the first shaft segment 210. The torque value measured by the torque meter 400 at the second shaft segment 220 is the actual torque value experienced by the turbine rotor 23, eliminating the need for transmission ratio conversion. This avoids calculation errors introduced by conversion and simplifies the interpretation of measurement readings, facilitating rapid conclusions.

[0060] In some embodiments of this application, the end of the turbine rotor 23 near the turbine exhaust pipe 24 is provided with a non-circular insertion hole, and the end of the first shaft segment 210 that sleeves with the turbine rotor 23 is provided with a connector 230 that is inserted into the insertion hole and whose outer contour matches the insertion hole. Thus, the operator only needs to insert the connector 230 of the first shaft segment 210 axially into the insertion hole at the end of the turbine rotor 23 to complete the sleeve connection; and after the sleeve connection is completed, since both the insertion hole and the connector 230 have non-circular outer contours, when the first shaft segment 210 rotates, the torque can be directly transmitted to the turbine rotor 23 through the contact surface between the inner wall of the insertion hole and the outer contour of the connector 230, allowing the turbine rotor 23 to rotate synchronously with the first shaft segment 210, ensuring the directness and effectiveness of torque transmission. Of course, in other embodiments, the end of the first shaft segment 210 that sleeves with the turbine rotor 23 is provided with an insertion hole, and the end of the turbine rotor 23 near the turbine exhaust pipe 24 is provided with a connector.

[0061] The non-circular structure of the insertion hole includes, but is not limited to, any one or more combinations of polygons (e.g., triangles, quadrilaterals, pentagons, hexagons), strips, waists, ellipses, D-shapes, and splines, as long as the inner wall of the insertion hole has a non-rotationally symmetrical limiting surface that can form a circumferential abutment with the outer contour of the first shaft segment 210 to transmit torque.

[0062] In some embodiments of this application, the second shaft segment 220 is connected to the torque measuring instrument 400 via a quick-connect connector 240. By using the quick-connect connector 240 to connect the second shaft segment 220 and the torque measuring instrument 400, the operator can quickly connect and disconnect the second shaft segment 220 and the torque measuring instrument 400 without the need for tools. Specifically, during the insertion of the rotor flexibility detection device 10 through the inspection hole 241, the torque measuring instrument 400, due to its large size and the potential limitation of external space of the turbine exhaust pipe 24 when inserted with the housing 100, may hinder the insertion operation of the housing 100 or interfere with surrounding pipelines if the two are already fixedly connected before insertion. By using the quick-connect connector 240, the operator can first insert the housing 100 and transmission assembly 300 into place through the inspection hole 241, and then quickly connect the torque measuring instrument 400 to the second shaft section 220 outside the turbine exhaust pipe 24 via the quick-connect connector 240. After the test is completed, the quick-connect connector 240 can be separated to remove the measuring instrument, and then the housing 100 can be pulled out from the inspection hole 241, effectively reducing the space requirements for insertion and removal operations. In addition, the quick-connect connector 240 connection does not require screwing or hammering assembly. When connecting, simply push the two together axially to automatically lock them in place, and when separating, press the unlocking structure to pull it out. The operation is convenient and helps to shorten the preparation and completion time before and after the test, meeting the needs of rapid maintenance.

[0063] As an example, the quick-connect fitting 240 may include a plug-in sleeve, one end of which is fixedly connected to the end of the second shaft segment 220, and the other end of which is inserted into and engaged with the connecting end of the torque measuring instrument 400. The plug-in sleeve and the second shaft segment 220 can be fixedly connected by welding to ensure connection strength and prevent relative rotation; alternatively, an external thread can be provided at the end of the second shaft segment 220, and an internal thread at the corresponding end of the plug-in sleeve, allowing for detachable fixing via threaded connection, facilitating replacement of the quick-connect fitting after wear. The inner wall of the plug-in sleeve may have a snap-fit ​​structure (e.g., an annular groove or elastic buckle), and the connecting end of the torque measuring instrument 400 has a corresponding elastic protrusion or retaining ring. When the connecting end of the torque measuring instrument 400 is axially inserted into the plug-in sleeve to a predetermined position, the elastic protrusion falls into the annular groove, forming an axial limit, achieving quick engagement; when separation is required, pressing the unlock button on the outer wall of the plug-in sleeve causes the elastic protrusion to exit the groove, allowing the measuring instrument to be pulled out axially.

[0064] In some embodiments of this application, the rotor flexibility detection device 10 further includes a monitoring module (not shown in the accompanying drawings). The monitoring module is located on the side of the housing 100 near the turbine rotor 23 and is configured to monitor whether the first shaft segment 210 and the turbine rotor 23 are properly engaged. Because the internal space of the turbine exhaust pipe 24 is narrow and poorly lit, the operator cannot directly observe the engagement status. The monitoring module allows the operator to view the engagement progress in real time on an external terminal, adjust the orientation of the housing 100 in a timely manner, avoid repeated attempts or forced engagement that could damage the mating surfaces, and also prevent slippage due to rotation when the engagement is not properly engaged.

[0065] Optionally, the monitoring module can be an endoscope or a miniature camera, preferably an endoscope, whose lens is fixed to the end of the housing 100 and is set towards the insertion hole of the turbine rotor 23. The endoscope's cable can be wrapped around the first shaft section 210 to avoid cable interference during the installation process. The collected image signals are transmitted to the back-end terminal for real-time display, realizing visual connection operation, reducing operation difficulty, and shortening installation time.

[0066] In some embodiments of this application, the outer peripheral surface of the second sub-shell 120 is also provided with axial angle markings, and the outer peripheral surface of the second sub-shell 120 is provided with axial scale markings. The angle markings are used to indicate the current rotation angle of the first sub-shell 110 in the turbine exhaust pipe 24. After the first sub-shell 110 is fully inserted into the turbine exhaust pipe 24, the operator only needs to rotate the second sub-shell 120 to the predetermined angle marking position based on the external reference point to ensure that the central axis of the first shaft segment 210 is parallel to the centerline of the turbine rotor 23. The scale markings are used to indicate the radial insertion depth of the second sub-shell 120 in the turbine exhaust pipe 24. After the central axis of the first shaft segment 210 is parallel to the centerline of the turbine rotor 23, the operator can use the relative position of the scale markings and the inspection hole 241 opening to know in real time whether the end of the first shaft segment 210 is aligned with the turbine rotor 23, avoiding excessive insertion that could impact the end face of the turbine rotor 23 or insufficient insertion depth that would prevent proper connection. By combining the angle markings and the scale markings, the invisible threading and attitude adjustment operations inside the exhaust pipe can be transformed into externally visible quantitative readings. This reduces reliance on operational experience and feel, minimizes the time spent on repeated attempts and the risk of wear on mating surfaces, and improves the accuracy and efficiency of threading and fitting.

[0067] On the other hand, one embodiment of this application also provides a method for detecting the rotor flexibility of a rocket engine turbopump 20. This rotor flexibility detection method is implemented by the rotor flexibility detection device 10 described in any of the above claims and includes the following steps:

[0068] S100, Open the inspection hole 241 on the turbine exhaust pipe 24, and insert the housing 100 of the rotor flexibility detection device 10 into the turbine exhaust pipe 24 through the inspection hole 241.

[0069] S200, the first shaft segment 210 of the rotor flexibility detection device 10 is fitted onto the turbine rotor 23;

[0070] S300, rotate the second shaft section 220 of the rotor flexibility detection device 10, and during the rotation of the second shaft section 220, use the rotational torque measuring meter 400 of the rotor flexibility detection device 10 to measure the rotational torque of the turbine rotor 23.

[0071] This rotor flexibility testing method eliminates the need to disassemble the entire exhaust pipe assembly and heat exchanger piping, saving the process of disassembling and assembling dozens of fastening bolts and sealing flanges. It is time-saving and requires less work, which can meet the actual needs of intensive launches and rapid maintenance of reusable rocket engines.

[0072] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0073] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A device for detecting the rotor flexibility of a rocket engine turbopump, characterized in that, The rocket engine turbopump includes a turbine housing, a turbine rotor, and a turbine exhaust pipe. The turbine rotor is rotatably disposed within the turbine housing. The turbine exhaust pipe is connected to the turbine housing. An openable and closable inspection port is provided on the circumferential wall of the turbine exhaust pipe near the turbine housing. The rotor flexibility detection device includes: The housing is configured to be inserted into the access hole; A rotating assembly includes a rotating shaft and a transmission assembly. The rotating shaft is rotatably disposed within the housing and includes a first shaft segment and a second shaft segment positioned at an included angle α. The first shaft segment is configured to engage with the turbine rotor. The transmission assembly is disposed within the housing and is drively connected to the first shaft segment and the second shaft segment. The transmission assembly is capable of driving the first shaft segment to rotate when the second shaft segment rotates. A rotational torque meter is located outside the housing and connected to the second shaft segment, the rotational torque meter being configured to measure the rotational torque of the turbine rotor.

2. The rotor flexibility testing device according to claim 1, characterized in that, The central axis of the inspection hole is coplanar with the central axis of the turbine rotor and the two form an angle of 90°. The included angle α is 90°.

3. The rotor flexibility testing device according to claim 1, characterized in that, The outer casing includes a first sub-outer casing and a second sub-outer casing connected at the included angle α, the first shaft segment being rotatably inserted through the first sub-outer casing, and the second shaft segment being rotatably inserted through the second sub-outer casing.

4. The rotor flexibility testing device according to claim 3, characterized in that, An inclined surface is provided at the junction of the first sub-shell and the second sub-shell, and the inclined surface is positioned away from the turbine shell.

5. The rotor flexibility testing device according to claim 3, characterized in that, The first sub-shell is provided with a first rolling bearing, through which the first shaft segment rotatably passes; And / or, the second sub-casing is provided with a second rolling bearing, through which the second shaft segment is rotatably inserted.

6. The rotor flexibility testing device according to claim 3, characterized in that, The second sub-shell has a handle at the end furthest from the first sub-shell.

7. The rotor flexibility testing device according to any one of claims 1 to 6, characterized in that, The transmission assembly includes a first bevel gear and a second bevel gear. The first bevel gear is mounted on the first shaft segment, and the second bevel gear is mounted on the second shaft segment and meshes with the first bevel gear.

8. The rotor flexibility testing device according to any one of claims 1 to 6, characterized in that, The turbine rotor has a non-circular insertion hole at one end near the turbine exhaust pipe and at the end of the first shaft segment that is sleeved with the turbine rotor, and the other end has an insertion connector that is inserted into the insertion hole and whose outer contour is adapted to the insertion hole. And / or, the second shaft segment is connected to the rotational torque meter via a quick-connect fitting.

9. The rotor flexibility testing device according to any one of claims 1 to 6, characterized in that, The rotor flexibility detection device further includes a monitoring module located on the side of the housing near the turbine rotor and configured to monitor whether the first shaft segment is properly fitted onto the turbine rotor.

10. A method for detecting the rotor flexibility of a rocket engine turbopump, characterized in that, The rotor flexibility detection method, implemented by the rotor flexibility detection device as described in any one of claims 1 to 9, comprises: Open the access port on the turbine exhaust pipe and insert the housing of the rotor flexibility testing device into the turbine exhaust pipe through the access port; The first shaft segment of the rotor flexibility detection device is fitted onto the turbine rotor; The second shaft section of the rotor flexibility detection device is rotated, and during the rotation of the second shaft section, the rotational torque of the turbine rotor is measured using the rotational torque measuring meter of the rotor flexibility detection device.

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