Turbine structure and turbine pump

Abstract

The application provides a turbine structure and a turbine pump, which at least comprise a turbine shell, a nozzle grid ring, a double-stage turbine disc, a first turbine sealing ring, a guide ring, a second turbine sealing ring and a connecting structure. Under the premise of ensuring high efficiency and high reliability of the turbine, the nozzle grid ring and the double-stage turbine disc are installed in the turbine shell, the second turbine sealing ring, the guide ring and the first turbine sealing ring are all fixedly installed in the turbine shell through the connecting structure, the double-stage turbine disc and the nozzle grid ring are sealingly installed in the turbine shell, and thus the assembly of the turbine structure is completed. When a fault occurs in the engine test process and turbine blade ablation may occur, the engine does not need to be removed from the test bench, the guide ring and the two turbine sealing rings can be all removed by disassembling the connecting mechanism, so that the fault cause can be quickly judged, and the fault diagnosis and maintenance of the turbine disc and the nozzle grid ring are very beneficial.

Description

Technical Field

[0001] This invention relates to the field of rocket engine technology, and in particular to a turbine structure and a turbopump. Background Technology

[0002] As a key component of the turbopump in a pump-fed liquid rocket engine, the turbine's main function is to accelerate the high-temperature, high-pressure gas from the generator, generate a high-speed airflow to drive the rotating blades, output shaft power, and provide power to the centrifugal pump.

[0003] For medium-power turbines in open-cycle systems, single-stage and two-stage impulse turbines can be used. Two-stage impulse turbines fully utilize the residual velocity at the first-stage rotor outlet; after being deflected by the second-stage guide vanes, the combustion gas continues to impact the second-stage rotor, resulting in significantly higher efficiency than single-stage impulse turbines. However, the structure of a two-stage impulse turbine is more complex.

[0004] The turbine of a cryogenic liquid rocket engine is in a complex environment of high temperature, high pressure, high speed, low temperature and vibration. Designers must not only ensure the advanced performance of the turbine, but also ensure the simplicity of the turbine structure, its reliability and the feasibility of fault diagnosis. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention proposes a turbine structure and a turbine pump. Without compromising high efficiency, the overall structural layout is optimized, resulting in better manufacturability, assembly, and disassembly of each component, and enhancing product interchangeability and fault diagnosis capabilities.

[0006] One aspect of the present invention provides a turbine structure, including a turbine housing, a nozzle vane ring, a two-stage turbine disk, a first turbine sealing ring, a guide ring, a second turbine sealing ring, and a connecting structure; the nozzle vane ring and the two-stage turbine disk are coaxially disposed within the turbine housing, and the blade channel of the nozzle vane ring is used to accelerate the combustion gas to generate a high-speed airflow, thereby driving the two-stage turbine disk to output shaft power; the two-stage turbine disk includes a rotating disk, and a first-stage moving blade and a second-stage moving blade coaxially disposed on the outer periphery of the rotating disk; the blade channel of the guide ring is disposed between the first-stage moving blade channel and the second-stage moving blade channel, and the outer ring portion of the guide ring is disposed between the first turbine sealing ring and the second turbine sealing ring; the connecting structure passes sequentially through the second turbine sealing ring, the guide ring, and the first turbine sealing ring and is connected to the turbine housing, thereby enclosing the two-stage turbine disk and the nozzle vane ring within the turbine housing.

[0007] In one embodiment, the turbine housing includes: a gas bend, a gas collecting ring, a first starting boss, and a second starting boss; the gas bend communicates with one radial outer wall of the gas collecting ring, and the other outer wall of the gas collecting ring is provided for communication between the first starting boss and the second starting boss; flanges are provided at both axial ends of the gas collecting ring; the height of the first starting boss and the second starting boss is not greater than the height of the flange.

[0008] In one embodiment, the first starting boss is used to connect to the gunpowder starter, and its orifice is matched with that of the gunpowder starter; the second starting boss is equipped with flanges of different orifice sizes to facilitate connection with starting valves for various gases.

[0009] In one embodiment, the guide ring includes three sector rings of equal area; each sector ring has a plurality of mounting holes on its radial periphery; the connecting structure is connected to the turbine housing by passing through the second turbine sealing ring, each of the mounting holes and the first turbine sealing ring in sequence, thereby assembling the three sector rings into the guide ring.

[0010] In one embodiment, the fan-shaped ring is provided with a plurality of blades in a circumferential direction, and the number of blades in the fan-shaped ring is an integer of 3; the fan-shaped ring is provided with sealing teeth on its radially inner side facing away from the blades.

[0011] In one embodiment, the first turbine sealing ring and the second turbine sealing ring have the same structure.

[0012] In one embodiment, the blade channel height of the nozzle vane ring is less than the height of the primary moving blade channel, which is less than the blade channel height of the guide ring, which is less than the height of the secondary moving blade channel.

[0013] In one embodiment, the tip of the primary moving blade is provided with a first tip band, and the tip of the secondary moving blade is provided with a second tip band; the outer diameters of the first tip band and the second tip band are the same.

[0014] In one embodiment, the connection structure includes a double-ended stud and a high-temperature self-locking nut; one end of the double-ended stud connects the second turbine sealing ring, the guide ring, the first turbine sealing ring and the gas collecting ring, and the other end is locked to the high-temperature self-locking nut.

[0015] Another aspect of the present invention provides a turbopump. This turbopump includes any of the turbine structures described in the above embodiments.

[0016] The turbine structure and turbine pump proposed in this invention have at least the following advantages:

[0017] 1. The turbine has high efficiency, a simple overall layout, a compact structure, and strong feasibility for fault diagnosis.

[0018] 2. It can simultaneously use gas starter and gunpowder starter to start the engine multiple times, or when the gunpowder starter fails or there is insufficient gunpowder, it can be directly replaced with gas starter.

[0019] 3. The integrated tuning fork dual-stage turbine disk has good strength and rigidity, a large margin of critical speed of the shaft system, and stable and reliable shaft system.

[0020] 4. The processing, assembly, and disassembly of its components are of good quality.

[0021] 5. The components are highly interchangeable and the cost is low.

[0022] Upon reading the detailed embodiments and examining the accompanying drawings, those skilled in the art will recognize additional features and advantages. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a cross-sectional view of the turbine structure of an embodiment of the present invention, cut along the diameter of the gas bend.

[0025] Figure 2 This is a schematic cross-sectional view of the turbine housing according to an embodiment of the present invention.

[0026] Figure 3 This is a schematic diagram of the overall structure of the turbine housing according to an embodiment of the present invention.

[0027] Figure 4 This is a schematic diagram of the sector-shaped ring that forms the guide ring in an embodiment of the present invention.

[0028] Figure 5 This is a schematic diagram of the structure of the first-stage moving blade and the second-stage moving blade in an embodiment of the present invention. Detailed Implementation

[0029] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.

[0030] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" 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 direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0031] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0032] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to refer to similar elements.

[0033] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0034] See Figure 1This invention provides a turbine structure, including a turbine housing 1, a nozzle vane ring 2, a two-stage turbine disk 3, a first turbine sealing ring 4, a guide ring 5, a second turbine sealing ring 6, and a connecting structure 7. The nozzle vane ring 2 and the two-stage turbine disk 3 are coaxially disposed within the turbine housing 1. The blade passage A of the nozzle vane ring 2 is used to accelerate the combustion gas to generate a high-speed airflow, driving the two-stage turbine disk 3 to rotate and accelerate, thereby continuously outputting shaft power. The two-stage turbine disk 3 includes a rotating disk 31, and a first-stage moving blade 32 and a second-stage moving blade 33 coaxially disposed on the outer periphery of the rotating disk 31. The first-stage moving blade 32 is closer to the nozzle vane ring 2 than the second-stage moving blade 33.

[0035] In an embodiment of the present invention, the nozzle vane ring 2, the two-stage turbine disk 3, the first turbine sealing ring 4, the guide ring 5, and the second turbine sealing ring 6 are all coaxially arranged.

[0036] Furthermore, the blade passage D of the guide ring 5 is located between the first-stage moving blade passage B and the second-stage moving blade passage C. That is, the guide ring 5 is partially positioned between the first-stage moving blade 32 and the second-stage moving blade 33, and there is a certain distance between the inner ring surface of the guide ring 5 and the turntable 31 to ensure that the guide ring, the first-stage moving blade, and the second-stage moving blade can rotate independently to continuously accelerate the working medium. When assembling the turbine structure of the engine, the first turbine sealing ring 4 and the second turbine sealing ring 6 can be arranged back-to-back, and the outer ring of the guide ring 5 can be positioned between the first turbine sealing ring 4 and the second turbine sealing ring 6, mating together to form a sealing structure. Then, by placing the side of the first turbine sealing ring 4 away from the guide ring 5 close to the turbine housing 1, the connecting structure 7 passes sequentially through the second turbine sealing ring 6, the guide ring 5, and the first turbine sealing ring 4 and connects to the turbine housing 1, thereby completely enclosing the two-stage turbine disk 3 and the nozzle vane ring 2 within the turbine housing 1.

[0037] Given the complexity of existing turbine structures and the significant difficulties in installation and disassembly, during engine testing, if a problem is suspected or confirmed with the two-stage turbine disk or nozzle vane rings, the engine must be removed from the test stand and transported back to the manufacturing plant for disassembly. Traditional turbine structures not only involve cumbersome turbine housing disassembly but also disrupt engine testing schedules, resulting in substantial manpower and material costs.

[0038] To address the aforementioned technical problems, this invention provides a turbine structure that facilitates assembly and disassembly. While ensuring high turbine efficiency and reliability, the second turbine sealing ring, guide ring, and first turbine sealing ring can be fixedly installed in the turbine housing via a connecting structure, forming a seal between them. This seal securely mounts the two-stage turbine disk and nozzle vane ring within the turbine housing, completing the turbine structure assembly. When the turbine structure of this invention malfunctions during engine testing, and turbine blade erosion or nozzle vane ring damage is suspected, it is unnecessary to remove the engine from the test stand. The guide ring and both turbine sealing rings can be removed by disassembling the connecting mechanism, allowing for rapid fault diagnosis and repair of the turbine disk and nozzle vane ring.

[0039] Regarding the feasibility of fault diagnosis, the turbine structure of this embodiment of the invention can be used to diagnose faults in the turbine disk and nozzle blade ring by visual inspection or endoscopy simply by removing the connecting structure and guide ring.

[0040] In one embodiment of the present invention, the two-stage turbine disk 3 needs to withstand strong centrifugal force and thermal stress, therefore its structural strength directly affects the stability of the entire turbine pump shaft system. The two-stage turbine disk in this embodiment of the present invention is optimized by adopting a tuning fork-integrated two-stage turbine disk, which has a simple and reliable structure, excellent strength performance, and the integrated turbine disk is very beneficial for assembly.

[0041] See also Figure 2 and Figure 3 Furthermore, the turbine housing includes a gas bend 11, a gas collecting ring 12, a first starting boss 13, and a second starting boss 14, all integrally cast. The gas bend 11 communicates with one radial outer wall of the gas collecting ring 12, while the other outer wall of the gas collecting ring 12 provides communication between the first starting boss 13 and the second starting boss 14. Both starting bosses can be used entirely for connection to the starting valve, entirely for connection to the propellant starter, or one can be used to connect to the starting valve and the other to the propellant starter. Therefore, during engine testing, whether there is insufficient propellant or a problem with one of the starting bosses, the other starting boss can be used for propellant or gas starting.

[0042] Furthermore, flanges are provided at both ends of the gas collecting ring 12 along its axial direction for installation with other components, such as the cryogenic housing. The heights of the first starting boss 13 and the second starting boss 14 are no greater than the height of the flanges on the gas collecting ring 12, thus not occupying axial and radial space in the turbine structure, allowing for a more compact turbine layout. Moreover, each starting boss can also provide auxiliary support for structures such as valves.

[0043] It should be noted that the gas collecting ring 12 has a gas collecting ring cavity, and the gas bend pipe 11 is connected to the gas collecting ring cavity. Both can have the same flow area to ensure that the gas can flow evenly downstream.

[0044] In the above embodiment, the first starting boss 13 is used for communication with the gunpowder starter, and its orifice diameter is matched with that of the gunpowder starter. The second starting boss 14 is equipped with flanges of different orifice diameters to facilitate communication with starting valves for various gases, thereby adapting to the characteristics of different gases. Typically, nitrogen is the gas commonly used for gas starting.

[0045] The inner holes connecting the two starting bosses to the gas collecting ring are directly machined during machining. The position and diameter of the inner holes can be adaptively adjusted according to changes in the turbine starting method, making the structure highly adaptable.

[0046] The turbine structure of this invention features two starting bosses on the gas collecting ring. The first starting boss is used to assemble a propellant starter, and the second starting boss is used to assemble a starting valve. When the propellant starter malfunctions or there is insufficient propellant, the starting valve can be directly installed on the second starting boss, thereby starting the engine using gas. Furthermore, the second starting boss for mounting the gas starter is equipped with flanges of different bore diameters, accommodating various gas filling methods, completely eliminating problems such as test delays caused by insufficient starting medium or starting boss malfunction.

[0047] It should be noted that the two starting bosses in the embodiments of the present invention can also directly realize multiple starts of the engine, and can also realize a starting method that combines gunpowder starting and nitrogen starting during the same hot test.

[0048] In the above embodiment, the nozzle vane ring 2 is located at the opening of the gas collecting ring 12 away from the gas bend 11. The blades of the nozzle vane ring 2 are in the form of Laval nozzles. The gas expands and accelerates through the Laval nozzles to generate a high-speed airflow, which drives the first-stage and second-stage moving blades to rotate, thereby further accelerating the high-speed airflow.

[0049] In this embodiment of the invention, the nozzle blade ring 2 is processed using 3D printing technology and is connected to the gas collecting ring 12 by electron beam welding.

[0050] The supersonic expansion section of the nozzle in the nozzle vane ring 2 is designed using the two-dimensional feature line method. This method allows for a shorter axial length of the nozzle and a parallel, uniform flow at the nozzle outlet, significantly improving nozzle efficiency.

[0051] See also Figure 1 , Figure 2 and Figure 4In one embodiment, to facilitate the installation and disassembly of the guide ring, the guide ring can be divided into three sector rings 51 of equal area. Each sector ring 51 has multiple mounting holes 511 on its radial periphery. The connecting structure 7 passes through the second turbine sealing ring 6, the mounting holes 511 of each sector ring 51, and the first turbine sealing ring 4 in sequence and then connects to the gas collecting ring 12, thereby enabling the three sector rings 51 to be assembled into a complete guide ring 5.

[0052] In the embodiments of the present invention, the guide ring 5 adopts a segmented casting scheme, which not only enables mass production, but also allows the guide ring 5 composed of three sector rings 51 to be flexibly installed, disassembled and repaired, and their structures are interchangeable.

[0053] In the above embodiment, the fan-shaped ring 51 is provided with multiple blades 512 circumferentially, and its inner blade profile is a double-circular arc symmetrical blade profile, which is simple and reliable in structure. The blades 512 mainly serve a guiding function. In order to ensure the aerodynamic performance of the turbine, the number of blades can be set to an integer multiple of 3.

[0054] Furthermore, in order to reduce the leakage of gas between the inner surface of the guide ring and the outer surface of the turbine disk, sealing teeth 513 can be provided on the radially inner side (inner surface) of the sector ring 51, facing away from the blade 512. This arrangement can reduce gas leakage, improve turbine work capacity, and increase turbine efficiency by 0.5 percentage points.

[0055] See also Figure 1 , Figure 2 and Figure 5 In any of the above embodiments, during engine operation, the working medium (gas) flows sequentially through the gas bend 11, the gas collecting chamber 12, the blade passage A of the nozzle vane ring, the first-stage moving blade passage B, the blade passage D of the guide ring, and the second-stage moving blade passage C. To meet the need for further enhanced compression of the gas already compressed to a certain degree, the height of the blade passage A of the nozzle vane ring can be less than the height of the first-stage moving blade passage B, less than the height of the blade passage D of the guide ring, and less than the height of the second-stage moving blade passage C.

[0056] Furthermore, in this embodiment of the invention, the turbine sealing ring is machined, making the first turbine sealing ring 4 and the second turbine sealing ring 6 structurally identical and interchangeable. The first turbine sealing ring 4 is located on the radial periphery of the first-stage moving blade 32, and the second turbine sealing ring 6 is located on the radial periphery of the second-stage moving blade 33. The guide ring 5, after being assembled with the first turbine sealing ring 4 and the second turbine sealing ring 6, achieves a seal to prevent the leakage of combustion gas from the first-stage moving blade passage B, the blade passage D of the guide ring, and the second-stage moving blade passage C.

[0057] Since the two turbine sealing rings have the same structure, it is not necessary to specifically distinguish between the first and second turbine sealing rings when assembling the turbine housing. The two turbine sealing rings can be placed back-to-back around the outer periphery of the first-stage and second-stage moving blades, respectively. The turbine sealing rings of this invention have excellent replaceability, which is highly beneficial for design, commissioning, production, acceptance, assembly, and maintenance replacement. It can significantly simplify the assembly process and reduce product design costs.

[0058] In the above embodiment, since the length of the second-stage moving blade is greater than that of the first-stage moving blade, a first blade tip shroud 321 can be provided at the tip of the first-stage moving blade 32, and a second blade tip shroud 331 can be provided at the tip of the second-stage moving blade 33. The outer diameters of the first and second blade tip shrouds 321 and 331 are the same. That is, although the lengths of the first-stage and second-stage moving blades 32 and 33 are different, the use of blade tip shrouds with the same outer diameter corrects the length difference, making the spacing between each blade tip shroud and its corresponding turbine sealing ring the same. Therefore, the sealing effect of the two turbine sealing rings is essentially the same. The technical analysis and effects of this section require confirmation from the inventor.

[0059] This configuration ensures turbine efficiency while reducing tip clearance leakage, and also guarantees that the first turbine sealing ring 4, located around the first-stage moving blade 32, and the second turbine sealing ring 6, located around the second-stage moving blade 33, have identical structures, making the two turbine sealing rings interchangeable.

[0060] Based on the characteristics of the turbine structure in this embodiment of the invention, turbine sealing performance can be further improved by replacing turbine sealing rings with different inner diameters to adjust the gap between the first blade top shroud and the first turbine sealing ring, as well as the gap between the second blade top shroud and the second turbine sealing ring.

[0061] Furthermore, the first and second blade top shrouds are machined to ensure the blade tip clearance while improving the rigidity of the turbine disk.

[0062] See Figure 2 In one embodiment, the connecting structure 7 includes a double-ended stud 71 and a high-temperature self-locking nut 72. The outer rings of the second turbine sealing ring, guide ring, and first turbine sealing ring are all provided with pin holes matching the double-ended stud 71 for radial positioning and assembly. Specifically, one end of the double-ended stud passes sequentially through the pin holes of the second turbine sealing ring, guide ring, and first turbine sealing ring and connects to the gas collecting ring; the other end is screwed into the high-temperature self-locking nut, which is then tightened using torque quantization control. Torque quantization control not only ensures the high-temperature self-locking nut is tightened but also ensures that the various connected components are subjected to uniform force.

[0063] The above embodiments can be combined with each other and have corresponding technical effects.

[0064] Another aspect of the present invention provides a turbopump. This turbopump includes any of the turbine structures described in the above embodiments. The turbopump of the present invention, while ensuring high turbine efficiency and advanced performance, makes the overall turbine structure simpler and more reliable, facilitates component processing, assembly, and disassembly, and has strong fault diagnosis feasibility, truly achieving high-efficiency assembly, rapid disassembly, and timely fault diagnosis. Furthermore, components with the same structure but different installation positions (or different functions) have strong interchangeability, reducing the difficulty of turbopump structural design while significantly reducing design costs.

[0065] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A turbine structure, characterized in that, It includes at least a turbine housing, a nozzle vane ring, a two-stage turbine disk, a first turbine sealing ring, a guide ring, a second turbine sealing ring, and a connecting structure; The nozzle vane ring and the dual-stage turbine disk are coaxially disposed within the turbine housing. The blade channel of the nozzle vane ring is used to accelerate the gas to generate a high-speed airflow, which drives the dual-stage turbine disk to output shaft power. The two-stage turbine disk includes a turntable, and a first-stage moving blade and a second-stage moving blade coaxially disposed on the outer periphery of the turntable; The blade channel of the guide ring is disposed between the first-stage moving blade channel and the second-stage moving blade channel, and the outer ring of the guide ring is disposed between the first turbine sealing ring and the second turbine sealing ring; the connecting structure passes through the second turbine sealing ring, the guide ring and the first turbine sealing ring in sequence and is connected to the turbine housing, thereby enclosing the two-stage turbine disk and the nozzle blade ring inside the turbine housing; The turbine housing includes: a gas bend, a gas collecting ring, a first starting boss, and a second starting boss; The gas bend is connected to one side of the outer wall of the gas collecting ring in the radial direction, and the other side of the outer wall of the gas collecting ring is provided for the first starting boss and the second starting boss to communicate with each other; The gas collecting ring is provided with flanges at both ends of the axial direction, and the height of the first starting boss and the second starting boss is not greater than the height of the flange; The first starting boss is used to communicate with the gunpowder starter, and the second starting boss is used to communicate with the gas starting valve.

2. The turbine structure according to claim 1, characterized in that, The first starting boss is used to connect the gunpowder starter, and its aperture is matched with that of the gunpowder starter. The second starting boss is equipped with flanges of different orifice diameters to facilitate connection with starting valves for various gases.

3. The turbine structure according to claim 1, characterized in that, The guide ring includes three sector rings of equal area; each sector ring has multiple mounting holes on its radial periphery; The connection structure is connected to the turbine housing by passing through the second turbine sealing ring, each of the mounting holes and the first turbine sealing ring in sequence, and assembling the three sector rings into the guide ring.

4. The turbine structure according to claim 3, characterized in that, The fan-shaped ring is provided with multiple blades in a circumferential direction, and the number of blades in the fan-shaped ring is an integer of 3; The fan-shaped ring has sealing teeth on its radially inner side, facing away from the fan-shaped ring blades.

5. The turbine structure according to claim 1, characterized in that, The blade channel height of the nozzle blade ring is less than the height of the primary moving blade channel, which is less than the height of the blade channel of the guide ring, which is less than the height of the secondary moving blade channel.

6. The turbine structure according to claim 5, characterized in that, The first turbine sealing ring has the same structure as the second turbine sealing ring.

7. The turbine structure according to claim 6, characterized in that, The tip of the primary moving blade is provided with a first tip band, and the tip of the secondary moving blade is provided with a second tip band. The outer diameters of the first and second blade top circumferences are the same. The first blade top shroud and the first turbine sealing ring cooperate to form a dynamic seal, and the second blade top shroud and the second turbine sealing ring cooperate to form a dynamic seal.

8. The turbine structure according to claim 1, characterized in that, The connection structure includes a double-ended stud and a high-temperature self-locking nut; One end of the double-ended stud connects the second turbine sealing ring, the guide ring, the first turbine sealing ring, and the gas collecting ring, while the other end is locked by the high-temperature self-locking nut.

9. A turbopump, characterized in that, Includes the turbine structure as described in any one of claims 1 to 8.

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