Two-stage turbine of liquid rocket engine
By adopting honeycomb damping seal structure and tongue-and-groove connection design in liquid rocket engines, the problems of instability and inconvenience in disassembly and assembly of the turbo pump rotor system are solved, and efficient energy conversion and reliable disassembly and assembly are achieved.
Patent Information
- Application Number
- CN202422449331.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-10
- Publication Date
- 2025-07-04
- Estimated Expiration
- 2034-10-10
AI Technical Summary
The labyrinth sealing structure of existing liquid rocket engines leads to unstable turbo pump rotor system, large loss of gas residual speed, and welding connection between the turbine housing and the outlet pipe is inconvenient for disassembly.
The honeycomb damping seal structure and tongue-and-groove connection design are adopted. The vortex movement is formed through the honeycomb groove to consume kinetic energy, enhance sealing and stability, and realize the removable assembly of the turbine through flange connection.
It improves the efficiency and stability of the turbine, enhances gas energy utilization, and realizes reliable disassembly and assembly of the turbine and efficient energy conversion.
Smart Images
Figure CN223062545U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of liquid rocket engine turbopumps, and particularly relates to a two-stage turbine of a liquid rocket engine. Background Art
[0002] Liquid rocket engines generally use turbines with labyrinth seal forms, and most of them are single-stage cascade turbine disk structures. The turbine housing is connected to the outlet pipe by welding. Due to the use of the labyrinth seal structure, the gas in the seal gap has an obvious circumferential rotational speed, which is likely to cause the risk of overall instability of the engine turbopump rotor system under high-speed conditions. At the same time, the residual velocity loss of the gas is relatively large after passing through the single-stage cascade turbine disk, resulting in low turbine efficiency; and the welding connection structure between the turbine housing and the outlet pipe has the disadvantage of inconvenient disassembly and assembly. Summary of the Utility Model
[0003] The purpose of the utility model is to solve the deficiencies of the above-mentioned prior art, and provide a two-stage turbine structure of a liquid rocket engine with excellent rotor dynamics performance, strong gas seal ability, high efficiency, convenient disassembly and assembly, reusable, and high reliability.
[0004] The technical solution adopted by the utility model to solve its technical problems is as follows.
[0005] Provide a two-stage turbine of a liquid rocket engine, including a turbine housing, two-stage turbine disks, a guide vane ring, and an outlet pipe;
[0006] The outlet pipe is fixed to the turbine housing through an outlet pipe flange and studs, and a tenon groove structure is provided between the outlet pipe and the turbine housing;
[0007] The guide vane ring is located inside the outlet pipe and fixed to the turbine housing; the two-stage turbine disks are located inside the guide vane ring; the outer edge of the two-stage turbine disks is provided with two-stage turbine disk cascades along the radial direction, and two-stage honeycomb damping seal structures are provided on the inner side of the guide vane ring, and the two-stage honeycomb damping seal structures correspond to the two-stage turbine disk cascades; the honeycomb damping seal structure is composed of a plurality of honeycomb grooves provided on the inner side of the guide vane ring.
[0008] In some other embodiments, the honeycomb groove is a regular hexagonal hole with a side length of 0.5 - 5 mm and a depth of 1 - 10 mm.
[0009] Preferably, the distance between adjacent honeycomb grooves of the honeycomb damping seal structure is 1 - 10 mm.
[0010] In some other embodiments, a gasket is provided in the tenon groove structure.
[0011] In some other embodiments, a guide vane ring cascade accommodating cavity is provided between the two-stage turbine disk cascades, and a guide vane ring cascade extending into the guide vane ring cascade accommodating cavity is provided between the two-stage honeycomb damping seal structures.
[0012] In some other embodiments, the turbine housing is composed of a gas collecting ring and a nozzle ring. Nozzles are circumferentially arranged inside the nozzle ring; the gas collecting ring is located on one side of the nozzle ring, and the guide vane ring is fixed to the other side of the nozzle ring through a detachable component.
[0013] In some other embodiments, an outer stop is further provided between the nozzle ring and the guide vane ring for radial positioning.
[0014] Preferably, the detachable component is a guide vane ring flange and a bolt.
[0015] In some other embodiments, the turbine housing is integrally formed by 3D printing.
[0016] In some other embodiments, the guide vane ring is composed of multiple components spliced together.
[0017] This two-stage turbine of the liquid rocket engine can be used in the turbine pump of the liquid rocket engine. Specifically, the turbine pump housing is sleeved on the main shaft of the turbine pump, the turbine pump housing is fixedly connected to the turbine housing, and the two-stage turbine disks are fixedly connected to the main shaft of the turbine pump through involute splines or flange plates.
[0018] The two-stage turbine of the liquid rocket engine of the present utility model arranges a honeycomb damping seal structure, enabling the gas to enter the honeycomb grooves to form a swirling motion and consume kinetic energy, achieving the functions of sealing and improving the stability of the rotor system. Through the flange connection design between the outlet pipe and the turbine housing, the repeated disassembly and assembly of the turbine can be realized. At the same time, this two-stage turbine of the liquid rocket engine arranges two-stage turbine disks, fully utilizes the residual velocity energy of the gas, improves the turbine efficiency, and utilizes the gas energy to output shaft power energy outward and generate partial thrust, effectively enhancing the overall stability of the rotor of the turbine pump of the rocket engine and improving the turbine energy conversion efficiency. Description of the Drawings
[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following drawings are some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.
[0020] Figure 1 It is a partial cross-sectional view of the two-stage turbine of the liquid rocket engine for the embodiment.
[0021] Figure 2The front view of the guide vane ring in the embodiment.
[0022] Figure 3 The sectional view of the guide vane ring in the embodiment.
[0023] Figure 4 The developed schematic diagram of the honeycomb damping seal structure in the embodiment.
[0024] Explanation of the markings in the figure:
[0025] 1 - Gas collecting ring; 2 - Nozzle ring; 3 - Guide vane ring; 301 - First component, 302 - Second component, 303 - Third component; 31 - Guide vane ring flange; 32 - Honeycomb damping seal structure; 321 - First - stage honeycomb damping seal structure; 322 - Second - stage honeycomb damping seal structure; 3201 - Honeycomb groove; 33 - Guide vane ring cascade; 34 - Contact part; 4 - Outlet pipe; 41 - Outlet pipe flange; 5 - Two - stage turbine disk; 51 - First - stage turbine disk cascade; 52 - Second - stage turbine disk cascade; 53 - Guide vane ring cascade accommodation cavity; 6 - Mortise - and - tenon structure; 7 - Bolt; 8 - Stud; 9 - Turbopump housing. Detailed implementation manners
[0026] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are part of the embodiments of the present utility model, rather than all of the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.
[0027] It should also be understood that the terms used in the specification of the present utility model are only for the purpose of describing specific embodiments and are not intended to limit the present utility model. As used in the specification of the present utility model and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" are intended to include the plural forms.
[0028] It should be further understood that the term " / and" as used in the specification of the present utility model and the appended claims refers to any combination and all possible combinations of one or more of the related listed items, and includes these combinations.
[0029] Embodiment
[0030] Please refer to Figures 1-4 The shown two - stage turbine of the liquid rocket engine includes a turbine housing, a guide vane ring 3, an outlet pipe 4 and a two - stage turbine disk 5.
[0031] The turbine housing is composed of a gas collecting ring 1 and a nozzle ring 2. The gas collecting ring 1 and the nozzle ring 2 are integrally formed by 3D printing, reducing the processing procedures and improving the processing accuracy. The inner circumference of the nozzle ring 2 is provided with nozzles along the circumferential direction. The nozzles can be conical or cascade-shaped nozzles, which play the role of reducing the pressure and increasing the speed of the combustion gas.
[0032] The outlet pipe 4 is fixed on the turbine housing. The turbine housing and the outlet pipe 4 are provided with a tenon and mortise structure 6 for radial positioning and sealing functions. Specifically, the outlet pipe 4 is installed and fixed on the turbine housing through a detachable part. In this embodiment, the detachable part is an outlet pipe flange 41 and a stud 8. The outlet pipe flange 41 is located at one end where the outlet pipe 4 is connected to the turbine housing and is an integrally formed part with the outlet pipe 4. It can be understood that, in order to realize the fixed connection between the outlet pipe 4 and the turbine housing, a plurality of studs 8 are arranged at equal intervals along the circumferential direction of the outlet pipe 4 for fixing the turbine housing and the outlet pipe 4, that is, the outlet pipe 4 is installed and fixed on the turbine housing through a plurality of studs 8. In this embodiment, the tenon and mortise structure 6 provided on the turbine housing and the outlet pipe 4 includes a mortise provided on the turbine housing and a tenon provided on the outlet pipe 4 corresponding to the mortise. The quick positioning and installation of the turbine housing and the outlet pipe 4 can be realized through the matching of the mortise and the tenon. A sealing gasket is also provided in the mortise. The sealing gasket is preferably a graphite sealing gasket for the pressing seal of the tenon and mortise structure 6. It can be understood that, in some other embodiments, the mortise can be provided on the outlet pipe 4, and the tenon corresponding to the mortise is provided on the turbine housing.
[0033] The guide vane ring 3 is located inside the outlet pipe 4 and is fixed on the turbine housing. Specifically, the gas collecting ring 1 is located on one side of the nozzle ring 2, and the guide vane ring 3 is fixed on the other side of the nozzle ring 2 through a detachable part. In this embodiment, the guide vane ring 3 is provided with a guide vane ring flange 31, and the guide vane ring flange 31 is an integrally formed part with the guide vane ring 3. The guide vane ring 3 is fixed to the nozzle ring 2 through the guide vane ring flange 31 and a bolt 7. The guide vane ring flange 31 and the bolt 7 are the so-called detachable parts. It can be understood that, in order to realize the fixed connection between the guide vane ring 3 and the nozzle ring 2, a plurality of bolts 7 are arranged at equal intervals along the circumferential direction of the nozzle ring 2 for fixing the guide vane ring 3 and the nozzle ring 2.
[0034] An outer stop is provided between the guide vane ring 3 and the nozzle ring 2 for radial positioning. In this embodiment, the outer stop is provided on the nozzle ring 2, and an abutting portion 34 matching the outer stop is provided on the guide vane ring 3. The quick positioning and installation of the nozzle ring 2 and the guide vane ring 3 can be realized through the matching of the outer stop and the abutting portion 34. It can be understood that, in some other embodiments, the outer stop can be provided on the guide vane ring 3, and the abutting portion 34 matching the outer stop is provided on the nozzle ring 2.
[0035] The guide vane ring 3 can be composed of a plurality of components spliced together. In this embodiment, the guide vane ring 3 is integrally processed and then divided into three components by wire cutting, such as Figure 2As shown, the guide vane ring 3 is composed of a first component 301, a second component 302, and a third component 303 spliced together, and the central angle of each component is 120°. The outer stop positioning and the splicing structure of the three components are conducive to the installation and disassembly of the guide vane ring 3.
[0036] On the inner side of the guide vane ring 3, there is a two-stage honeycomb damping seal structure 32, and the honeycomb damping seal structure 32 is composed of a plurality of honeycomb grooves 3201 arranged on the inner side of the guide vane ring (as Figure 4 shown); the honeycomb groove is a regular hexagonal hole with a side length of 0.5 - 5 mm and a depth of 1 - 10 mm, and the distance between adjacent honeycomb grooves is 1 - 10 mm. In this embodiment, the honeycomb groove is a regular hexagonal hole with a side length of 1.15 mm and a depth of 3 mm, and the distance between adjacent honeycomb grooves is specifically 2.5 mm.
[0037] The honeycomb damping seal structure 32 is composed of a series of regularly arranged honeycomb grooves 3201. Its function is that when the gas passes through the top clearance of the two-stage turbine disk 5 blade cascade, the gas enters the honeycomb groove 3201 to form a vortex motion and consume kinetic energy, achieving a sealing effect. Its advantages are low gas leakage, and since the honeycomb grooves 3201 densely distributed in the circumferential and axial directions block the circumferential motion of the gas in the clearance, reducing the action of fluid cross-excitation force, effectively enhancing the stability of the turbine pump rotor system.
[0038] As Figure 3 shown, the two-stage honeycomb damping seal structure 32 is respectively a first-stage honeycomb damping seal structure 321 and a second-stage honeycomb damping seal structure 322, and there is a guide vane ring blade cascade 33 between the first-stage honeycomb damping seal structure 321 and the second-stage honeycomb damping seal structure 322.
[0039] The two-stage turbine disk 5 is located inside the guide vane ring 3. Along the radial direction on the outer edge of the two-stage turbine disk 5, there are two-stage turbine disk blade cascades, namely a first-stage turbine disk blade cascade 51 and a second-stage turbine disk blade cascade 52, and a guide vane ring blade cascade accommodation cavity 53 is formed between the first-stage turbine disk blade cascade 51 and the second-stage turbine disk blade cascade 52. Among them, the first-stage turbine disk blade cascade 51 corresponds to the first-stage honeycomb damping seal structure 321, the second-stage turbine disk blade cascade 52 corresponds to the second-stage honeycomb damping seal structure 322, and the guide vane ring blade cascade 33 extends into the guide vane ring blade cascade accommodation cavity 53.
[0040] The working mode of the two-stage turbine of this liquid rocket engine is as follows: High-temperature gas enters the gas collecting ring 1. After being rectified by the gas collecting ring 1, it is distributed to the nozzles inside the nozzle ring 2. The gas expands rapidly in the nozzles, with the temperature and pressure decreasing and the velocity increasing, and the thermal energy is converted into kinetic energy. Then, the high-speed gas enters the cascade channels of the two-stage turbine disk 5 to do work, driving the two-stage turbine disk 5 to rotate at high speed. The cascade channels of the guide vane ring in the middle of the two-stage turbine disk 5 play a role in deflecting the gas flow. A small part of the gas enters the hole-type damping seal gap between the two-stage turbine disk 5 and the guide vane ring 3. The honeycomb damping seal structure plays a role in sealing the gas, reducing the leakage amount, resisting the gas excitation force and stabilizing the rotor system. Finally, the gas flowing out of the cascade channels of the two-stage turbine disk 5 enters the outlet pipe 4, continues to expand and accelerate, is discharged from the outlet pipe 4 into the environment, and generates part of the thrust. By making full use of the gas energy, the two-stage turbine of this liquid rocket engine outputs shaft power energy outward, generates part of the thrust, and effectively enhances the overall stability of the turbine pump rotor of the rocket engine and improves the turbine energy conversion efficiency.
[0041] The two-stage turbine of the liquid rocket engine in this embodiment can be used for the turbine pump of the liquid rocket engine. Specifically, the turbine pump housing 9 is sleeved on the main shaft of the turbine pump, and the turbine pump housing 9 is fixedly connected to the turbine housing (as Figure 1 shown). The two-stage turbine disk 5 and the main shaft of the turbine pump are fixedly connected by involute splines or flange plates. The rotation of the two-stage turbine disk 5 can drive the rotation of the main shaft of the turbine pump, playing a role in reliably transmitting torque.
[0042] As mentioned above, the above are only the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of various equivalent modifications or substitutions, and these modifications or substitutions should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims
1. A two-stage turbine for a liquid rocket engine, characterized in that, It includes a turbine housing, a two-stage turbine disk, a guide vane ring and an outlet pipe; The said outlet pipe is fixed to the turbine housing through an outlet pipe flange and studs, and a tenon and mortise structure is provided between the outlet pipe and the turbine housing; The said guide vane ring is located inside the outlet pipe and fixed to the turbine housing; the two-stage turbine disk is located inside the guide vane ring; on the outer edge of the two-stage turbine disk, two-stage turbine disk cascades are provided radially, and on the inner side of the guide vane ring, two-stage honeycomb damping seal structures are provided, and the two-stage honeycomb damping seal structures correspond to the two-stage turbine disk cascades; the honeycomb damping seal structure consists of a plurality of honeycomb grooves provided on the inner side of the guide vane ring.
2. The two-stage turbine of the liquid rocket engine according to claim 1, wherein, The said honeycomb groove is a regular hexagonal hole with a side length of 0.5 - 5 mm and a depth of 1 - 10 mm.
3. The two-stage turbine of the liquid rocket engine according to claim 2, characterized in that, The distance between adjacent honeycomb grooves of the honeycomb damping seal structure is 1 - 10 mm.
4. The two-stage turbine of a liquid rocket engine according to claim 1, characterized in that, A gasket is provided inside the tenon and mortise structure.
5. The two-stage turbine of the liquid rocket engine according to claim 1, characterized in that, A guide vane ring cascade accommodation cavity is provided between the two-stage turbine disk cascades, and a guide vane ring cascade extending into the guide vane ring cascade accommodation cavity is provided between the two-stage honeycomb damping seal structures.
6. The two-stage turbine of the liquid rocket engine according to claim 1, wherein, The said turbine housing consists of a gas collecting ring and a nozzle ring, and nozzles are provided circumferentially inside the nozzle ring; the gas collecting ring is located on one side of the nozzle ring, and the guide vane ring is fixed to the other side of the nozzle ring through a detachable part.
7. The two-stage turbine of the liquid rocket engine according to claim 6, characterized in that, An outer stop is also provided between the nozzle ring and the guide vane ring for radial positioning.
8. The two-stage turbine of a liquid rocket engine according to claim 6, characterized in that, The said detachable part is a guide vane ring flange and bolts.
9. The two-stage turbine of the liquid rocket engine according to claim 6, characterized in that, The said turbine housing is integrally formed by 3D printing.
10. The two-stage turbine of a liquid rocket engine according to claim 1, wherein The said guide vane ring is composed of a plurality of components spliced together.