Space turbine device with exhaust flow guide cone and tubular heat exchanger
By introducing exhaust cone and tube heat exchanger into the turbine device of the liquid rocket engine, the problems of gas flow disorder and thermal energy loss are solved, and efficient utilization of gas energy and the improvement of turbine efficiency are achieved.
Patent Information
- Application Number
- CN202422450380.0
- 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
In the turbine device of liquid rocket engines, gas flow disorder in the outlet pipe causes a decrease in turbine efficiency, and high-temperature gas is directly discharged into the surrounding environment, causing heat and kinetic energy loss.
A space turbine device with exhaust cone and tube heat exchanger is designed. By setting a diversion cone and tube heat exchanger in the outlet pipe, the diversion cone guides the gas into the straight pipe section of the outlet pipe, and the tube heat exchanger absorbs gas heat energy and improves energy conversion efficiency.
Effectively utilize gas energy, reduce flow and heat energy losses, improve turbine energy conversion efficiency, and enhance device stability and energy output.
Smart Images
Figure CN223062499U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of liquid rocket engine turbopumps, in particular to a space turbine device with an exhaust guide cone and a tube heat exchanger. Background Art
[0002] At present, liquid rocket engines generally adopt an outlet pipe structure with an open turbine. After the gas flows out from the narrow cascade channel, it directly enters the open space of the outlet pipe. Since there is no flow guiding device in the outlet pipe, the gas flow in the outlet pipe is relatively disordered, which further affects the flow in the upstream cascade channel and leads to a decrease in turbine efficiency. At the same time, the high-temperature gas in the outlet pipe is directly discharged into the surrounding environment, resulting in losses of gas thermal energy and kinetic energy.
[0003] In view of the above problems, the utility model provides a space turbine device with an exhaust guide cone and a tube heat exchanger. Summary of the Utility Model
[0004] In order to solve the above technical problems, the utility model aims to propose a space turbine device with an exhaust guide cone and a tube heat exchanger, which has strong gas flow guiding ability, high turbine energy conversion efficiency, and stable and reliable operation. The purpose of the utility model is achieved by the following technical solutions:
[0005] Provide a space turbine device with an exhaust guide cone and a tube heat exchanger, including a turbine housing, a guide vane seal ring, an outlet pipe, two-stage turbine disks, and an exhaust guide cone; the turbine housing is composed of a gas collecting ring and a nozzle ring connected to each other, the guide vane seal ring is arranged on the nozzle ring, the outlet pipe is welded to the nozzle ring, a tube heat exchanger is arranged in the outlet pipe, the two-stage turbine disks are arranged between the turbine housing and the outlet pipe, and the exhaust guide cone is welded to the two-stage turbine disks.
[0006] Preferably, the gas collecting ring and the nozzle ring are integrally formed by 3D printing.
[0007] Furthermore, nozzles are arranged circumferentially along the inner side of the nozzle ring, and the nozzles are conical or cascade-shaped.
[0008] Furthermore, a flange structure and bolts are arranged between the guide vane seal ring and the nozzle ring, and the guide vane seal ring is fixed on the nozzle ring through the flange structure and bolts.
[0009] Furthermore, the space turbine device with an exhaust guide cone and a tube heat exchanger further includes a turbine main shaft, and the turbine main shaft is fixedly connected to the two-stage turbine disks.
[0010] Furthermore, the turbine main shaft and the two-stage turbine disks are connected through an involute spline structure or a flange disk structure.
[0011] Further, the guide vane seal ring is evenly divided into three segments along the circumferential direction.
[0012] Further, an outlet is provided at one end of the outlet pipe away from the nozzle ring, and an outlet pipe throat is provided at a position close to the outlet inside the outlet pipe.
[0013] Further, the aerospace turbine device with an exhaust gas deflector cone and a tube heat exchanger further includes a cascade passage, and the cascade passage is arranged inside the two-stage turbine disk.
[0014] Preferably, a non-contact mechanical seal gap is further provided between the two-stage turbine disk and the guide vane seal ring.
[0015] Further, the aerospace turbine device with an exhaust gas deflector cone and a tube heat exchanger further includes a diversion passage, and the diversion passage is arranged between the outlet pipe and the exhaust gas deflector cone.
[0016] Further, an outlet pipe straight section is provided inside the outlet pipe, the diversion passage is connected to the outlet pipe straight section, and the tube heat exchanger is arranged in the outlet pipe straight section.
[0017] The beneficial effects compared with the prior art are as follows:
[0018] The present utility model provides an aerospace turbine device with an exhaust gas deflector cone and a tube heat exchanger. By arranging the exhaust gas deflector cone, the combustion gas is discharged into the outlet pipe straight section through the diversion passage. By arranging the tube heat exchanger inside the outlet pipe straight section, the heat energy and kinetic energy of the combustion gas are fully utilized, and the energy conversion efficiency of the turbine device is improved. The turbine device fully utilizes the energy of the combustion gas, reduces the flow and heat energy loss of the combustion gas, outputs shaft power energy outward, and effectively improves the energy conversion efficiency of the turbine. BRIEF 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 an axial sectional view of the aerospace turbine device with an exhaust gas deflector cone and a tube heat exchanger according to the embodiment of the present utility model.
[0021] Explanation of the reference numerals in the drawings:
[0022] 1 - gas collecting ring; 2 - nozzle ring; 3 - guide vane seal ring; 4 - outlet pipe; 5 - two-stage turbine disk; 6 - exhaust gas deflector cone; 7 - tube heat exchanger; 8 - outlet pipe throat. Detailed implementation manners
[0023] The following will clearly and completely describe the technical solutions in the embodiments of the present utility model in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present utility model without making creative efforts shall fall within the protection scope of the present utility model.
[0024] It should be understood that when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, wholes, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, wholes, steps, operations, elements, components, and / or their combinations.
[0025] It should also be understood that the terms used in this 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 this 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.
[0026] It should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the inventive product is customarily placed during use. It is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.
[0027] The terms "parallel" and "perpendicular" do not mean that the components are absolutely parallel or perpendicular, but may be slightly inclined. For example, "parallel" only means that its direction is more parallel relative to "perpendicular", and does not mean that the structure must be completely parallel, but may be slightly inclined.
[0028] In the description of the present invention, it should also be noted that unless otherwise clearly defined and limited, the terms "connected" and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal communication of two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.
[0029] Embodiment
[0030] Please refer to Figure 1The aerospace turbine device with an exhaust flow guide cone and a tube heat exchanger as shown in the figure includes a turbine housing, and the turbine housing is composed of a gas collecting ring 1 and a nozzle ring 2 which are connected to each other. It also includes a guide vane seal ring 3, an outlet pipe 4, a two-stage turbine disk 5, and an exhaust flow guide cone 6. The guide vane seal ring 3 is arranged on the nozzle ring 2. The outlet pipe 4 is welded to the nozzle ring 2. A tube heat exchanger 7 is arranged inside the outlet pipe 4. The two-stage turbine disk 5 is arranged between the turbine housing and the outlet pipe 4. The exhaust flow guide cone 6 is welded to the two-stage turbine disk 5. In this embodiment, the gas collecting ring 1 and the nozzle ring 2 are integrally formed by 3D printing, which can reduce the processing procedures and improve the processing accuracy. Nozzles are arranged circumferentially along the inner side of the nozzle ring 2, and the nozzles are conical or cascade-shaped. In this embodiment, the nozzles are conical. The arrangement of the nozzles plays a role in cooling, depressurizing, and accelerating the combustion gas. A flange structure and bolts are arranged between the guide vane seal ring 3 and the nozzle ring 2, and the guide vane seal ring 3 is fixed on the nozzle ring 2 through the flange structure and bolts. The guide vane seal ring 3 is evenly divided into 3 segments along the circumference, which is convenient for disassembly and assembly. Since the outlet pipe 4 and the nozzle ring 2 in this embodiment are welded, the assembly and manufacturing cost can be reduced, and it can play a role in reliably sealing the combustion gas. It also includes a turbine main shaft, and the turbine main shaft is fixedly connected to the two-stage turbine disk 5. The turbine main shaft and the two-stage turbine disk 5 are connected through an involute spline structure or a flange structure. In this embodiment, the turbine main shaft and the two-stage turbine disk 5 are connected through a flange structure, which plays a role in reliably transmitting torque. It also includes a cascade channel, and the cascade channel is arranged inside the two-stage turbine disk 5. In this embodiment, a non-contact mechanical seal gap is also arranged between the two-stage turbine disk 5 and the guide vane seal ring 3. It also includes a diversion channel, and the diversion channel is arranged between the outlet pipe 4 and the exhaust flow guide cone 6. An outlet pipe straight section is arranged inside the outlet pipe 4. The diversion channel is connected to the outlet pipe straight section, and the tube heat exchanger 7 is arranged in the outlet pipe straight section. The exhaust flow guide cone 6 guides the combustion gas to enter the outlet pipe straight section after rectification. The tube heat exchanger 7 is specifically a serpentine tube heat exchanger, which can effectively absorb the heat energy of the discharged high-temperature combustion gas. One end of the outlet pipe 4 away from the nozzle ring 2 is provided with an outlet, and an outlet pipe throat 8 is arranged at a position close to the outlet inside the outlet pipe 4. The arrangement of the outlet pipe throat 8 can ensure that the combustion gas reaches supersonic speed after being discharged from the outlet pipe 4.
[0031] The working process of the aerospace turbine device with an exhaust flow guide cone and a tube heat exchanger is as follows:
[0032] The high-temperature gas enters the gas collecting ring 1. After being rectified by the gas collecting ring 1, it is distributed to the nozzles of 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 a high speed. Specifically, the cascade channels are divided into the first-stage cascade and the second-stage cascade. The high-speed gas first enters the first-stage cascade of the two-stage turbine disk 5 to expand and do work, and then changes the gas flow direction through the guide vane channel of the guide vane sealing ring 3, and then enters the second-stage cascade of the two-stage turbine disk 5 to continue expanding and doing work. The guide vane channel of the guide vane sealing ring 3 plays a role in turning the gas, and the cascade channels of the two-stage turbine disk 5 play a role in gas expansion and work output and shaft work output. A small part of the gas enters the non-contact mechanical seal gap between the two-stage turbine disk 5 and the guide vane sealing ring 3. The mechanical seal plays a role in sealing the gas, reducing the leakage amount and stabilizing the rotor system. The non-contact mechanical seal in this embodiment specifically refers to a labyrinth seal. The gas flowing out of the cascade channels of the two-stage turbine disk 5 enters the diversion channel between the outlet pipe 4 and the exhaust guide cone 6 to continue expanding and accelerating, guiding the gas to smoothly enter the straight pipe section of the outlet pipe. Then, the high-temperature gas hits the outer wall surface of the tubular heat exchanger 7 at a high speed, and strong heat exchange occurs between the gas and the fluid in the tubular heat exchanger 7. The heated fluid can be used for tank pressurization or other purposes during rocket flight. Finally, the gas is discharged from the outlet of the outlet pipe 4 to the environment through the throat 8 of the outlet pipe, generating partial thrust.
[0033] The present utility model provides a space turbine device with an exhaust guide cone and a tubular heat exchanger. By making full use of the gas energy, reducing the gas flow and heat energy losses, and outputting shaft work energy, the turbine energy conversion efficiency is effectively improved.
[0034] The above is only the specific implementation manner of the present utility model, but the protection scope of the present utility model is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present utility model 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 utility model. Therefore, the protection scope of the present utility model shall be subject to the protection scope of the claims.
Claims
1. An aerospace turbine device with an exhaust guide cone and a tubular heat exchanger, characterized in that, It includes a turbine housing, a guide vane seal ring, an outlet pipe, a two-stage turbine disk, and an exhaust gas deflector cone; the turbine housing is composed of a gas collecting ring and a nozzle ring connected to each other, the guide vane seal ring is arranged on the nozzle ring, the outlet pipe is welded to the nozzle ring, a tubular heat exchanger is arranged in the outlet pipe, the two-stage turbine disk is arranged between the turbine housing and the outlet pipe, and the exhaust gas deflector cone is welded to the two-stage turbine disk.
2. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger as claimed in claim 1, characterized in that, Nozzles are arranged circumferentially along the inner side of the nozzle ring, and the nozzles are conical or cascade-shaped.
3. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger as claimed in claim 1, wherein, A flange structure and bolts are provided between the guide vane seal ring and the nozzle ring, and the guide vane seal ring is fixed to the nozzle ring through the flange structure and bolts.
4. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger according to claim 1, characterized in that, It further includes a turbine main shaft, and the turbine main shaft is fixedly connected to the two-stage turbine disk.
5. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger according to claim 4, characterized in that, The turbine main shaft and the two-stage turbine disk are connected through an involute spline structure or a flange disk structure.
6. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger as claimed in claim 1, wherein The guide vane seal ring is evenly divided into 3 segments along the circumference.
7. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger as claimed in claim 1, wherein One end of the outlet pipe away from the nozzle ring is provided with an outlet, and an outlet pipe throat is arranged at a position close to the outlet in the outlet pipe.
8. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger according to claim 1, characterized in that, It further includes a cascade channel, and the cascade channel is arranged in the two-stage turbine disk.
9. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger according to claim 1, characterized in that, It further includes a diversion channel, and the diversion channel is arranged between the outlet pipe and the exhaust gas deflector cone.
10. The aerospace turbine device with an exhaust flow guide cone and a tubular heat exchanger according to claim 9, characterized in that, An outlet pipe straight section is arranged in the outlet pipe, the diversion channel is connected to the outlet pipe straight section, and the tubular heat exchanger is arranged in the outlet pipe straight section.