Turbine shell structure for gas turbine engine of unmanned aerial vehicle
By using 3D printing technology to manufacture the turbine housing structure of the gas turbine engine for drones, the problems of complex assembly and heavy weight have been solved, achieving lightweighting and efficient maintenance, and improving the performance and endurance of drones.
Patent Information
- Application Number
- CN202520786125.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-24
- Publication Date
- 2026-01-27
- Estimated Expiration
- 2035-04-24
AI Technical Summary
Existing UAV gas turbine engines are complex to assemble, heavy, and affect performance and stability. They also have high maintenance costs, which limits the UAV's endurance and mission capabilities.
The turbine housing structure of a gas turbine engine for unmanned aerial vehicles (UAVs) is manufactured using 3D printing technology. It includes an outer housing, turbine guide structure and bearing sleeve. The one-piece molding design reduces the number of parts and optimizes the flow channel structure to improve flow efficiency.
It simplifies the assembly process, reduces weight and maintenance costs, improves engine combustion efficiency and power output, enhances structural strength and reliability, and improves the flight performance and endurance of the drone.
Smart Images
Figure CN223839234U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a turbine housing structure for a gas turbine engine for UAVs. Background Technology
[0002] In existing UAV gas turbine designs, engine components such as the casing and turbine are typically manufactured independently and then assembled. This traditional multi-part assembly method has many drawbacks. On the one hand, the assembly process is extremely complex, requiring a large amount of manual operation and high-precision assembly techniques. This not only increases production time and costs but also makes it prone to assembly errors due to human factors, affecting the overall performance and stability of the engine. On the other hand, the combination of numerous parts results in a large overall engine weight. For UAVs, an excessively heavy engine is detrimental to their endurance, flight flexibility, and payload capacity, limiting their application in missions such as long-endurance reconnaissance and high-altitude complex environment operations. Summary of the Invention
[0003] In order to overcome the shortcomings and deficiencies of the existing technology, the purpose of this utility model is to provide a turbine housing structure for a gas turbine engine of a drone.
[0004] The objective of this utility model is achieved through the following technical solution: a turbine housing structure for a gas turbine engine of an unmanned aerial vehicle (UAV), comprising an outer housing, a turbine guide structure, and a bearing sleeve. The bearing sleeve is inserted into the turbine guide structure, and the turbine guide structure is inserted into the cavity of the outer housing. One end of the outer housing is provided with a connecting flange, and the connecting flange is provided with a plurality of mating mounting holes at intervals. The turbine guide structure has an integrated turbine section and a connecting sleeve. The outer surface of the integrated turbine section is provided with a mating flange, and the mating flange is provided with a through hole corresponding to each of the mating mounting holes. One end of the connecting sleeve is provided with a plurality of mounting holes at intervals, and one end of the bearing sleeve is provided with a plurality of connecting lugs at intervals. Each connecting lug is provided with a through hole, and the through hole corresponds one-to-one with the mounting hole.
[0005] As an improvement to the turbine housing structure for a gas turbine engine in a UAV, the integrated turbine housing section includes an inner housing and an outer housing, with an air duct formed between the inner and outer housings. Multiple turbine blades are spaced apart within the air duct, and each turbine blade is integrally formed with both the inner and outer housings. A hole is formed in the center of the inner housing, and the other end of the connecting sleeve is connected to the edge of the hole. The integrated turbine housing design makes the flow channel between the turbine and the housing smoother and more continuous, reducing gas resistance and turbulence during flow. This helps improve the combustion efficiency and power output of the gas turbine, thereby enhancing the flight performance and endurance of the UAV.
[0006] As an improvement to the turbine housing structure for the gas turbine engine of the UAV of this utility model, an integrally formed wind-gathering shroud is formed on one end edge of the outer shell. The wind-gathering shroud is horn-shaped, and the mating baffle is provided on the outer surface of the outer shell.
[0007] As an improvement to the turbine housing structure for the gas turbine engine of the UAV of this utility model, one end of the bearing sleeve passes through one end of the connecting sleeve, and the connecting lug on the bearing sleeve is fixedly connected to the mounting hole by screws.
[0008] As an improvement to the turbine housing structure for the gas turbine engine of the UAV of this utility model, the turbine integrated compartment section of the turbine guide structure passes through one end of the outer housing, the mating flange abuts against the connecting flange, the mating mounting hole corresponds one-to-one with the through hole, and is fixed by screws.
[0009] As an improvement to the turbine housing structure for the gas turbine engine of the UAV of this utility model, the outer shell is provided with two supporting feet and two fixed connecting seats at intervals on the outer side. Each of the two supporting feet is provided with a first fixing hole, and the two fixed connecting seats are correspondingly arranged, each of the two fixed connecting seats is provided with a second fixing hole.
[0010] The beneficial effects of this invention are as follows: The number of parts is significantly reduced, allowing technicians to perform overall maintenance more quickly and conveniently during engine upkeep and repair. Unlike traditional engines, which require checking numerous parts individually, this significantly improves maintenance efficiency and reduces costs. The turbine guide vane structure is integrally molded, resulting in a smoother and more continuous flow path between the turbine and the casing, reducing gas resistance and turbulence. This helps improve the combustion efficiency and power output of the gas turbine, thereby enhancing the flight performance and endurance of the UAV. Due to the fewer connections between parts, this invention can better withstand the complex loads generated by high temperature, high pressure, and high speed during engine operation. Compared to traditional assembly structures, its overall structural strength is higher, reliability is stronger, and it effectively reduces the probability of engine failure due to loose parts or connection failures. Attached Figure Description
[0011] Figure 1 This is an exploded view of this utility model;
[0012] Figure 2 This is a schematic diagram of the external shell structure of this utility model;
[0013] Figure 3 This is a schematic diagram of the turbine guide structure of this utility model;
[0014] Figure 4 This is a schematic diagram of the bearing sleeve structure of this utility model;
[0015] The attached figures are labeled as follows:
[0016] 1. Outer shell; 11. Connecting flange; 12. Butt mounting hole; 13. Support foot; 14. Fixed connecting seat; 15. First fixing hole; 16. Second fixing hole;
[0017] 2. Turbine guide structural components; 21. Turbine integrated compartment section; 22. Connecting sleeve; 23. Butt joint flange; 24. Through hole; 25. Mounting hole; 211. Inner casing; 212. Outer casing; 213. Air duct; 214. Turbine blade; 215. Hole; 216. Wind concentrator.
[0018] 3. Bearing sleeve; 31. Connecting lug; 32. Through hole. Detailed Implementation
[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.
[0020] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment are only used to explain the relative positional relationship and movement of each component in a specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.
[0021] Furthermore, the use of terms such as "first" and "second" in this utility model is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. If the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this utility model.
[0022] like Figures 1-4 As shown, a turbine housing structure for a gas turbine engine of an unmanned aerial vehicle includes an outer housing 1, a turbine guide structure 2, and a bearing sleeve 3. The bearing sleeve 3 is inserted into the turbine guide structure 2, and the turbine guide structure 2 is inserted into the cavity of the outer housing 1. One end of the outer housing 1 is provided with a connecting baffle 11, and the connecting baffle 11 is provided with a plurality of mating mounting holes 12 at intervals. The turbine guide structure 2 has an integrated turbine housing section 21 and a connecting sleeve 22. The outer surface of the integrated turbine housing section 21 is provided with a mating baffle 23, and the mating baffle 23 is provided with a through hole 24 corresponding to the position of each mating mounting hole 12. One end of the connecting sleeve 22 is provided with a plurality of mounting holes 25 at intervals. One end of the bearing sleeve 3 is provided with a plurality of connecting lugs 31 at intervals, and each connecting lug 31 is provided with a through hole 32, which corresponds one-to-one with the mounting hole 25. The outer shell 1, turbine guide vane structure 2, and bearing sleeve 3 are all manufactured using metal 3D printing technology. Based on a pre-designed three-dimensional model, metal powder is deposited layer by layer and melted and sintered using a high-energy laser beam to produce the outer shell, turbine guide vane structure, and bearing sleeve, respectively. 3D printing technology enables the precise manufacture of complex structures, further optimizing the lightweight design of the turbine housing structure while ensuring structural strength.
[0023] Preferably, the integrated turbine housing 21 includes an inner casing 211 and an outer casing 212, with an air duct 213 formed between the inner casing 211 and the outer casing 212. Multiple turbine blades 214 are spaced apart within the air duct 213. The turbine blades 214 are integrally formed with the inner casing 211 and the outer casing 212. A hole 215 is formed in the middle of the inner casing 211, and the other end of the connecting sleeve 22 is connected to the edge of the hole 215. The design of the integrated turbine housing 21 makes the flow channel between the turbine and the casing smoother and more continuous, reducing gas resistance and turbulence during flow. This helps improve the combustion efficiency and power output of the gas turbine, thereby enhancing the flight performance and endurance of the UAV.
[0024] Preferably, one end edge of the outer casing 212 is integrally formed with a wind concentrator 216, which is trumpet-shaped, and the mating edge 23 is provided on the outer surface of the outer casing 212.
[0025] Preferably, one end of the bearing sleeve 3 is inserted into one end of the connecting sleeve 22, and the connecting lug 31 on the bearing sleeve 3 is fixedly connected to the mounting hole 25 by screws.
[0026] Preferably, the turbine integrated compartment section 21 of the turbine guide structure 2 passes through one end of the outer housing 1, the mating flange 23 abuts against the connecting flange 11, the mating mounting hole 12 corresponds one-to-one with the through hole 24, and is fixed by screws.
[0027] Preferably, the outer shell 1 is provided with two support feet 13 and two fixed connecting seats 14 at intervals on the outer side. Each of the two support feet 13 is provided with a first fixing hole 15, and the two fixed connecting seats 14 are provided with corresponding holes and a second fixing hole 16.
[0028] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and structure of the present invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A turbine housing structure for a gas turbine engine of an unmanned aerial vehicle (UAV), characterized in that, The device includes an outer housing, a turbine guide vane structure, and a bearing sleeve. The bearing sleeve is installed inside the turbine guide vane structure, which is installed inside the cavity of the outer housing. One end of the outer housing has a connecting flange with multiple mating mounting holes spaced apart. The turbine guide vane structure has an integrated turbine housing section and a connecting sleeve. The outer surface of the integrated turbine housing section has a mating flange with through holes corresponding to each of the mating mounting holes. One end of the connecting sleeve has multiple mounting holes spaced apart, and one end of the bearing sleeve has multiple connecting lugs spaced apart, each of which has a through hole corresponding to one of the mounting holes.
2. The turbine housing structure for a gas turbine engine for an unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The integrated turbine housing section includes an inner casing and an outer casing, with an air duct formed between the inner casing and the outer casing. Multiple turbine blades are spaced apart in the air duct. The turbine blades are integrally formed with the inner casing and the outer casing. A hole is formed in the middle of the inner casing, and the other end of the connecting sleeve is connected to the edge of the hole.
3. The turbine housing structure for a gas turbine engine for an unmanned aerial vehicle according to claim 2, characterized in that, One end edge of the outer casing is integrally formed with a wind-gathering hood, which is horn-shaped, and the mating baffle is provided on the outer surface of the outer casing.
4. The turbine housing structure for a gas turbine engine of an unmanned aerial vehicle according to claim 2, characterized in that, One end of the bearing sleeve passes through one end of the connecting sleeve, and the connecting lug on the bearing sleeve is fixedly connected to the mounting hole by screws.
5. The turbine housing structure for a gas turbine engine for an unmanned aerial vehicle according to claim 2, characterized in that, The turbine integrated compartment of the turbine guide structure passes through one end of the outer housing, the mating flange abuts against the connecting flange, the mating mounting hole corresponds one-to-one with the through hole, and is fixed by screws.
6. The turbine housing structure for a gas turbine engine for an unmanned aerial vehicle according to claim 1, characterized in that, The outer shell is provided with two support feet and two fixed connecting seats at intervals on its outer side. Each of the two support feet is provided with a first fixing hole, and the two fixed connecting seats are provided with corresponding second fixing holes.