An air inlet passage structure matched with a turbojet engine

Abstract

The utility model belongs to the technical field of aero-engine, concretely relates to an air inlet channel structure matched with turbojet engine inlet, at least includes air inlet channel inner tube and air inlet channel lip, air inlet channel lip is connected in the air inlet port of air inlet channel inner tube, air inlet channel lip and air inlet channel inner tube outside wall lower part have the air inlet channel of intercommunication, the utility model air inlet channel and the air inlet ring reliable butt joint of engine, and use the positioning pin to carry out the assembly limit of engine, not only can guarantee the assembly precision, and will not happen because the air inlet channel and the air inlet mouth of engine seal not strict lead to the problem of air leakage, air leakage, the utility model air inlet channel increases the cooling channel for engine cabin from the structure design, makes the airflow can enter the engine cabin from the cooling channel, effectively cools the engine, improves the service life of engine cabin rudder machine and other equipment, the utility model reliable air inlet channel structure, help to improve the reliability and stability of whole unmanned aerial vehicle system.

Description

Technical Field

[0001] This utility model belongs to the field of aero-engine technology, specifically relating to an air intake structure that is matched with the inlet of a turbojet engine. Background Technology

[0002] In military exercises and weapons tests, drones need to simulate aerial targets in various real-world scenarios, including flight in adverse weather conditions and complex geographical environments. Inlet-Engine Matching is one of the core issues in aerospace propulsion system design. Its purpose is to ensure that the inlet can provide stable airflow to the engine under different flight conditions (such as speed, altitude, angle of attack, etc.), while optimizing the engine's performance, efficiency, and reliability.

[0003] If the air intake and engine of a drone do not work well together, and the problem of high temperature in the engine compartment cannot be solved, it will lead to unstable air intake of the engine, which will affect the air intake volume. In more serious cases, high temperature environment can easily cause damage to the airframe and failure of components, which will seriously affect the normal flight of the drone and reduce the performance and reliability of the drone. Therefore, it is urgent to design a structure that can work closely with the turbojet engine, without affecting the air intake of the engine, and at the same time cool down the engine compartment. Utility Model Content

[0004] This utility model provides an air intake structure that is compatible with the turbojet engine, with the aim of providing an air intake structure design that is compatible with the turbojet engine, so as to stabilize the intake of the UAV engine and solve the problem of high temperature in the engine compartment.

[0005] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0006] An air intake structure compatible with a turbojet engine includes at least an inner air intake tube and an air intake lip; the air intake lip is connected to the air intake port of the inner air intake tube; and there is a communicating air intake passage between the air intake lip and the lower part of the outer side wall of the inner air intake tube.

[0007] The inner tube of the intake manifold is a curved, interconnected tubular structure, with a circular cross-section at one end and a semi-circular cross-section at the other end, with the semi-circular segment located at the bottom. The circular end is connected to an engine adapter ring for connection with the engine, and the semi-circular segment is connected to the intake manifold lip.

[0008] The intake lip is a hollow plate-shaped structure formed by two arc-shaped plates that are narrow at the front end and wide at the rear end; the hollow space forms a lip cooling duct, which is connected to the lower part of the outer wall of the inner tube of the intake; the rear end of the intake lip is connected to the intake port of the inner tube of the intake.

[0009] The arc length at the rear end of the intake duct lip matches the arc length at the lower part of the intake duct inner tube.

[0010] The inner tube of the air intake and the lip of the air intake are an integral structure.

[0011] The engine adapter ring is equipped with a locating pin.

[0012] The locating pins are provided in 2 to 4 units.

[0013] There are three positioning pins.

[0014] Beneficial effects:

[0015] 1. This utility model provides a stable air intake effect: the air intake duct is reliably connected to the engine's air intake ring, and the engine is assembled and limited by a positioning pin. This not only ensures assembly accuracy and stable air intake of the engine, but also prevents air leakage or venting caused by poor sealing between the air intake duct and the engine's air intake port.

[0016] 2. This utility model effectively reduces the high temperature environment in the engine compartment: The intake duct is structurally designed to include a cooling channel for the engine compartment, allowing airflow to enter the engine compartment through the cooling channel, effectively cooling the engine and extending the service life of equipment such as the engine compartment steering gear.

[0017] 3. This utility model improves overall reliability: As an important part of the UAV, the reliable air intake structure of this utility model helps to improve the reliability and stability of the entire UAV system.

[0018] The above description is only an overview of the technical solution of this utility model. In order to better understand the technical means of this utility model and to implement it in accordance with the contents of the specification, the preferred embodiments of this utility model are described in detail below with reference to the accompanying drawings. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model 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 this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is an assembly diagram of the present invention.

[0021] Figure 2 This is a structural diagram of the air intake duct of this utility model.

[0022] Figure 3This is an exploded view of the rear of the air intake duct and the engine air intake of this utility model.

[0023] Figure 4 This is a schematic diagram of the intake lip structure of this utility model.

[0024] In the diagram: 1. Intake lip; 2. Intake duct inner tube; 3. Rear panel of the fuselage; 4. Engine adapter ring; 5. Engine; 6. Servo; 101. Lip cooling duct; 401. Positioning pin. Detailed Implementation

[0025] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. 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 of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0026] Example:

[0027] according to Figures 1-4 The diagram shows an air intake structure that is compatible with the inlet of a turbojet engine, comprising at least an inner air intake tube 2 and an air intake lip 1; the air intake lip 1 is connected to the air intake port of the inner air intake tube 2; and the air intake lip 1 has a communicating air intake channel with the lower part of the outer side wall of the inner air intake tube 2.

[0028] In actual use, the air intake structure matching the turbojet engine is bonded to the rear plate 3 of the fuselage using molds and positioning fixtures. At this time, the air intake structure matching the turbojet engine forms an integral part with the fuselage. A metal frame connecting the servo motor 6 is arranged at the rear end of the rear plate 3, and the frame is fixed to the rear plate 3 using molds and positioning fixtures. At this time, the servo motor 6 is close to the engine 5, and the rear plate 3 and the upper plate of the fuselage form a closed space. The nozzle of the engine 5 and the servo motor 6 are exactly in this area. Therefore, the temperature in this area will rise due to the operation of the engine 5, which has a great impact on the servo motor 6. The air intake channel connecting the air intake lip 1 and the lower part of the outer wall of the inner pipe 2 of the air intake is connected to the aforementioned closed high-temperature environment. When the drone is flying in the air, the airflow splits into two streams. One stream passes through the upper part of the intake lip 1, through the inner pipe 2 of the intake duct, and reaches the intake port of the engine 5. The intake port of the engine 5 is closely fitted with the intake duct structure that matches the turbojet engine, ensuring stable air intake and preventing loss of air volume. The other stream enters the engine compartment formed by the rear plate 3 and the upper plate of the fuselage through the intake channel connecting the intake lip 1 and the lower part of the outer wall of the inner pipe 2. At this time, the engine 5 has already raised the temperature in the engine compartment. After the airflow comes in through the intake channel, it will carry the high-temperature gas and be discharged from the tail nozzle of the fuselage, thereby reducing the high-temperature environment and facilitating the normal operation of the equipment.

[0029] In some embodiments, the inner pipe 2 of the intake manifold is a curved connecting pipe structure, with a circular cross-section at one end and a semi-circular arc cross-section at the other end, and the semi-circular arc segment is located at the lower part; the circular end is connected to an engine adapter ring 4 for connection with the engine 5, and the semi-circular arc segment is connected to an intake manifold lip 1.

[0030] Furthermore, the intake lip 1 is a hollow plate structure formed by two arc-shaped plates that are narrow at the front end and wide at the rear end; the hollow space forms a lip cooling duct 101, which is connected to the lower part of the outer wall of the inner wall of the intake duct 2; the rear end of the intake lip 1 is connected to the intake port of the inner wall of the intake duct 2.

[0031] In actual use, the intake manifold inner pipe 2 adopts the above-mentioned technical solution, which facilitates the connection with the engine 5 on the one hand, and connects with the engine 5 through the engine adapter ring 4 on the other hand, ensuring a tight fit between the engine 5 intake port and the engine adapter ring 4, thereby ensuring stable intake and no loss of air volume.

[0032] The air intake lip 1 adopts the above-mentioned technical solution. When the UAV is flying in the air, an airflow will enter the engine compartment formed by the rear plate 3 and the upper plate of the fuselage through the lip cooling duct 101. The duct airflow in the lip cooling duct 101 will exhaust the high-temperature gas that rises in the engine compartment when the engine 5 is working from the tail nozzle of the fuselage, thereby reducing the high-temperature environment and ensuring the normal operation of the equipment.

[0033] In some embodiments, the arc length of the rear end of the intake duct lip 1 matches the arc length of the lower part of the intake duct inner tube 2. This maximizes the introduction of airflow into the engine compartment formed by the rear panel 3 and the upper panel of the fuselage, improving the efficiency of removing high-temperature gases.

[0034] In some embodiments, the inner intake pipe 2 and the intake lip 1 are an integral structure. This structural design not only improves the efficiency of mass production of intake structures, but also ensures the stability and lifespan of the intake structure.

[0035] In some embodiments, the engine adapter ring 4 is provided with a positioning pin 401.

[0036] Furthermore, the positioning pin 401 is provided in 2 to 4 parts.

[0037] Furthermore, the positioning pin 401 is provided in three parts.

[0038] When installing the intake structure matching the turbojet engine with the engine 5, it is required that the air intake of the engine 5 be tightly attached to the engine adapter ring 4. The positioning pin 401 is inserted into the positioning hole of the engine 5 to accurately complete the installation of the intake structure matching the turbojet engine with the engine 5, ensuring the fit between the air intake of the engine 5 and the engine adapter ring 4.

[0039] This utility model is installed in the middle and rear section of the fuselage of the UAV. The rear section of the inner pipe 2 of the air intake is embedded in the fuselage, while the air intake lip 1 is exposed to the outside, providing reliable air intake for the engine 5 and providing low-temperature airflow for the engine compartment.

[0040] Where there is no conflict, those skilled in the art can combine the relevant technical features in the above examples according to the actual situation to achieve the corresponding technical effects. Specific details of the various combinations will not be elaborated here.

[0041] 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 certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0042] The above description is merely a preferred embodiment of the present invention. The present invention is not limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein. Any simple modifications, equivalent variations, and alterations made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the present invention.

Claims

1. An air intake structure compatible with the starting mechanism of a turbojet engine, characterized in that: It includes at least an inner intake pipe (2) and an intake lip (1); the intake lip (1) is connected to the intake port of the inner intake pipe (2); the intake lip (1) and the lower part of the outer side wall of the inner intake pipe (2) have a communicating intake channel.

2. The air intake structure for matching a turbojet engine as described in claim 1, characterized in that: The intake manifold inner tube (2) is a curved connecting tube structure, with a circular cross-section at one end and a semi-circular arc cross-section at the other end, and the semi-circular arc segment is located at the bottom; the circular end is connected to an engine adapter ring (4) for connecting to the engine (5), and the semi-circular arc segment is connected to an intake manifold lip (1).

3. An air intake structure matching the start-up of a turbojet engine as described in claim 1 or 2, characterized in that: The intake lip (1) is a hollow plate structure formed by two arc-shaped plates that are narrow at the front end and wide at the rear end; the hollow space forms a lip cooling duct (101), which is connected to the lower part of the outer wall of the inner tube of the intake duct (2); the rear end of the intake lip (1) is connected to the intake port of the inner tube of the intake duct (2).

4. The air intake structure for matching a turbojet engine as described in claim 3, characterized in that: The arc length of the rear end of the intake lip (1) matches the length of the lower arc of the intake inner tube (2).

5. An air intake structure matching a turbojet engine as described in claim 1 or 2, characterized in that: The inner tube (2) of the air intake duct and the lip (1) of the air intake duct are an integral structure.

6. The air intake structure for matching a turbojet engine as described in claim 2, characterized in that: The engine adapter ring (4) is provided with a positioning pin (401).

7. The air intake structure for matching a turbojet engine as described in claim 6, characterized in that: The positioning pins (401) are provided in 2 to 4 units.

8. The air intake structure for matching a turbojet engine as described in claim 7, characterized in that: There are three positioning pins (401).

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