Aircraft engine tail nozzle high-temperature backflow airflow cut-off device and method thereof

Abstract

The invention belongs to the technical field of aircraft engine tail spray pipe high-temperature backflow airflow cut-off design, and particularly relates to an aircraft engine tail spray pipe high-temperature backflow airflow cut-off device and a method thereof.The aircraft engine tail spray pipe high-temperature backflow airflow cut-off device comprises two air curtain machines arranged on a deck; the two air curtain machines are located behind the aircraft and located on the two sides of an aircraft body. The two air curtain machines are perpendicular to the axis of the aircraft body, and outlets face the aircraft body. The two air curtain machines are located between wings and a horizontal tail on the two sides of the airplane.

Description

Technical Field

[0001] This application belongs to the technical field of high-temperature recirculation airflow cutoff design for aircraft engine tail nozzles, and specifically relates to a high-temperature recirculation airflow cutoff device and method for aircraft engine tail nozzles. Background Art

[0002] Aircraft usually take off in a ski-jump manner on the deck. To avoid damage to the equipment and personnel behind caused by the high-temperature flame ejected from the engine tail nozzle during takeoff, a deflector is set behind the engine tail nozzle for shielding.

[0003] Setting a deflector behind the engine tail nozzle on the deck to shield the high-temperature flame ejected from the engine tail nozzle during takeoff can effectively protect the equipment and personnel behind from damage. However, the high-temperature airflow ejected from the engine tail nozzle, blocked by the deflector, will flow back to the front of the intake duct and then be sucked into the engine, resulting in intake distortion. In severe cases, it will cause the engine to surge, leading to the inability of the aircraft to take off normally. Currently, in response to this, when the aircraft takes off, the aircraft usually takes off against the wind, or the thrust of the engine is restricted to avoid a large amount of the high-temperature airflow ejected from the engine tail nozzle flowing back to the front of the intake duct and being sucked into the engine. Among them, taking off against the wind requires a long adjustment time, and restricting the engine thrust is likely to lead to insufficient takeoff power of the aircraft, resulting in a failed takeoff and even danger.

[0004] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0005] The purpose of this application is to provide a high-temperature recirculation airflow cutoff device and method for aircraft engine tail nozzles to overcome or mitigate at least one aspect of the known technical defects.

[0006] The technical solution of this application is as follows:

[0007] On the one hand, a high-temperature recirculation airflow cutoff device for aircraft engine tail nozzles is provided, including:

[0008] Two air curtain machines, which are arranged on the deck;

[0009] The two air curtain machines are located behind the aircraft and on both sides of the aircraft fuselage;

[0010] The two air curtain machines are perpendicular to the axis of the aircraft fuselage, and the outlets face the aircraft fuselage;

[0011] The two air curtain machines are located between the wings and horizontal tails on both sides of the aircraft.

[0012] According to at least one embodiment of this application, in the above high-temperature recirculation airflow cutoff device for aircraft engine tail nozzles, the two air curtain machines are close to the trailing edges of the wing tips on both sides of the aircraft.

[0013] According to at least one embodiment of the present application, in the above-mentioned high-temperature recirculation air flow cut-off device for the tail nozzle of an aircraft engine, the two air curtain machines are powered by battery charging.

[0014] According to at least one embodiment of the present application, in the above-mentioned high-temperature recirculation air flow cut-off device for the tail nozzle of an aircraft engine, both sides of the two air curtain machines are adsorbed and fixed on the deck by electromagnets.

[0015] On the other hand, a method for cutting off the high-temperature recirculation air flow of the tail nozzle of an aircraft engine is provided, which is implemented based on the above-mentioned high-temperature recirculation air flow cut-off device for the tail nozzle of an aircraft engine, and includes:

[0016] When the aircraft takes off, start the two air curtain machines, blow out air currents between the wings and the horizontal tail of both sides of the aircraft to form an air curtain, cut off the high-temperature air flow that is ejected from the tail nozzle of the aircraft engine and blocked by the deflector and recirculates, and prevent it from flowing back in front of the aircraft intake port and being sucked into the engine, resulting in intake distortion.

[0017] According to at least one embodiment of the present application, in the above-mentioned method for cutting off the high-temperature recirculation air flow of the tail nozzle of an aircraft engine, when the aircraft takes off, judge the wind speed. If the headwind speed is less than 15 m / s, start the two air curtain machines; if the headwind speed is greater than 15 m / s, do not start the two air curtain machines.

[0018] The present application has at least the following beneficial technical effects:

[0019] A high-temperature recirculation air flow cut-off device for the tail nozzle of an aircraft engine is provided. It is designed to set two air curtain machines on the deck. The two air curtain machines are located behind the aircraft, on both sides of the aircraft, and perpendicular to the axis of the aircraft body. The outlets face the aircraft body, and are between the wings and the horizontal tail of both sides of the aircraft. When the aircraft takes off, the two air curtain machines can be started, and the two air curtain machines are used to blow out air currents between the wings and the horizontal tail of both sides of the aircraft, cut off the high-temperature air flow that is ejected from the tail nozzle of the aircraft engine and blocked by the deflector and recirculates, and prevent it from flowing back in front of the aircraft intake port and being sucked into the engine, resulting in intake distortion and causing engine surge. The operation is convenient and fast, without restricting the engine thrust, and can ensure that the aircraft can take off normally. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is a schematic diagram of the high-temperature recirculation air flow cut-off device for the tail nozzle of an aircraft engine provided by an embodiment of the present application;

[0021] Figure 2 is Figure 1 the side view of

[0022] Wherein:

[0023] 1 - air curtain machine; 2 - aircraft; 3 - deflector.

[0024] To better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which does not represent the size of the actual product. In addition, the drawings are only for illustrative purposes and should not be construed as a limitation of this patent. Detailed implementation manners

[0025] To make the technical solutions and their advantages of this application clearer, the technical solutions of this application will be further described clearly and completely in conjunction with the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of this application, which are only used to explain this application and are not a limitation of this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.

[0026] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the field to which this application belongs. The terms indicating directions used in the description of this application are only used to represent relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. The "including" used in the description of this application means that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0027] In addition, it should be noted that unless otherwise clearly specified and limited, the terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to the specific situation.

[0028] On the one hand, a high-temperature return air flow truncation device for the tail nozzle of an aircraft engine is provided, as Figure 1-2 shown, including:

[0029] Two air curtain machines 1, which are arranged on the deck;

[0030] The two air curtain machines 1 are behind the aircraft 2 and on both sides of the aircraft 2 fuselage;

[0031] The two air curtain machines 1 are perpendicular to the axis of the aircraft 2 fuselage, and the outlets face the aircraft 2 fuselage;

[0032] The two air curtain machines 1 are between the wings and horizontal tails on both sides of the aircraft 2.

[0033] When the aircraft takes off by ski-jumping on the deck, the high-temperature air flow ejected from the tail nozzle of the engine is blocked by the deflector plate and mainly returns to the front of the intake duct through the wing tips on both sides of the aircraft 2. Based on this, in the high-temperature return air flow truncation device for the tail nozzle of the aircraft engine disclosed in the above embodiment, it is designed to set two air curtain machines 1 on the deck. The two air curtain machines 1 are located behind the aircraft 2, on both sides of the aircraft 2, and perpendicular to the axis of the aircraft 2 body. The outlets face the aircraft 2 body, and between the wings and horizontal tail on both sides of the aircraft 2. When the aircraft takes off, the two air curtain machines 1 can be started, and the two air curtain machines 1 are used to blow out air flow between the wings and horizontal tail on both sides of the aircraft 2 to truncate the high-temperature air flow ejected from the tail nozzle of the aircraft engine and blocked by the deflector plate 3 from flowing back, avoiding flowing back to the front of the intake duct of the aircraft 2 and being sucked into the engine, resulting in intake distortion and causing engine surge. The operation is convenient and fast, without restricting the engine thrust, and can ensure that the aircraft can take off normally.

[0034] In some alternative embodiments, in the high-temperature return air flow truncation device for the tail nozzle of the aircraft engine described above, the two air curtain machines 1 are close to the trailing edges of the wing tips on both sides of the aircraft 2, and can truncate the high-temperature air flow ejected from the tail nozzle of the aircraft engine and blocked by the deflector plate 3 from flowing back between the wing tips on both sides of the aircraft 2, avoiding violent turbulence affected by the wings and making it difficult to truncate.

[0035] In some alternative embodiments, in the high-temperature return air flow truncation device for the tail nozzle of the aircraft engine described above, the two air curtain machines 1 are powered by battery charging.

[0036] In some alternative embodiments, in the high-temperature return air flow truncation device for the tail nozzle of the aircraft engine described above, both sides of the two air curtain machines 1 are adsorbed and fixed on the deck by electromagnets.

[0037] On the other hand, a method for truncating the high-temperature return air flow of the tail nozzle of an aircraft engine is provided, which is implemented based on the above high-temperature return air flow truncation device for the tail nozzle of an aircraft engine, and includes:

[0038] When the aircraft takes off, start the two air curtain machines 1, blow out air flow between the wings and horizontal tail on both sides of the aircraft 2 to form an air curtain, and truncate the high-temperature air flow ejected from the tail nozzle of the aircraft engine and blocked by the deflector plate 3 from flowing back, avoiding flowing back to the front of the intake duct of the aircraft 2 and being sucked into the engine to generate intake distortion.

[0039] For the method for truncating the high-temperature recirculation air flow at the tail nozzle of an aircraft engine disclosed in the above embodiments, it is implemented based on the device for truncating the high-temperature recirculation air flow at the tail nozzle of an aircraft engine disclosed in the above embodiments. The description is relatively simple. For specific relevant parts, reference can be made to the relevant descriptions in the part of the device for truncating the high-temperature recirculation air flow at the tail nozzle of an aircraft engine. Its technical effects can also be referred to the technical effects of the relevant parts of the device for truncating the high-temperature recirculation air flow at the tail nozzle of an aircraft engine, which will not be elaborated here.

[0040] In some alternative embodiments, in the method for truncating the high-temperature recirculation air flow at the tail nozzle of the above aircraft engine, when the aircraft takes off, the wind speed is judged. If the headwind speed is less than 15 m / s, two air curtain machines 1 are started. If the headwind speed is greater than 15 m / s, the two air curtain machines 1 are not started, and the high-temperature air flow that is ejected from the tail nozzle of the aircraft engine and blocked by the deflector 3 and recirculates can be truncated outward by relying on the headwind, preventing it from flowing back to the front of the intake duct of the aircraft 2 and being sucked into the engine, thus avoiding intake distortion and causing engine surge, and ensuring the normal takeoff of the aircraft.

[0041] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other. Without conflict, the embodiments and the technical features in the embodiments in the present application can be combined with each other to obtain new embodiments.

[0042] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the protection scope of the present application.

Claims

1. A high-temperature reflux air flow truncation device for the tail nozzle of an aircraft engine, characterized in that Including: Two air curtain machines (1) are arranged on the deck; The two air curtain machines (1) are located behind the aircraft (2) and on both sides of the aircraft (2) body; The two air curtain machines (1) are perpendicular to the axis of the aircraft (2) body, and the outlets face the aircraft (2) body; The two air curtain machines (1) are located between the wings and horizontal tails on both sides of the aircraft (2); 2. The high-temperature reflux air flow truncation device for the tail nozzle of an aircraft engine according to claim 1, characterized in that: The two air curtain machines (1) are close to the trailing edges of the wing tips on both sides of the aircraft (2); 3. The high-temperature reflux air flow truncation device for the tail nozzle of an aircraft engine according to claim 1, characterized in that: The two air curtain machines (1) are powered by battery charging; 4. The high-temperature reflux air flow truncation device for the tail nozzle of an aircraft engine according to claim 1, characterized in that: The two sides of the two air curtain machines (1) are adsorbed and fixed on the deck by electromagnets; 5. A method for intercepting high-temperature reflux air flow at the tail nozzle of an aircraft engine, characterized in that, Based on the implementation of the high-temperature reflux air flow truncation device for the tail nozzle of an aircraft engine according to claim 1, including: When the aircraft takes off, start the two air curtain machines (1), blow out air between the wings and horizontal tails on both sides of the aircraft (2) to form an air curtain, truncate the high-temperature air flow that is blocked and refluxed by the deflector (3) from the tail nozzle of the aircraft engine, and prevent it from flowing back to the front of the air intake of the aircraft (2) and being sucked into the engine, resulting in air intake distortion.

6. The high-temperature reflux air flow truncation method for the tail nozzle of an aircraft engine according to claim 5, characterized in that: When the aircraft takes off, judge the wind speed. If the headwind speed is less than 15 m / s, start the two air curtain machines (1). If the headwind speed is greater than 15 m / s, do not start the two air curtain machines (1).

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