阅读说明：本技术 一种用于飞机在偏流板前起飞的高温尾气流动控制装置 (High-temperature tail gas flow control device for take-off of airplane in front of flow deflector ) 是由 田方超 赵肃 杨瀚超 张志学 王军 于 2021-11-19 设计创作，主要内容包括：本申请属于发动机控制技术领域,具体涉及一种用于飞机在偏流板前起飞的高温尾气流动控制装置。在飞机(1)后机轮与偏流板(2)之间的甲板的舰面(3)上设置有槽口,所述高温尾气流动控制装置包括抽吸装置,抽吸装置设置在甲板底下,并通过抽吸管路(6)连接至甲板的舰面槽口,偏流板(2)倾斜布置于飞机(1)的后方,用于基于飞机的高温喷流(4)对飞机提供推力,所述高温尾气流动控制装置用于对高温喷流(4)沿偏流板(2)向甲板舰面(3)方向的部分气体进行抽吸。本申请无需对偏流板、止动轮挡等复杂机构进行改造,降低了技术难度,缩减了研制成本,保障飞机起飞安全。(The application belongs to the technical field of engine control, and particularly relates to a high-temperature tail gas flow control device for an airplane to take off in front of a flow deflector. The high-temperature tail gas flow control device comprises a suction device, the suction device is arranged below a deck and connected to a deck ship surface notch through a suction pipeline (6), the deflector (2) is obliquely arranged behind the aircraft (1) and used for providing thrust to the aircraft based on high-temperature jet flow (4) of the aircraft, and the high-temperature tail gas flow control device is used for sucking partial gas of the high-temperature jet flow (4) in the direction from the deflector (2) to the deck ship surface (3). According to the airplane take-off control method and device, complex mechanisms such as the flow deflector and the stop wheel block do not need to be modified, the technical difficulty is reduced, the development cost is reduced, and the airplane take-off safety is guaranteed.)

1. The high-temperature tail gas flow control device for the aircraft to take off in front of the flow deflector is characterized in that a notch is formed in a ship surface (3) of a deck between a rear wheel of the aircraft (1) and the flow deflector (2), the high-temperature tail gas flow control device comprises a suction device, the suction device is arranged below the deck and connected to the ship surface notch of the deck through a suction pipeline (6), the flow deflector (2) is obliquely arranged behind the aircraft (1) and used for providing thrust for the aircraft based on high-temperature jet flow (4) of the aircraft, and the high-temperature tail gas flow control device is used for sucking partial gas of the high-temperature jet flow (4) in the direction from the flow deflector (2) to the ship surface (3) of the deck.

2. A high temperature exhaust flow control device for an aircraft takeoff ahead of a deflector as in claim 1, characterized in that the suction device comprises a vacuum tank (8), one end of the vacuum tank (8) being connected to a centrifugal pump (10) by a hose and the other end being connected to the suction line (6).

3. A high temperature exhaust flow control device for an aircraft taking off before a deflector as in claim 2, characterized in that the hose is provided with a one-way valve (9) and the suction line is provided with a valve (7).

4. A high temperature exhaust gas flow control device for aircraft taking off before a flow deflector according to claim 1, characterized in that a plurality of slots are provided on the deck (3), each slot being connected collectively to the suction line (6).

5. A high temperature exhaust flow control device for an aircraft taking off before a flow deflector as in claim 4, wherein a grille is disposed on the slot.

6. A hot exhaust gas flow control device for an aircraft taking off before a deflector as in claim 1, characterized in that the suction means comprise a fan, the suction face of which forms a housing space communicating with the suction duct (6).

Technical Field

The application belongs to the technical field of engine safety design, and particularly relates to a high-temperature tail gas flow control device for an airplane to take off in front of a flow deflector.

Background

The take-off environment of the carrier-based aircraft is different from that of the land aircraft, and an aircraft stop wheel block and a flow deflector are arranged on a take-off runway on an aircraft carrier and are respectively used for fixing the aircraft before taking off and guiding high-temperature jet flow of an engine so as to protect the safety of facilities and personnel on the rear surface of the ship. Before the carrier-based aircraft takes off and runs, the carrier-based aircraft needs to stay in front of the flow deflector and work for a period of time, in the period of time, high-temperature jet flow of the engine continuously impacts on the flow deflector, a part of high-temperature jet flow is reflected by the flow deflector, flows towards the aircraft nose direction along the deck and is sucked by the engine under the action of suction force at the inlet of the engine, temperature distortion is generated at the inlet of the engine, the stable working margin of the engine is reduced, the unstable work of the engine is easily caused, and the take-off safety of the aircraft is influenced.

The engine inevitably faces the problem of high temperature tail gas suction before the drift plate works, and great potential safety hazard is brought to the stable work of the engine.

At present, there is no prior art solution for solving such problems, and the analysis considers that the solution can be adopted is:

1) reducing the lifting angle of the deflector

The lifting angle of the flow deflecting plate is reduced, so that the degree of the reflection backflow of the high-temperature tail gas of the engine can be reduced, and the amount of the high-temperature tail gas sucked by the engine is reduced.

However, the lifting angle of the flow deflector is reduced, the existing flow deflector control mechanism, a cooling system and the like need to be modified to a greater extent, the influence range is large, the construction period is long, and the modification cost is high. And after the angle of the deflector is reduced, the shielding effect on the high-temperature jet flow of the engine is weakened, and the safety of facilities and personnel behind the deflector is influenced.

2) Increasing the distance between the engine and the deflector

After the distance between the engine and the deflector is increased, the influence range of the deflector on the reflection degree of the jet flow of the engine and the backflow tail gas is weakened, so that the high-temperature tail gas amount sucked by the engine is reduced.

However, the distance between the engine and the deflector needs to be increased, the airplane stopping position needs to be moved forwards, the existing airplane stopping wheel chock needs to be modified, the stopping wheel chock comprises a complex control mechanism, the modification difficulty is high, and the modification cost is high. And after the stop position of the airplane moves forward, the sliding distance of the airplane can be shortened, and the safe departure and the taking off of the airplane from the ship are influenced.

Disclosure of Invention

This application is to engine high temperature tail gas backward flow phenomenon, designs a high temperature tail gas flow control device, pumps high temperature backward flow tail gas, alleviates its antecedent trend to reduce the engine and inhale high temperature tail gas degree, promote engine job stabilization nature.

The application provides a high temperature exhaust flow control device that is used for aircraft to take off before the deflector is provided with the notch on the warship face of the deck between wheel and the deflector behind the aircraft, high temperature exhaust flow control device includes suction device, suction device sets up beneath the deck to be connected to the warship face notch on deck through the suction pipeline, the deflector slope is arranged at the rear of aircraft for high temperature jet stream based on the aircraft provides thrust to the aircraft, high temperature exhaust flow control device is used for sucking the partial gas of high temperature jet stream along the deflector to deck warship face direction.

Preferably, the suction device comprises a vacuum tank, one end of the vacuum tank is connected to the centrifugal pump through a hose, and the other end of the vacuum tank is connected to the suction pipeline.

Preferably, the hose is provided with a one-way valve, and the suction pipeline is provided with a valve.

Preferably, the deck is provided with a plurality of notches, and each notch is connected to the suction pipeline in a gathering mode.

Preferably, a grating is disposed on the notch.

Preferably, the suction means comprise a fan, the suction face of which forms an accommodation space communicating with the suction duct.

According to the method, complex mechanisms such as a flow deflector, a stop wheel block and the like do not need to be modified, the technical difficulty is reduced, and the development cost is reduced; the flow field at the rear of the flow deflector is changed less, so that rear facilities and personnel are prevented from being damaged; the method and the device do not change the sliding distance of the airplane and guarantee the taking-off safety of the airplane.

Drawings

FIG. 1 is a schematic illustration of the installation of the high temperature exhaust flow control device for aircraft takeoff in front of a deflector of the present application.

The system comprises an airplane 1, a deflector 2, a ship surface 3, a high-temperature jet flow 4, an engine 5, a suction pipeline 6, a valve 7, a vacuum tank 8, a one-way valve 9 and a centrifugal pump 10.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.

The application provides a high temperature exhaust flow control device for aircraft takes off before deflector, as shown in fig. 1, be provided with the notch on the warship face 3 of the deck between aircraft wheel and deflector 2 behind aircraft 1, high temperature exhaust flow control device includes suction device, suction device sets up beneath the deck to be connected to the warship face notch of deck through suction line 6, deflector 2 slope is arranged in the rear of aircraft 1 for high temperature efflux 4 based on the aircraft provides thrust to the aircraft, high temperature exhaust flow control device is used for pumping high temperature efflux 4 along deflector 2 to the partial gas of deck warship face 3 direction.

In some alternative embodiments, the suction device comprises a vacuum tank 8, one end of the vacuum tank 8 is connected to a centrifugal pump 10 through a hose, and the other end is connected to the suction line 6, and in alternative embodiments, the suction device can also be a fan, and the suction surface of the fan forms a containing space which is communicated with the suction line 6.

When the suction device is a centrifugal pump and a vacuum tank 8, the hose is provided with a one-way valve 9, and the suction pipeline is provided with a valve 7.

Under the condition of not adopting flow control, before taking off, the airplane 1 is parked on a deck ship surface 3 and positioned in front of a flow deflector 2, when an engine 5 works, high-temperature jet flow 4 impacts the flow deflector 2, wherein most of high-temperature engine tail gas flows to the rear upper part of the flow deflector, but part of high-temperature gas flows downwards along the flow deflector, backflow is generated below a fuselage, and the high-temperature gas is sucked by the engine under the action of suction force at an inlet of the engine.

A flow control system is arranged in a cabin body below a deck to suck the reflowed high-temperature tail gas, and the working principle is as shown in figure 1: at the serious tail gas backflow position, the ship surface 3 of the deck is grooved and connected with a suction pipeline 6, and the other end of the suction pipeline 6 is connected with a vacuum tank 8 through a valve 7. Before the flow control system works, the valve 7 needs to be closed, the centrifugal pump 10 needs to be opened, the one-way valve 9 needs to be opened, the pressure in the vacuum tank 8 needs to be pumped to a vacuum state, and the one-way valve 9 needs to be closed after the pressure in the vacuum tank is pumped to the vacuum state, so that the pressure leakage of the vacuum tank is prevented. When the flow control system works, the valve 7 is opened, and the backflow high-temperature tail gas 4 is sucked into the vacuum tank through the suction pipe 6, so that the continuous forward movement of the backflow high-temperature tail gas is prevented from being sucked by the engine.

In some alternative embodiments, there are provided a plurality of notches on the deck 3, each notch being collectively connected to the suction line 6.

In some alternative embodiments, a grill is disposed over the slot.

Compared with other technologies, the method has the following advantages: the complex mechanism of the ship surface is not required to be modified, the technical difficulty is reduced, and the development cost is reduced; the flow guide device does not obviously change the rear flow field of the flow deflector, thereby avoiding damage to rear facilities and personnel; the sliding distance of the airplane is not changed, and the take-off safety of the airplane is guaranteed.

Although the present application has been described in detail with respect to the general description and specific embodiments, it will be apparent to those skilled in the art that certain modifications or improvements may be made based on the present application. Accordingly, such modifications and improvements are intended to be within the scope of this invention as claimed.