Aero-engine tail jet boosting device

Abstract

The aero-engine tail jet boosting device comprises an engine body, a plurality of oil conveying pipes and a plurality of breather pipes are arranged on the periphery of the outer portion of the engine body, the oil conveying pipes penetrate into the engine body, oil nozzles are arranged at the inner ends of the oil conveying pipes, and air nozzles are arranged at the inner ends of the breather pipes penetrate into the engine body; the breather pipe is provided with an air valve. The eight oil conveying pipes and the eight ventilation pipes are uniformly distributed along the circumference in a staggered manner; the upper ends of the eight oil conveying pipes are communicated through an annular pipe A. The upper ends of the eight ventilation pipes are communicated through an annular pipe B. The annular pipe A is provided with an oil conveying header pipe, and the annular pipe B is provided with a ventilation header pipe. The main oil delivery pipe is connected with the oil pump. The ventilation header pipe is connected with the gas compressor. And the oil nozzle and the air nozzle are 80cm away from an air outlet at the lower end of the engine body. Compared with the prior art, the engine has the advantages that oil and gas are mixed at the position, close to the outlet, of the engine body and are combusted and jetted, thrust of the engine body is increased, and the engine is easy to install on an existing aero-engine.

Description

Technical Field

[0001] This patent relates to the technical field of aircraft engine tail jet booster devices, specifically to an aircraft engine tail jet booster device. Background Art

[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry.

[0003] The development of aircraft engines has gone through piston engines, turbojet / turbofan engines, and non-traditional new aircraft engines. As the requirements for flight speed continue to increase, the thrust system of current aircraft engines is difficult to meet the rapidly increasing needs.

[0004] Patent content

[0005] The technical problem to be solved by this patent is to overcome the defects of the above-mentioned technology and provide an aircraft engine tail jet booster device. In order to solve the above-mentioned technical problems, the technical solution provided by this patent is an aircraft engine tail jet booster device: comprising an engine body, a plurality of oil pipes and a plurality of ventilation pipes are arranged around the outside of the engine body, the oil pipe penetrates into the engine body and is provided with an oil nozzle at the inner end, the ventilation pipe penetrates into the engine body and is provided with an air nozzle at the inner end, the oil pipe is provided with an oil valve, and the ventilation pipe is provided with an air valve.

[0006] As an improvement, the number of the oil pipes and ventilation pipes is eight, which are evenly distributed along the circumference. The upper ends of the eight oil pipes are connected through an annular pipe A, and the upper ends of the eight ventilation pipes are connected through an annular pipe B. The annular pipe A is provided with an oil main pipe, and the annular pipe B is provided with a ventilation main pipe.

[0007] Compared with the prior art, the advantages of this patent are: the oil and gas are mixed and burned near the outlet of the engine body, thereby increasing the thrust of the engine body. This aircraft engine tail jet booster device is easy to install on the existing aircraft engine, effectively improves the thrust of the engine, and thus increases the flight speed, and has high practical value and promotion value. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] Figure 1 This is a schematic diagram of the structure of an aircraft engine tail jet booster device of this patent.

[0009] Figure 2 yes Figure 1 Schematic diagram of the structure without the engine body.

[0010] Figure 3 This is a side view of the aircraft engine tail nozzle.

[0011] Figure 4 Depend on Figure 3 As shown in the figure: 1. The 8 fuel injection nozzles are connected (6) to the oil pressure valve, 2. The 8 air injection nozzles are connected (7) to the air pressure valve. Figure 4 , 1. 8 fuel injectors penetrate the engine body and connect Figure 4 , (2)(6)(8)(4) oil pipelines are interconnected and connected to the fuel pump. Figure 4 , 2. 8 jet nozzles penetrate the engine body and connect Figure 4 , (3)(7)(9)(5) the air pipes are connected to the air compressor. Figure 5 The patent discloses an aircraft engine tail jet booster device, as shown in the figure: (1) engine body (2) oil pipeline, (3) ventilation pipe, (4) oil main pipe, (5) ventilation main pipe, (6) oil pressure valve, (7) air pressure valve, (8) oil ring pipe, and (9) air ring pipe. DETAILED DESCRIPTION

[0012] The following is a further detailed description of an aircraft engine tail jet booster device of this patent in conjunction with the accompanying drawings.

[0013] Combined with Figures 1 to 4 A tail jet booster device for an aircraft engine comprises an engine body 1, a plurality of oil pipes 2 and a plurality of ventilation pipes 3 are arranged around the outside of the engine body 1, the oil pipes 2 penetrate into the engine body 1 and an oil nozzle 4 is arranged at the inner end, the ventilation pipes 3 penetrate into the engine body 1 and an air nozzle 5 is arranged at the inner end, the oil pipes 2 are provided with an oil valve 6, and the ventilation pipes 3 are provided with an air valve 7.

[0014] There are eight oil pipes 2 and eight ventilation pipes 3, which are staggered and evenly distributed along the circumference; the upper ends of the eight oil pipes 2 are connected through an annular pipe A8, and the upper ends of the eight ventilation pipes 3 are connected through an annular pipe B9. The annular pipe A8 is provided with an oil main pipe 11, and the annular pipe B9 is provided with a ventilation main pipe 10.

[0015] The oil delivery main pipe 11 is connected to an oil pump.

[0016] The ventilation main pipe 10 is connected to a gas compressor.

[0017] The distance between the fuel injection nozzle 4 and the air injection nozzle 5 and the air injection outlet at the lower end of the engine body 1 is 80 cm.

[0018] When this patent is implemented, oil and gas are mixed and burned near the outlet of the engine body 1 to increase the thrust of the engine body 1. This aircraft engine tail jet booster device is easy to install on the existing aircraft engine, effectively improves the thrust of the engine, and then increases the flight speed, and has high practical value and promotion value.

[0019] The above describes the present patent and its implementation methods, which is not restrictive. The drawings show only one implementation method of the present patent, and the actual structure is not limited thereto. In short, if ordinary technicians in this field are inspired by it and design structural methods and embodiments similar to the technical solution without creative design without departing from the purpose of the invention of the present patent, they should all fall within the scope of protection of the present patent.

Claims

1. An invention patented aircraft engine tail jet booster device, characterized in that: The invention comprises an engine body (1), wherein a plurality of oil delivery pipes (2) and a plurality of ventilation pipes (3) are arranged around the outside of the engine body (1), wherein the oil delivery pipe (2) penetrates into the engine body (1) and is provided with an oil injection nozzle (4) at the inner end, wherein the ventilation pipe (3) penetrates into the engine body (1) and is provided with an air injection nozzle (5) at the inner end, wherein the oil delivery pipe (2) is provided with an oil valve (6), and wherein the ventilation pipe (3) is provided with an air valve (7).

2. The aircraft engine tail jet booster device according to claim 1, characterized in that: The number of the oil delivery pipes (2) and the ventilation pipes (3) are both eight, and they are evenly distributed along the circumference in an alternating manner; the upper ends of the eight oil delivery pipes (2) are connected through an annular pipe A (8), and the upper ends of the eight ventilation pipes (3) are connected through an annular pipe B (9); the annular pipe A (8) is provided with an oil delivery main pipe (11), and the annular pipe B (9) is provided with a ventilation main pipe (10).

3. The tail jet booster device of an aircraft engine according to claim 1, characterized in that: The oil delivery main pipe (11) is connected to the oil pump.

4. The aircraft engine tail jet booster device according to claim 1, characterized in that: The ventilation main pipe (10) is connected to a gas compressor.

5. The aircraft engine tail jet booster device according to claim 1, characterized in that: The fuel injection nozzle (4) and the air injection nozzle (5) are 80 centimeters away from the air injection outlet at the lower end of the engine body (1).

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