Air starting system of turbojet engine

Abstract

The utility model discloses an air starting system of a turbojet engine, and relates to the technical field of turbojet engines. Comprising a workbench, a tool body used for installing an engine body is arranged on the workbench, a plurality of nozzles used for driving blades of the engine body to rotate are arranged on the tool body, and the nozzles communicate with a gas supply assembly used for providing gas. According to the tool, the engine body is convenient to mount and dismount through the tool body, meanwhile, gas of the gas supply assembly is conveyed to blades of the engine body through the nozzle, the engine body can effectively and rapidly rotate to the ignition rotating speed from the zero speed, auxiliary ignition is carried out, and the ignition efficiency is improved. Working-medium-free (oil-free state) parameter testing and engine testing work of an engine body are facilitated, and experimental ignition can be conveniently and rapidly carried out.

Description

Technical Field

[0001] The utility model relates to the technical field of turbojet engines, in particular to an air starting system for turbojet engines. Background Art

[0002] At present, in the parameter testing and trial operation of the engine body of the turbojet engine, in order to enable the engine body of the turbojet engine to start reliably in the absence of working fluid (in the oil-free state) and to meet a certain starting acceleration, a ground air source vehicle or a windmill is usually used to start the engine to reach the appropriate speed. This type of operation is complicated and the starting equipment is inconvenient to move, which has great limitations. Therefore, there is an urgent need for an air starting system for a turbojet engine that can effectively rotate the engine from zero speed to the ignition speed quickly, perform auxiliary ignition, facilitate the parameter testing and trial operation of the engine in the absence of working fluid (in the oil-free state), and can quickly and easily perform experimental ignition. Utility Model Content

[0003] The purpose of the utility model is to provide an air starting system for a turbojet engine to solve the problems existing in the above-mentioned prior art.

[0004] To achieve the above-mentioned purpose, the present invention provides the following solution: The present invention provides an air starting system for a turbojet engine, comprising a workbench, on which a tooling body for mounting an engine body is provided, and on which a plurality of nozzles for driving the blades of the engine body to rotate are provided, and the nozzles are connected to an air supply assembly for providing gas.

[0005] Preferably, the tooling body includes a shell, the shell is detachably connected to the engine body, and a plurality of nozzles are fixedly connected to the shell, with the nozzles of the nozzles facing the air inlet of the engine body.

[0006] Preferably, the plurality of nozzles are arranged at equal intervals.

[0007] Preferably, the nozzle and the blades of the engine body are arranged in a geometric multiple relationship.

[0008] Preferably, the gas supply assembly includes an air source line connected to the nozzle, and one end of the air source line away from the nozzle is fixedly connected and connected to an air source.

[0009] Preferably, a switch valve and a pressure regulating valve are installed on the gas source line.

[0010] Preferably, the switch valve is arranged close to the nozzle.

[0011] Preferably, the pressure regulating valve is arranged close to the gas source.

[0012] The utility model discloses the following technical effects:

[0013] The utility model not only facilitates the installation and disassembly of the engine body through the tooling body, but also transmits the gas of the air supply assembly to the blades of the engine body through the nozzle, which can effectively rotate the engine body from zero speed to ignition speed quickly, perform auxiliary ignition, and facilitate the parameter testing and trial operation of the engine body without working fluid (no oil state). The utility model can carry out experimental ignition conveniently and quickly. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0015] Figure 1 This is a schematic diagram of the overall structure of the utility model;

[0016] Figure 2 This is a front view structural diagram of the utility model in which the engine body is installed in the tooling body;

[0017] Figure 3 This is a side view of the main structure of the tooling of the utility model;

[0018] Among them, 1. Tool body; 2. Workbench; 3. Engine body; 4. Switch valve; 5. Air supply line; 6. Pressure regulating valve; 7. Air source; 8. Casing; 9. Nozzle; 10. Blade; 11. Rotation direction. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0020] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific implementation methods.

[0021] Reference Figure 1-Figure 3The utility model discloses an air starting system for a turbojet engine, comprising a workbench 2, on which a tooling body 1 for mounting an engine body 3 is provided, and on which a plurality of nozzles 9 for driving blades 10 of the engine body 3 to rotate are provided, and the nozzles 9 are connected to an air supply assembly for providing gas.

[0022] The tool body 1 is sealed and connected to the engine body 3 by threaded connection, sealing rubber ring and the like.

[0023] The utility model not only facilitates the installation and disassembly of the engine body 3 through the tooling main body 1, but also transports the gas of the air supply assembly to the blades of the engine body 3 through the nozzle 9, which can effectively rotate the engine body 3 from zero speed to the ignition speed for auxiliary ignition, and facilitates the parameter testing and trial operation of the engine body 3 without working fluid (in oil-free state). The utility model can carry out experimental ignition conveniently and quickly.

[0024] According to a further optimization scheme, the tooling body 1 includes an outer shell 8, which is detachably connected to the engine body 3, and a plurality of nozzles 9 are fixedly connected to the outer shell 8, with the nozzles of the nozzles 9 facing the air intake duct of the engine body 3.

[0025] The gas provided by the air supply assembly is sprayed onto the blades of the engine body 3 through the nozzle 9, driving the blades of the engine body 3 to rotate.

[0026] In a further optimized solution, a plurality of nozzles 9 are arranged at equal intervals. The nozzles 9 are evenly arranged on the housing 8 in a circular shape.

[0027] According to a further optimization scheme, the nozzle 9 and the blades 10 of the engine body 3 are arranged in a geometric multiple relationship.

[0028] The nozzle of the nozzle 9 is located at the air inlet of the engine body 3. According to the rotation direction 11 of the blade 10, the circumferential direction forms an angle of 75-90° with the tangent line of the circumscribed circle of the blade 10, and the axial direction forms an angle of 25-45° with the blade 10.

[0029] According to a further optimized solution, the gas supply assembly includes a gas source line 5 connected to the nozzle 9 , and one end of the gas source line 5 away from the nozzle 9 is fixedly connected to and connected to the gas source 7 .

[0030] To further optimize the solution, a switch valve 4 and a pressure regulating valve 6 are installed on the gas source line 5.

[0031] In a further optimized solution, the switch valve 4 is provided near the nozzle 9. The switch valve 4 is used to open or close the gas supply.

[0032] In a further optimized solution, the pressure regulating valve 6 is provided close to the gas source 7. The pressure regulating valve 6 is used to regulate the gas pressure.

[0033] The gas is passed through the gas source 7 in sequence through the pressure regulating valve 6 and the switch valve 4 into the nozzle 9 , and the gas is sprayed toward the blade 10 through the nozzle 9 .

[0034] Working process: After placing the engine body 3 on the workbench 2, install the engine body 3 into the outer shell 8, and then open the switch valve 4. The gas in the gas source 7 passes through the pressure regulating valve 6 and the switch valve 4 along the gas source line 5 and enters the nozzle 9. The gas is ejected from the nozzle 9 to the tangent of the circumscribed circle of the blade 10, and the blade 10 is driven by the gas to rotate, so that the engine body 3 rotates quickly from zero speed to the ignition speed, and auxiliary ignition is performed, which is convenient for parameter testing and trial operation of the engine body 3 without working fluid (oil-free state). The utility model can perform experimental ignition conveniently and quickly.

[0035] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present invention.

[0036] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements to the technical solutions of the present invention made by ordinary technicians in this field should fall within the scope of protection determined by the claims of the present invention.

Claims

1. A turbojet engine air starting system, characterized by: The invention comprises a workbench (2), wherein a tooling body (1) for mounting an engine body (3) is provided on the workbench (2), and a plurality of nozzles (9) for driving blades (10) of the engine body (3) to rotate are provided on the tooling body (1), and the nozzles (9) are connected to a gas supply assembly for providing gas.

2. The turbojet engine air starting system according to claim 1, characterized in that: The tooling body (1) comprises a shell (8), the shell (8) is detachably connected to the engine body (3), and a plurality of nozzles (9) are fixedly connected to the shell (8), with the nozzles of the nozzles (9) facing the air inlet of the engine body (3).

3. The turbojet engine air starting system according to claim 2, characterized in that: A plurality of the nozzles (9) are arranged at equal intervals.

4. The turbojet engine air starting system according to claim 2, characterized in that: The nozzle (9) and the blades (10) of the engine body (3) are arranged in a geometric multiple relationship.

5. The turbojet engine air starting system according to claim 2, characterized in that: The air supply assembly comprises an air source line (5) connected to the nozzle (9), and one end of the air source line (5) away from the nozzle (9) is fixedly connected to and connected to an air source (7).

6. The turbojet engine air starting system according to claim 5, characterized in that: The gas source line (5) is equipped with a switch valve (4) and a pressure regulating valve (6).

7. The turbojet engine air starting system according to claim 6, characterized in that: The switch valve (4) is arranged close to the nozzle (9).

8. The turbojet engine air starting system according to claim 6, characterized in that: The pressure regulating valve (6) is arranged close to the gas source (7).

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