Turbojet engine with standard starting function

Abstract

The turbojet engine comprises a spray pipe, a gunpowder fuel gas generator and a flameout detection unit, gunpowder is contained in the spray pipe, one end of the spray pipe is arranged opposite to the gunpowder fuel gas generator, and the other end of the spray pipe faces a guider; the gunpowder fuel gas generator is electrically connected with the engine electric control unit; the flameout detection unit detects the rotating speed and temperature of an engine and transmits corresponding detection signals to the engine electric control unit, and the engine electric control unit controls the gunpowder gas generator according to the detection signals. When the gunpowder fuel gas generator is ignited to ignite gunpowder, high-pressure airflow is generated and blows the turbine to rotate through the guider, and then the rotor is driven to rotate, so that the rotating speed of the engine starts to rise. And when the rotating speed of the engine reaches the starting ignition rotating speed, oil injection ignition is started in the combustion chamber until the engine enters a slow working state, and the engine is started successfully. Therefore, the air flameout device can be quickly restarted in a short time when flameout is carried out in the air.

Description

[0001] This utility model claims the priority of the following patent applications:

[0002] The application date is May 18, 2024, the application number is 202421090184.0, and the name is a Chinese utility model patent application for a turbojet engine with standard start. Technical Field

[0003] The utility model relates to the technical field of turbojet engines, in particular to a turbojet engine with standard starting. Background Art

[0004] When a turbojet engine is working in the air, it may stop in the air due to various reasons, and the engine needs to be restarted in the air after stopping. When a turbojet engine encounters an engine flameout during high-altitude flight, it requires a quick start in a short time. Since the turbojet engine for missiles is disposable, it requires a simple structure and a short start time. The missile cannot provide a strong current or too much space. Therefore, the air start method using high-pressure gas filled in a high-pressure gas cylinder cannot be used, nor can the electric start method using batteries or storage batteries that are several times heavier than the starter motor itself be used. In addition, the power of the starter motor is very sensitive to changes in the external temperature and its own voltage.

[0005] In view of the above technical problems, technical personnel in this field urgently need to design a turbojet engine with standard start to solve the problem of restarting after parking in the air. Utility Model Content

[0006] In view of the above-mentioned shortcomings, the technical problem to be solved by the utility model is to provide a turbojet engine with standard starting, which can quickly restart with a lower current in a short time when the engine stalls in the air, and has the advantages of simple structure and light weight.

[0007] In order to solve the above technical problems, the technical solution of the utility model is:

[0008] A turbojet engine with standard starting comprises a shell, a combustion chamber, a fuel ignition system and a rotor chamber are arranged on the inner side of the shell, a rotor, a turbine installed at the rear end of the rotor, and a guide arranged in front of the turbine are arranged in the rotor chamber, and the engine also comprises: a nozzle, the nozzle is arranged on the shell, gunpowder is filled in the nozzle, one end of the nozzle extends out of the shell, and the other end of the nozzle extends into the rotor chamber and is arranged toward the guide; a gunpowder gas generator, the gunpowder gas generator is arranged on the outer side of the shell, the gunpowder gas generator is arranged relative to the gunpowder at the nozzle port, and the gunpowder gas generator is electrically connected to the engine electronic control unit; a flameout detection unit, the flameout detection unit is used to detect the engine speed and temperature, and transmit the corresponding detection signal to the engine electronic control unit, and the engine electronic control unit controls the gunpowder gas generator according to the detection signal.

[0009] Preferably, the nozzle is a Rafale nozzle, and the Rafale nozzle is arranged close to the guide.

[0010] Preferably, the working pressure in the combustion chamber is set according to the throat area of ​​the Rafale nozzle.

[0011] Preferably, the gunpowder includes a main gunpowder and an ignition tablet disposed at the outer end of the main gunpowder, and the ignition tablet is disposed opposite to the gunpowder gas generator.

[0012] Preferably, the main gunpowder is in columnar or tubular shape.

[0013] Preferably, the ignition tablet is a double lead powder with a low ignition point.

[0014] Preferably, the main gunpowder is a double-base propellant with a low burning rate.

[0015] Preferably, the ignition pressure of the fuel ignition system is set according to the size of the burning surface of the ignition tablet.

[0016] A preferred embodiment is that the engine also includes a vaned diffuser, a mounting plate, a guide cover, a compressor and an air intake casing; the vaned diffuser is disposed in the rotor chamber and installed at the front end of the rotor; the mounting plate is pressed onto the vaned diffuser, and the mounting plate is connected to the casing; the guide cover is connected to the mounting plate; the compressor is disposed in front of the vaned diffuser, and the compressor is coaxially arranged with the rotor; the air intake casing cover is disposed on the outside of the compressor, and the air intake casing is connected to the mounting plate.

[0017] Preferably, the engine further comprises a starter motor, and the starter motor is inserted into the air intake casing and arranged coaxially with the compressor.

[0018] After adopting the above technical solution, the beneficial effects of the utility model are:

[0019] The utility model of the turbojet engine with standard start includes a nozzle, a gunpowder gas generator and a flameout detection unit, wherein the nozzle is arranged on the shell, gunpowder is contained in the nozzle, one end of the nozzle extends out of the shell, and the other end of the nozzle extends into the rotor chamber and is arranged toward the guide; wherein the gunpowder gas generator is arranged outside the shell, the gunpowder gas generator and the port of the nozzle are arranged relative to each other, and the gunpowder gas generator is electrically connected to the engine electronic control unit; wherein the flameout detection unit is used to detect the engine speed and temperature, and transmit the flameout signal to the corresponding detection signal to the engine electronic control unit, and the engine electronic control unit controls the gunpowder gas generator according to the detection signal. When the engine electronic control unit starts the gunpowder gas generator to ignite, after the gunpowder is ignited, a high-speed airflow is generated, and this airflow blows the turbine to rotate through the guide, and the turbine then drives the rotor to rotate, so that the engine speed begins to rise. When the engine speed reaches the starting ignition speed, the fuel ignition system starts to spray and ignite in the combustion chamber, and the turbine starts to generate power; at this time, enough air has entered the engine, so that the gas temperature will not be too high when the combustion chamber is ignited; after the combustion chamber is ignited, the engine rotor is driven by the turbine, and as the speed increases, the power generated by the turbine increases rapidly; when the engine speed exceeds the minimum stable working speed, the gas temperature before the turbine is maintained at the maximum allowable value, and the turbine power is greater than the power consumed by the compressor; relying on the turbine power, the engine speed continues to rise until the engine enters the slow working state, and the engine starts successfully. It can be seen that the utility model can quickly restart with a lower current in a short time when the flameout occurs in the air, and has the advantages of simple structure and light weight. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a structural schematic diagram of a turbojet engine with a standard start in the utility model;

[0021] In the figure: 1-engine electronic control unit, 2-propellant gas generator, 3-propellant, 4-Rafale nozzle, 5-deflector, 6-intake casing, 7-compressor, 8-mounting plate, 9-casing, 10-starter motor, 11-vaned diffuser, 12-combustion chamber, 13-guide vane, 14-turbine, 15-tail nozzle, 16-rotor, 17-rotor chamber. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the utility model more clear, the utility model is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the utility model and are not used to limit the utility model.

[0023] It should be noted that, in the description of the present invention, terms such as "up", "down", "left", "right", "inside", and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings. This is merely for the convenience of description and does not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the present invention.

[0024] In addition, it should be noted that in the description of the present invention, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0025] like Figure 1 As shown, a turbojet engine with standard starting comprises a casing 9, a combustion chamber 12, a fuel ignition system and a rotor chamber 17 are arranged on the inner side of the casing 9, a rotor 16, a turbine 14 installed at the rear end of the rotor 16, and a guide 13 arranged in front of the turbine 14 are arranged in the rotor chamber 17, a vaned diffuser 11 and a compressor 7 are respectively installed at the front end of the rotor 16, and a starter motor 10 is arranged in front of the compressor 7; a tail nozzle 15 is arranged at the rear of the turbine 14, the tail nozzle 15 is connected to the casing 9, a mounting plate 8 is pressed on the vaned diffuser 11, the outer side of the mounting plate 8 is connected to the casing 9, and the mounting plate 8 is also connected to the shroud 5 and the air intake casing 6 respectively, a cavity is enclosed between the shroud 5 and the air intake casing 6, wherein the starter motor 10 is inserted into the air intake casing 6 and is arranged coaxially with the compressor 7.

[0026] like Figure 1 As shown, the turbojet engine of the utility model further includes a nozzle, a powder gas generator 2 and a flameout detection unit, and the nozzle is a Rafale nozzle 4.

[0027] The Rafale nozzle 4 is arranged on the shell 9. The Rafale nozzle 4 is filled with gunpowder 3. One end of the Rafale nozzle 4 extends out of the shell 9, and the other end of the Rafale nozzle 4 extends into the rotor chamber 17 and is arranged toward the guide 13. Specifically, the Rafale nozzle 4 is arranged close to the guide 13. The Rafale nozzle 4 is a key component for providing high-speed airflow. The throat area of ​​the nozzle inside the combustion chamber 12 is set according to the working pressure to ensure the normal combustion of the gunpowder column.

[0028] The gunpowder gas generator 2 is arranged outside the housing 9, and the gunpowder gas generator 2 is arranged opposite to the gunpowder 3 at the port of the Rafale nozzle 4 so as to ignite the gunpowder 3; the gunpowder gas generator 2 is electrically connected to the engine electronic control unit 1, that is, the gunpowder gas generator 2 is started by the engine electronic control unit 1, and the gunpowder gas generator 2 used in the utility model ignites the gunpowder 3 with low electric ignition energy. The gunpowder 3 in the utility model includes a main gunpowder and an ignition tablet arranged at one end of the main gunpowder, and the ignition tablet is located at the outer end of the Rafale nozzle 4 and is arranged opposite to the gunpowder gas generator 2. A preferred solution is that the main gunpowder is columnar or tubular, the main gunpowder is a double-base propellant with a low burning rate, and the main gunpowder can be a tubular gunpowder with internal and external dual combustion. The tubular gunpowder has a simple structure, constant surface combustion, stable pressure, and good mechanical properties, which can be used in complex environments; wherein the ignition tablet is a double lead powder with a low ignition point, and the ignition pressure of the fuel system is set according to the size of the burning surface of the ignition tablet.

[0029] The flameout detection unit is used to detect the engine speed and temperature, and transmit the corresponding detection signal to the engine electronic control unit 1. The engine electronic control unit 1 controls the gunpowder gas generator 2 according to the detection signal. Specifically, the flameout detection unit includes a speed sensor and a temperature sensor. When the speed and temperature are lower than the preset flameout setting value, the engine electronic control unit 1 will determine that the engine is flameout and trigger the ignition system of the gunpowder gas generator 2 to ignite.

[0030] like Figure 1 As shown, after the turbojet engine with standard start of the utility model is put into use, when flying in the air, the flameout detection unit detects the engine speed and temperature in real time, and transmits the detection signal to the engine electronic control unit 1, and the engine electronic control unit 1 compares the detection signal with the preset flameout setting value. When the detection signal is lower than the preset flameout setting value, it indicates that the engine is about to flameout. At this time, the engine electronic control unit 1 starts the ignition system of the gunpowder gas generator 2, and the ignition system ignites the ignition tablets with low electrical ignition energy to generate high-temperature energy; when a certain pressure and temperature are established, the ignition tablets ignite the main gunpowder with a low burning rate to form high-temperature and high-pressure gas, and the high-temperature and high-pressure gas passes through the Rafale nozzle 4, generating a high-speed airflow that passes through the guide 13 to blow the turbine 14 to rotate at a high speed.

[0031] The rotating turbine 14 rotates with the coaxial engine rotor 16, and the engine speed begins to rise. When the engine speed reaches the starting ignition speed, the fuel ignition system starts to spray and ignite in the combustion chamber 12, and the turbine 14 begins to generate power. At this time, enough air has entered the engine, so that the gas temperature will not be too high when the combustion chamber 12 is ignited. After the combustion chamber 12 is ignited, the engine rotor 16 is driven by the turbine 14. As the engine speed increases, the power generated by the turbine 14 increases rapidly.

[0032] When the engine speed exceeds the minimum stable operating speed, the gas temperature before the turbine 14 is kept at the maximum allowable value, and the power of the turbine 14 is greater than the power consumed by the compressor 7. The engine speed is continuously increased by the power of the turbine 14 until the engine enters the slow working state, and the engine starts successfully.

[0033] It can be seen that the turbojet engine with standard start of the utility model solves the problem of flameout and restart in the air. When flameout occurs in the air, it can be quickly restarted in a short time with a lower current, and has the advantages of simple structure and light weight.

[0034] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications made within the spirit and principles of the present invention, improvements to a turbojet engine with a standard start, etc., should be included in the protection scope of the present invention.

Claims

1. A turbojet engine with a standard start, comprising a housing, a combustion chamber, a fuel ignition system and a rotor chamber are arranged inside the housing, a rotor, a turbine installed at the rear end of the rotor, and a guide arranged in front of the turbine are arranged in the rotor chamber, characterized in that: The engine also includes: a nozzle, the nozzle being arranged on the shell, the nozzle containing gunpowder, one end of the nozzle extending out of the shell, the other end of the nozzle extending into the rotor chamber and arranged toward the guide; A gunpowder gas generator, the gunpowder gas generator is arranged outside the shell, the gunpowder gas generator is arranged opposite to the gunpowder at the nozzle port, and the gunpowder gas generator is electrically connected to the engine electronic control unit; A flameout detection unit, the flameout detection unit is used to detect the engine speed and temperature and transmit corresponding detection signals to the engine electronic control unit, and the engine electronic control unit controls the gunpowder gas generator according to the detection signals.

2. The turbojet engine with standard start according to claim 1, characterized in that: The nozzle is a Rafale nozzle, and the Rafale nozzle is arranged close to the guide.

3. The turbojet engine with standard start according to claim 2, characterized in that: The working pressure in the combustion chamber is set according to the throat area of ​​the Rafale nozzle.

4. The turbojet engine with standard start according to claim 1, characterized in that: The gunpowder comprises a main gunpowder and an ignition tablet arranged at the outer end of the main gunpowder, and the ignition tablet is arranged opposite to the gunpowder gas generator.

5. The turbojet engine with standard start according to claim 4, characterized in that: The main gunpowder is in column or tube shape.

6. The turbojet engine with standard start according to claim 4, characterized in that: The ignition tablet is a double lead powder with a low ignition point.

7. The turbojet engine with standard start according to claim 4, characterized in that: The main gunpowder is a double-base propellant with a low burning rate.

8. The turbojet engine with standard start according to claim 4, characterized in that: The ignition pressure of the fuel ignition system is set according to the size of the burning surface of the ignition tablet.

9. The turbojet engine with standard start according to any one of claims 1 to 8, characterized in that: The engine also includes a vaned diffuser, a mounting plate, a deflector, a compressor and an air intake casing; The vaned diffuser is disposed in the rotor chamber and mounted at the front end of the rotor; The mounting plate is pressed on the vaned diffuser, and the mounting plate is connected to the housing; The deflector is connected to the mounting plate; The compressor is arranged in front of the vaned diffuser, and the compressor is arranged coaxially with the rotor; The air intake casing cover is arranged on the outer side of the compressor, and the air intake casing is connected to the mounting plate.

10. The turbojet engine with standard start according to claim 9, characterized in that: The engine also includes a starter motor, which is inserted into the air intake casing and is coaxially arranged with the compressor.

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