Cannon type starting system of small turbojet engine

Abstract

The utility model discloses a small turbojet engine cannon type starting system which comprises a gunpowder starter, the gunpowder starter comprises a shell, the shell is fixed with an outer shell, two ends of the shell are provided with openings, and a first cavity and a second cavity communicated with the first cavity are arranged in the shell; the gunpowder tube is mounted in the first chamber; the ignition powder tube is mounted in the second cavity; the igniter is connected with the opening in one end of the shell, and the igniter is matched with the ignition powder tube; the end socket is connected with the opening in the other end of the shell, and a drainage hole is formed in the end socket; one end of the nozzle is connected with the end socket, and the other end of the nozzle penetrates through the through hole in the outer shell and the guider to be in clearance fit with the turbine. According to the utility model, the small turbojet engine can be quickly started in the air.

Description

Technical Field

[0001] The utility model relates to the technical field of small turbojet engines, in particular to a cannon-type starting system for a small turbojet engine. Background Art

[0002] Theoretically, the rapid start of a turbojet engine is more complicated and difficult than a conventional start because the starting conditions are more stringent. There are many issues to consider during the rapid start of a turbojet engine, such as the ignition characteristics and flameout boundary of the combustion chamber, the working characteristics of the compressor, and the high temperature resistance limit performance of the turbine rotor blades.

[0003] At present, the domestic aviation industry has not conducted in-depth and extensive research on the cannon start technology of small turbojet engines, and there is even less research on the cannon start of turbojet engines using evaporative nozzles. Therefore, a small turbojet engine with a low-pressure fuel pump as the fuel supply equipment was taken as the research object. Through analysis and calculation and with the help of experimental means, relevant research and testing were carried out on the cannon start characteristics of small turbojet engines to obtain the fuel supply law and design method of the cannon start of small turbojet engines. Utility Model Content

[0004] The utility model provides a cannon-type starting system for a small turbojet engine. The utility model can enable the small turbojet engine to start quickly in the air.

[0005] A small turbojet engine cannon-type starting system includes a powder starter, the powder starter includes: a shell, the shell is fixed to an outer shell, both ends of the shell have openings, and a first chamber and a second chamber connected to the first chamber are arranged in the shell;

[0006] a powder tube, the powder tube being mounted in the first chamber;

[0007] an ignition powder tube, the ignition powder tube being installed in the second chamber;

[0008] An igniter, which is connected to an opening at one end of the shell and cooperates with an ignition powder tube;

[0009] A sealing head is connected to the opening at the other end of the shell and is provided with a drainage hole;

[0010] The nozzle has one end connected to the head, and the other end of the nozzle passes through the through hole on the outer shell and the guide and is matched with the turbine clearance.

[0011] Furthermore, the gunpowder starter also includes a buffer sleeve, which wraps the gunpowder tube, and both ends of the buffer sleeve are respectively provided with clearance holes.

[0012] Furthermore, the head includes an end cover, an inner connector, and an outer connector. The outer diameter of the inner connector is smaller than the outer diameter of the end cover. One end of the inner connector is fixed to the end cover, and the other end of the inner connector is inserted into the shell and threadedly connected to the shell. The end cover cooperates with the opening at the other end of the shell, and the outer connector is fixed to the other end of the end cover, and the outer connector is connected to one end of the nozzle.

[0013] Furthermore, the sealing head also includes a first sealing component, which is sleeved on the inner connecting body. When the inner connecting body is threadedly connected to the shell, the first sealing component is pressed between the inner connecting body and the shell.

[0014] Furthermore, it also includes a second sealing ring, which is pressed between the igniter and the shell.

[0015] The utility model has the following advantages:

[0016] 1. Using a gunpowder starter to replace the traditional starting system allows small turbojet engines to start quickly in the air, ensuring that the aircraft obtains sufficient thrust before reaching the minimum stall speed.

[0017] 2. Using gunpowder as a power source can make it easier to carry to remote areas.

[0018] 3. The use of high-strength and high-temperature resistant materials as the starter housing and nozzle can effectively resist the high temperature and pressure generated by the combustion of gunpowder.

[0019] 4. Use high-energy gunpowder as the power source to replace the electric starting system, which has the characteristics of small size, light weight and fast starting.

[0020] 5. The whole system has a compact structure and more reliable starting.

[0021] The small turbojet engine gunpowder starting system of the utility model is mainly used for the rapid air starting of the power systems of small unmanned aerial vehicles such as attack drones and cruise missiles. It adopts a powerful and efficient gunpowder starting system instead of the traditional electric starting system. After the aircraft is launched on the field battlefield, the small turbojet engine can be quickly started in a short time. In situations where energy is relatively scarce, the power source for starting the engine can be obtained, and the battlefield application effect is very good. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a structural diagram of the cannon-type starting system for a small turbojet engine.

[0023] Figure 2 This is a cross-sectional view of a gunpowder starter.

[0024] Markings in the accompanying drawings: compressor A, turbine shaft assembly B, oil supply assembly C, vent C1, guide D, turbine E, outer shell F, combustion chamber G, tail nozzle H, gas delivery channel I, gunpowder starter J, limit component K, shell 10, gunpowder tube 11, ignition powder tube 12, igniter 13, head 14, end cover 14a, inner connector 14b, outer connector 14c, nozzle 15, buffer sleeve 16, make way hole 16a, first sealing component 17, second sealing ring 18. DETAILED DESCRIPTION

[0025] The utility model is described in detail below in conjunction with the accompanying drawings.

[0026] like Figure 1 , is a small turbojet engine, which includes a compressor A, a turbine shaft assembly B, an oil supply assembly C, a guide D, a turbine E, an outer shell F, a combustion chamber G, and a tail nozzle H. One end of the turbine shaft assembly B is connected to the compressor A, and the other end of the turbine shaft assembly B passes through the oil supply assembly C and is fixed to the turbine E. A part of the oil supply assembly C is annular. After the compressor A is fixed to one end of the oil supply assembly C, an air delivery channel I is formed between the compressor A and the oil supply assembly C. The other end of the oil supply assembly C is fixed to the outer shell F. The oil supply assembly C is provided with an air vent C1 that matches the air delivery channel I. The guide D is located in the outer shell F and one end is fixed to the oil supply assembly C. The guide D surrounds the turbine E. The other end of the guide D is fixed to the combustion chamber G located in the outer shell F. One end of the tail nozzle H is fixed to the guide D, and the other end of the tail nozzle H extends to the outside of the outer shell F.

[0027] like Figure 1 A gunpowder starter J is installed on the small turbojet engine to form a cannon-type starting system for the small turbojet engine. The gunpowder starter J is fixed to an outer shell F, and a through hole is provided on the outer shell F. A part of the gunpowder starter J passes through the through hole on the outer shell F and the clearance between the guide D and the turbine E.

[0028] like Figure 1 The utility model processes a through hole at a position near the guide D of the outer casing F of the small turbojet engine, and a part of the gunpowder starter J passes through the outer casing F and the guide D and extends toward the blades of the turbine E. When the gunpowder starter J is working, high-temperature and high-pressure combustion gas is ejected from the nozzle and impacts the blades of the turbine E. The blades are forced to start rotating. As the high-temperature and high-pressure airflow continuously impacts the blades, the turbine E rotates at a high speed. When the turbine E rotates, it drives the coaxially connected turbine shaft assembly B and the compressor A to rotate, and the compressor A inhales air when it rotates.

[0029] like Figure 1When the speed of turbine E reaches the specified value, the small turbojet engine enters the ignition start program under the control of ECU. The pyrotechnic igniter ignites the fuel and air mixture in the combustion chamber and starts to burn in the combustion chamber. The airflow generated by compressor A increases the inlet pressure of the combustion chamber and increases the air flow rate to ensure the rapid combustion of the fuel in the combustion chamber. The fuel burns in the combustion chamber to release energy to generate high-temperature and high-pressure combustion gas, which expands and works in the flow channel of turbine E. The internal energy of the combustion gas is converted into the mechanical energy of turbine E. The small turbojet engine enters the starting operation state under the impact of the gunpowder starter J. The high-temperature combustion gas continues to blow the turbine E rotor, and turbine E drives compressor A to accelerate. Compressor A needs to consume the power obtained by turbine E from the combustion gas. At a low speed, the power consumed by compressor A is greater than the power obtained by turbine E. When the speed of turbine shaft assembly B reaches a certain value, the power obtained from turbine E can be greater than the power consumption of compressor A. The extra power can support the speed of turbine shaft assembly B to continue to rise. After reaching the working speed under the control of ECU, it is maintained at the working speed. The engine quickly enters normal operation within 6 seconds, and the gunpowder starting system completes its work.

[0030] like Figure 1 Compared with the traditional starting method, the gunpowder starting system has higher driving efficiency, smaller system weight, faster power output, and more convenient power acquisition method. The starting efficiency of small turbojet engines is greatly improved, the starting time is shortened, the starting speed is faster, and the starting operation is quick and efficient. Small turbojet engines can reach the specified operating speed in a short time, so that aircraft equipped with small turbojet engines can enter normal working state in a short time, effectively improving the system operation efficiency.

[0031] like Figure 1 and Figure 2 In the utility model, the gunpowder starter J includes a shell 10, a gunpowder tube 11, an ignition powder tube 12, an igniter 13, a head 14, and a nozzle 15. The shell 10 is fixed to the outer shell F, and both ends of the shell 10 have openings. The shell 10 is provided with a first chamber and a second chamber connected to the first chamber. The gunpowder tube 11 is installed in the first chamber, and the ignition powder tube 12 is installed in the second chamber; the igniter 13 is connected to the opening at one end of the shell 10, and the igniter 13 cooperates with the ignition powder tube 12; the head 14 is connected to the opening at the other end of the shell 10, and a drainage hole is provided on the head 14; one end of the nozzle 15 is connected to the head 14, and the other end of the nozzle 15 passes through the through hole on the outer shell F and the guide D and the turbine E clearance cooperate.

[0032] like Figure 2The gunpowder tube 11 is made of gunpowder and is cylindrical. The gunpowder tube 11 has a first axial flow channel, which is composed of a cylindrical hole and a conical hole. The diameter of the cylindrical hole is 5-8mm, and the diameter of the cylindrical hole is preferably 6mm. The conical hole corresponds to the output end of the ignition powder tube 12, and the taper of the conical hole is preferably 30°. The ignition powder tube 12 is made of gunpowder and is cylindrical. The ignition powder tube 12 is provided with a second axial flow channel. One end of the second axial flow channel matches the conical hole, and the other end of the second axial flow channel corresponds to the igniter 13. The igniter 13 is preferably an electronic igniter. The electric spark generated by the igniter 13 when working ignites the ignition powder tube 12. The airflow generated after the ignition powder tube 12 is ignited quickly flows along the first axial flow channel, and the gunpowder tube 11 is quickly heated and burned as a whole.

[0033] like Figure 2 The gunpowder starter J in the utility model also includes a buffer sleeve 16, which wraps the gunpowder tube 11. The two ends of the buffer sleeve 16 are respectively provided with a clearance hole 16a, one end of the clearance hole on the buffer sleeve 16 cooperates with the orifice at one end of the first axial flow channel, and the other end of the clearance hole on the buffer sleeve 16 cooperates with the orifice at the other end of the first axial flow channel.

[0034] like Figure 2 When the gunpowder tube 11 is loaded into the first chamber in the shell 10 and the end cap 14 is connected to the shell 10, pressure is generated on the end cap when the end cap 14 is connected to the shell 10, and then pressure is generated on the gunpowder tube 11, or other factors (such as vibration force during transportation) exert force on the gunpowder tube 11, which may easily cause the gunpowder tube 11 to become loose, or unsafe factors may occur when the force is too large. By installing the buffer sleeve 16, the buffer sleeve 16 can wrap the gunpowder tube 11, which can prevent the gunpowder tube 11 from becoming loose on the one hand, and on the other hand, the buffer sleeve 16 can absorb the external force and reduce the external force on the gunpowder tube 11, thereby improving the safety of the gunpowder tube 11.

[0035] like Figure 2 The end cap 14 includes an end cap 14a, an inner connector 14b, and an outer connector 14c. The outer diameter of the inner connector 14b is smaller than that of the end cap 14a. One end of the inner connector 14b is fixed to the end cap 14a. The other end of the inner connector 14b is inserted into the shell 10 and threadedly connected to the shell 10. The end cap 14a is matched with the opening at the other end of the shell 10. The outer connector 14c is fixed to the other end of the end cap 14a. The outer connector 14c is connected to one end of the nozzle 15. The inner connector 14b is annular, and the inner connector 14b surrounds or wraps a part of the gunpowder tube 11, thereby protecting the gunpowder tube 11.

[0036] like Figure 2The sealing head 14 further includes a first sealing component 17 , which is sleeved on the inner connector 14 b . When the inner connector 14 b is threadedly connected to the housing 10 , the first sealing component 17 is pressed between the inner connector 14 b and the housing 10 .

[0037] like Figure 2 The gunpowder starter J of the utility model further includes a second sealing ring 18 , which is compressed between the igniter 13 and the housing 10 .

[0038] like Figure 2 The sealing effect formed by the first sealing component 17 and the second sealing component 18 on the two ends of the shell 10 prevents moisture in the air from entering the interior of the shell 10, preventing the gunpowder tube 11 and the ignition powder tube 12 from getting wet, thereby ensuring that the gunpowder tube 11 and the ignition powder tube 12 can burn normally during use.

[0039] like Figure 1 A limiting component K is also fixed on the outer circumference of the outer casing F or the fuel supply assembly C of the small turbojet engine. The limiting component K cooperates with the gunpowder starter J. The limiting component K forms a limiting effect on the gunpowder starter J in both axial and radial directions.

Claims

1. A small turbojet engine cannon-type starting system, comprising a powder starter (J), characterized in that: The gunpowder starter (J) comprises: a shell (10), the shell (10) is fixed to an outer shell (F), both ends of the shell (10) have openings, and a first chamber and a second chamber communicating with the first chamber are arranged in the shell (10); A powder tube (11), the powder tube (11) is installed in the first chamber; An ignition powder tube (12), the ignition powder tube (12) being installed in the second chamber; An igniter (13), the igniter (13) is connected to an opening at one end of the housing (10), and the igniter (13) cooperates with the ignition powder tube (12); A sealing head (14), the sealing head (14) is connected to the opening at the other end of the shell (10), and a drainage hole is provided on the sealing head (14); A nozzle (15), one end of which is connected to the head (14), and the other end of which passes through a through hole on the outer shell (F) and a clearance fit between the guide (D) and the turbine (E).

2. The small turbojet engine cannon-type starting system according to claim 1 is characterized in that: The gunpowder starter (J) also includes a buffer sleeve (16), which wraps the gunpowder tube (11), and two ends of the buffer sleeve (16) are respectively provided with clearance holes (16a).

3. The small turbojet engine cannon-type starting system according to claim 1, characterized in that: The sealing head (14) comprises an end cover (14a), an inner connector (14b), and an outer connector (14c); the outer diameter of the inner connector (14b) is smaller than the outer diameter of the end cover (14a); one end of the inner connector (14b) is fixed to the end cover (14a); the other end of the inner connector (14b) is inserted into the shell (10) and is threadedly connected to the shell (10); the end cover (14a) cooperates with the opening at the other end of the shell (10); the outer connector (14c) is fixed to the other end of the end cover (14a); and the outer connector (14c) is connected to one end of the nozzle (15).

4. The small turbojet engine cannon-type starting system according to claim 3 is characterized in that: The sealing head (14) further comprises a first sealing component (17), which is sleeved on the inner connecting body (14b); when the inner connecting body (14b) is threadedly connected to the shell (10), the first sealing component (17) is pressed between the inner connecting body (14b) and the shell (10).

5. The small turbojet engine cannon-type starting system according to claim 1, characterized in that: The invention also comprises a second sealing ring (18), wherein the second sealing ring (18) is compressed between the igniter (13) and the housing (10).

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