CN211174361U - Starting and launching integrated system for micro turbojet engine - Google Patents

Abstract

The utility model relates to an integrated starting system for a miniature turbojet engine, comprising a turbojet engine and an engine electronic control system. The miniature turbojet engine is provided with a compressor, and the compressor is arranged in a casing of the compressor and enters the turbojet. The high-pressure airflow after the engine is supercharged enters the engine case through the diffuser, and is ejected from the tail nozzle. The gas compressed by the turbojet engine drives the generator to generate electricity, and supplies the electricity to the high-pressure air pump and the high-pressure air pump. The generated high-pressure gas is stored in the high-pressure gas cylinder, and at the same time, the high-pressure gas in the high-pressure gas cylinder is used to assist or lead the rotation of the rotor of the micro-turbojet engine, so as to help the turbojet engine to quickly enter the idle state; it is monitored by the engine electronic control system. When the turbojet engine is in the state, the pneumatic starting system is activated. When the turbojet engine enters the idle state, the ignition system is controlled to complete the ignition. The utility model effectively improves the endurance capacity and the starting capacity of the engine.

Description

Initiator integrated system for micro turbojet engine

technical field

The utility model relates to an integrated system for starting and generating electricity for a miniature turbojet engine.

Background technique

As a branch of the turbojet engine, the micro-turbojet engine has the advantages of high thrust-to-weight ratio and fast flight speed compared with the piston engine. Compared with the battery, it has the characteristics of high energy density and long battery life. It is an important power for future UAVs. direction. However, the existing micro-turbojet engine has no power generation system, and has a single function, which cannot support more electronic control functions; the fuel consumption rate is high, the energy utilization efficiency is low, and the battery life is short, which can only last for 3-10 minutes; It needs to carry a lot of batteries, and the flying weight of the aircraft is heavy. The airflow compressed by the compressor of the turbojet engine has a higher pressure. Effective use of this airflow to do work has very practical significance for energy saving and emission reduction.

The starting characteristics of the gas turbine engine are: first make the airflow flow, and then ignite and burn, that is, the engine must rotate first, and then start. According to this starting characteristic, it is necessary to drive the engine to rotate by other energy sources before ignition and combustion. In the previous low-power engine, the power required to drive the engine to a certain speed was small, so a starter motor was used to drive the engine to rotate, such as turboprop 5 and turboprop 6. However, with the advent of high-thrust engines, the electric motor has been unable to provide such a large amount of energy to drive the engine to reach the speed of ignition and combustion. Therefore, more energy is required to drive the engine.

The existing engine has only one starting system, and there is no alternative for special or emergency situations. The startup time of the existing startup system is 30s-60s. In special or emergency situations, the startup is required to be completed within 10 seconds, and the existing startup methods are invalid. Restricted by the ignition method and ignition environment, the existing start-up system cannot complete the start-up in the air flight state; the existing high-pressure gas start-up method has a limited gas storage capacity and can only perform a limited number of starts; after the gas in the gas cylinder is consumed, it cannot be independently replenished ; Empty gas cylinders and their systems become ineffective loads of the aircraft, reducing the performance of the aircraft.

SUMMARY OF THE INVENTION

The purpose of the utility model is to avoid the deficiencies of the prior art and provide a kind of power generation that effectively utilizes the airflow compressed by the turbojet engine through the compressor, and utilizes the high-pressure air pump and the high-pressure air cylinder to realize the cyclic use of the high-pressure air cylinder, effectively improving the A starter-integrated system for micro-turbojet engines that has endurance and can be started within 10 seconds in special or emergency situations.

In order to achieve the above purpose, the technical solution adopted by the present utility model is: a starting integrated system for a micro-miniature turbojet engine, comprising a turbojet engine and an engine electronic control system, and the micro-turbojet engine has a compressor, The compressor is set in the compressor casing, the airflow entering the turbojet engine is pressurized by the compressor, and the pressurized high-pressure airflow enters the engine combustion chamber through the diffuser for combustion. The nozzle is ejected, and also includes a high-pressure gas cylinder. The high-pressure gas cylinder guides the high-pressure air flow into the compressor casing of the micro-turbojet engine through the air duct, and the high-pressure air flow drives the compressor rotor to rotate, so that the micro-turbojet engine quickly enters In the idle speed state, a solenoid valve is arranged on the air guide pipe; it also includes an oil tank, and the oil tank is connected with the fuel injection pipe in the combustion chamber of the micro turbojet engine through the oil guide pipe, and the oil guide pipe is provided with a two-way connection. There is also an oil pump connected to the oil guide pipe between the oil tank and the two-way valve. The oil in the oil tank is pumped into the two-way valve through the oil pump, and then pumped into the combustion chamber of the micro-turbojet engine for ignition. The ignited oil quality At the same time, the high-pressure gas pressurized by the compressor is heated to form a high-temperature and high-pressure gas mixture and stably burn in the combustion chamber, so that the engine can start quickly and maintain high-power operation; it also includes a power generation device, which provides power for the high-pressure air pump, and the high-pressure air pump will The generated high-pressure gas is stored in the high-pressure gas cylinder through an air duct; the engine electronic control system is electrically connected to the battery, and the two-way valve, the solenoid valve and the oil pump are respectively electrically connected to the engine electronic control system; the engine The electronic control system is used to control the fuel pump to control the flow of aviation fuel and to control the opening and closing of the two-way valve and solenoid valve. The engine electronic control system is a Xicoy ECU controller.

Further, the power generating device includes a turbine and a generator, the drive shaft of the turbine is coaxially connected to the rotating shaft of the generator, the turbine is arranged in the turbine casing, the turbine casing is installed on the generator casing through the base, and the turbine casing is installed on the generator casing. A high-pressure air inlet is provided on the casing, and a high-pressure air outlet is provided on the engine casing at the high-pressure air outlet of the diffuser. The trachea is connected, and the trachea is fixed on the engine casing through the trachea connecting seat, and the air duct is provided with a flow electric control valve for flow regulation. In order to meet the demand for electricity under certain conditions, the flow rate of the airflow that is introduced into the turbine casing to drive the turbine is controlled; the high-pressure airflow is introduced into the turbine casing through the air duct, and impacts the turbine to drive the rotating shaft of the generator to rotate to generate electrical energy. The electrical energy generated by the generator It is output to the high pressure air pump through the output plug.

Further, the power generating device includes a turbine and a generator, the drive shaft of the turbine is coaxially connected to the rotating shaft of the generator, the turbine is arranged in the turbine casing, the turbine casing is installed on the generator casing through the base, and the turbine casing is installed on the generator casing. The box is provided with at least one high-pressure air inlet, and the tail nozzle is provided with at least one air pipe connection seat, one end of the air guide pipe is installed on the air pipe connection seat, and the other end of the air guide pipe is connected to the high pressure air inlet. The air ports are connected, and a flow electric control valve for flow regulation is arranged on the air guide pipe; the high-pressure air flow is introduced into the turbine casing through the air guide pipe in the tail nozzle, and impacts the turbine to drive the rotating shaft of the generator to rotate to generate electric energy , the electrical energy generated by the generator is output to the high-pressure air pump through the output plug.

Further, a voltage stabilization integrated module for stabilizing current is connected in series between the generator and the output plug. The voltage regulator integrated module is an integrated block composed of an analog circuit. There are many types on the market. The voltage regulator range is small and the precision is high. It protects the circuit and stabilizes the current generated by the generator.

Further, a high-temperature gas cooling device for cooling and storing the high-pressure gas flow is also communicated with the air duct.

Further, it also includes a bearing, the inner ring of the bearing is in transition fit with the rotating shaft of the generator, and the outer ring of the bearing is fixed inside the base; the base is fixed on the end cover of the generator by bolts; the turbine casing Mounted on the front end of the generator through the base. Bearings are used to support the mechanical rotating body, reduce the friction coefficient during its movement, and ensure its rotation accuracy.

Further, the included angle between the axis of the high-pressure gas inlet and the bleed air of the turbine casing is 15-60 degrees.

Further, the rotating shaft of the generator extends out of the generator, and the turbine is directly installed on the rotating shaft of the generator.

Further, an oil filter device is also communicated with the oil guide pipe between the oil tank and the oil pump.

Further, it also includes a display for displaying monitoring data, the display is electrically connected to the engine electronic control system; the temperature and rotational speed sensors of the micro turbojet engine transmit electronic signals to the engine electronic control system and display on the engine display.

The miniature turbojet engine is mainly composed of a compressor, an engine casing, a combustion chamber, a rotor shaft and a turbine, and the core engine is mainly used as a gas generator to provide high temperature and high pressure gas working medium.

The generator refers to a mechanical device that converts high-pressure gas into electrical energy, which is driven by a power machine, converts the energy of the high-pressure gas into mechanical energy and transmits it to the generator, which is then converted into electrical energy by the generator.

The beneficial effects of the present utility model are:

1. On the basis of the original engine starting system, the starting system is connected in parallel with different types of starting systems with wider applicability;

2. The high-pressure gas pressure in the starting system can reach up to 3Mpa, whether on the ground or in the air, the engine can be started within 10 seconds, which is suitable for more complex use requirements;

3. The start-up system can be started in 10 seconds in the air flight state, which greatly improves the use efficiency;

4. The start-up system can continuously replenish gas for the high-pressure gas cylinder during the running phase of the engine, which is available at any time, which improves the guarantee factor of the system;

5. The power generation capacity of the power generation device of the present utility model is 50 watts to 500 watts, which can be adjusted through the flow electric control valve, which supports the power consumption of the engine itself, and can expand more electric control functions at the same time;

6. The battery life is no longer limited by the battery, and the single airborne time is extended by more than 30% compared with the same model;

7. Reduce the excess load. Under the same take-off weight, the single flight time of the aircraft is increased by 30%-50%. The same fuel carrying capacity has a better thrust-to-weight ratio of the aircraft.

Description of drawings

Fig. 1 is the structural representation of the present utility model;

2 is a schematic structural diagram of a power generating device in Embodiment 1 of the present invention;

3 is a structural diagram of the connection between the generator and the base in Embodiment 1 of the present utility model;

4 is a structural diagram of the connection between the rotating shaft of the generator and the base in Embodiment 1 of the present utility model;

5 is a schematic structural diagram of the included angle between the axis of the high-pressure gas inlet and the bleed air of the turbine casing 3 in Embodiment 1 of the present invention;

6 is a schematic structural diagram of a power generating device in Embodiment 2 of the present invention.

Detailed ways

The principles and features of the present invention will be described below with reference to the accompanying drawings, and the examples are only used to explain the present invention, and are not intended to limit the scope of the present invention.

Embodiment 1: As shown in Figures 1-5, an integrated starting system for a micro turbojet engine includes a turbojet engine 8 and an engine electronic control system 14, and the micro turbojet engine 3 has a compressor 85. The compressor is arranged in the compressor casing, the airflow entering the turbojet engine 8 is pressurized by the compressor 85, and the pressurized high-pressure airflow enters the engine combustion chamber through the diffuser 86 for combustion, and the high-pressure gas after combustion passes through. The engine turbine is also ejected by the tail nozzle, and also includes a high-pressure gas cylinder 2. The high-pressure gas cylinder 2 introduces a high-pressure air flow into the compressor casing of the micro-turbojet engine 8 through an air duct, and the high-pressure air flow drives the compressor rotor to rotate, The micro-turbojet engine 8 is quickly entered into an idle state, and a solenoid valve 7 is arranged on the air guide pipe; it also includes an oil tank 9, and the oil tank 9 passes through the oil guide pipe and the fuel injection pipe in the combustion chamber of the micro-turbojet engine 8 A two-way valve 12 is provided on the oil guide pipe, and an oil pump 11 is also connected to the oil guide pipe between the oil tank 9 and the two-way valve 12. The oil in the oil tank 9 is pumped into the two-way valve 12 through the oil pump 11, and then It is pumped into the combustion chamber of the micro-turbojet engine 8 for ignition, and the ignited oil heats the high-pressure gas pressurized by the compressor at the same time, forming a high-temperature and high-pressure mixture and stably burning in the combustion chamber, enabling the engine to start quickly and keep high. Power operation; also includes a power generation device 4, the power generation device 4 provides power for the high-pressure air pump 3, and the high-pressure air pump 3 stores the generated high-pressure gas in the high-pressure gas cylinder 2 through an air guide; the engine electronic control system 14 and The battery 13 is electrically connected, and the two-way valve 12, the solenoid valve 7 and the oil pump 11 are respectively electrically connected to the engine electronic control system 14; the engine electronic control system 14 is used to control the oil pump 11 to control the flow of aviation fuel and control the two-way valve 12. The opening and closing of the solenoid valve 7. An oil filter device 10 is also communicated with the oil guide pipe between the oil tank 9 and the oil pump 11 . Also includes a display 15 for displaying monitoring data, the display 15 is electrically connected with the engine electronic control system 14; the temperature and rotational speed sensors provided by the micro turbojet engine 8 transmit electronic signals to the engine electronic control system 14 and display on the engine display. 15 on. The engine electronic control system 14 is a Xicoy ECU controller.

The power generating device 4 includes a turbine 41 and a generator 42 , the drive shaft of the turbine 41 is coaxially connected to the rotating shaft of the generator 42 , the turbine 41 is arranged in the turbine casing 43 , and the turbine casing 43 is installed on the generator through the base 44 . 42 casing, the turbine casing 43 is provided with a high-pressure gas inlet 45, the engine casing at the high-pressure airflow outlet of the diffuser 86 is provided with a high-pressure gas outlet 81, and the high-pressure gas outlet 81 is connected to the The high-pressure air inlets 45 on the turbine casing 43 are connected through an air duct, the air duct is fixed on the engine casing through the air duct connecting seat 82, and the air duct is provided with a flow rate for flow regulation. Electronically controlled valve 49; the high-pressure air flow is introduced into the turbine casing 43 through the air duct, and impacts the turbine 41 to drive the rotating shaft of the generator 42 to rotate to generate electrical energy. A voltage stabilization integrated module 421 for stabilizing current is connected in series between the generator 42 and the output plug 46 . The included angle between the axis of the high-pressure air inlet 45 and the bleed air of the turbine casing 43 is 15-60 degrees. The rotating shaft of the generator extends out of the generator, and the turbine is directly installed on the rotating shaft of the generator. It also includes a bearing 47, the inner ring of the bearing 47 is in transition fit with the rotating shaft of the generator 42, and the outer ring of the bearing 47 is fixed inside the base 44; the base 44 is fixed on the end of the generator 42 through bolts 48. Cover; the turbine casing 43 is mounted on the front end of the generator through the base 44.

The utility model uses the gas compressed by the turbojet engine 8 to drive the generator 42 to generate electric energy, and provides the electric energy to the high-pressure air pump 3, and the high-pressure air generated by the high-pressure air pump 3 is stored in the high-pressure air cylinder 2. The high-pressure gas in the bottle 2 assists or drives the rotor of the micro-turbojet engine to rotate, so as to help the turbojet engine 8 to quickly enter the idle state; the state of the turbojet engine 8 is monitored by the engine electronic control system 14, and the pneumatic starting system is activated, When the turbojet engine 8 enters the idle state, the ignition system is controlled to complete the ignition.

The power generation device includes: the utility model uses the air guide 5 to introduce the high-pressure air flow compressed by the compressor of the turbojet engine 9 into the flow electric control valve 6, and the flow electric control valve 6 adjusts the amount of electricity according to the different working conditions of the turbojet engine 9. According to the requirements, the flow rate of the airflow introduced into the turbine casing 3 is controlled, and then the turbine 4 is driven to rotate, the energy of the high-pressure gas is converted into the mechanical energy of the turbine 4, and then converted into electrical energy through the generator, so that the turbojet engine 8 can meet the requirements of the operation process. At the same time, each electronic unit supports more electronic control functions, improves battery life and reduces fuel consumption.

The pneumatic starting system includes: a one-way valve 1, a high-pressure gas cylinder 2, a high-pressure gas pump 3, and a high-pressure solenoid valve 7. The electric energy generated by the generator 42 can be supplied to the high-pressure air pump 3, so that the high-pressure air pump 3 compresses the airflow in the air, and pumps it into the high-pressure air cylinder 2 through the one-way valve 1, so as to realize the cyclic use of the high-pressure air cylinder 2, and solve the problem of existing problems. There is a problem that the gas cylinder of the high-pressure gas starting method has a limited gas storage capacity and can only be started for a limited number of times. When the startup system works, the high-pressure solenoid valve 7 is in an open state, so that the high-pressure gas in the high-pressure gas cylinder 2 is introduced into the compressor casing of the micro-turbojet engine 8 through the gas pipe, and then assists or leads the blowing of the micro-turbojet compressor rotor. Rotate to help the engine quickly enter the idle state. When the starting system is in a non-working state, the high-pressure solenoid valve 7 is in a closed state.

The ignition system includes: fuel tank 9 , filter 10 , fuel pump 11 , and two-way valve 12 . When the ignition system is working, the aviation fuel in the fuel tank 9 is introduced into the filter 10 through the fuel pipe, and after passing through the filter 10, most impurities in the aviation fuel are removed. The filtered aviation fuel is then introduced into the oil pump 11 through the oil pipe, pumped into the two-way valve 12 through the oil pump 11 , and then pumped into the combustion chamber of the micro-turbojet engine 8 . The two-way valve 12 of the present invention is a control valve with two pipelines. When it is in an open state, it is equivalent to a pipeline and can conduct fluid without obstruction. When it is in a closed state, it can cut off the fluid conduction. .

The control system includes: battery 13 , engine electronic control system 14 , and engine display 15 . The engine electronic control system 14 and the engine display 15 are powered by the battery 13 . The engine running state is monitored through the engine display 15 and the signal is transmitted to the engine electronic control system 14 . The oil pump 11 is controlled by the engine electronic control system 14 to control the flow of aviation fuel; The electrical energy stored in the battery 13 may come from electrical energy generated by the generator 42 .

Embodiment 2, as shown in FIG. 6, is the same as Embodiment 1, except that the power generating device 4 includes a turbine 41 and a generator 42. The drive shaft of the turbine 41 is coaxially connected to the rotating shaft of the generator 42, and the turbine 41 is arranged in the turbine casing 43, the turbine casing 43 is mounted on the casing of the generator 42 through the base 44, at least one high-pressure gas inlet 45 is arranged on the turbine casing 43, and the tail nozzle 83 is arranged with At least one air pipe connection seat 84, one end of the air guide pipe is installed on the air pipe connection seat 84, the other end of the air guide pipe is communicated with the described high-pressure gas inlet 45, and the described air guide pipe is provided with a flow rate for flow regulation. Electronically controlled valve 49; the high-pressure air flow is introduced into the turbine casing 43 through the air duct in the tail nozzle 83, and impacts the turbine 41 and then drives the rotating shaft of the generator to rotate to generate electric energy, and the electric energy generated by the generator 42 is output to the high pressure through the output plug 46 Air pump 3. A high-temperature gas cooling device 50 for cooling and storing the high-pressure gas flow is also communicated with the air duct.

Example 3: Same as Example 1, the difference is that the included angle between the axis of the high-pressure gas inlet 45 and the bleed air of the turbine casing 3 is 15 degrees.

Embodiment 4 is the same as Embodiment 1, except that the included angle between the axis of the high-pressure air inlet 45 and the bleed air of the turbine casing 3 is 45 degrees.

Embodiment 5 is the same as Embodiment 1, except that the included angle between the axis of the high-pressure gas inlet 45 and the bleed air of the turbine casing 3 is 60 degrees.

The above are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the present invention. within the scope of protection of the utility model.

Claims (10)

1. A starting and starting integrated system for a micro-miniature turbojet engine comprises the turbojet engine and an engine electronic control system, wherein the micro-miniature turbojet engine is provided with a gas compressor, a diffuser, an engine turbine and a tail spray pipe, and the gas compressor is arranged in a gas compressor casing; the micro-turbojet engine is characterized by further comprising an oil tank, wherein the oil tank is communicated with an oil injection pipe in a combustion chamber of the micro-turbojet engine through an oil guide pipe, the oil guide pipe is provided with a two-way valve, and an oil pump is communicated with the oil guide pipe between the oil tank and the two-way valve; the high-pressure air pump is used for generating high-pressure air; the two-way valve, the electromagnetic valve and the oil pump are respectively and electrically connected with the electronic control system of the engine; the electronic control system of the engine is used for controlling the oil pump so as to control the flow of the aviation fuel and control the opening and closing of the two-way valve and the electromagnetic valve.

2. The system as claimed in claim 1, wherein the power generating device comprises a turbine and a generator, a driving shaft of the turbine is coaxially connected with a rotating shaft of the generator, the turbine is disposed in a turbine casing, the turbine casing is mounted on the generator casing through a base, a high-pressure air inlet is disposed on the turbine casing, a high-pressure air outlet is disposed on the engine casing at a high-pressure air outlet of the diffuser, the high-pressure air outlet is communicated with the high-pressure air inlet on the turbine casing through an air duct, the air duct is fixed on the engine casing through an air duct connecting seat, and an electric flow control valve for flow control is disposed on the air duct; the high-pressure air flow is guided into the turbine casing through the air guide pipe, the turbine is impacted to drive the rotating shaft of the generator to rotate to generate electric energy, and the electric energy generated by the generator is output to the high-pressure air pump through the output plug.

3. The integrated starting system for a micro turbojet engine as claimed in claim 1, wherein the power generating device comprises a turbine and a generator, a driving shaft of the turbine is coaxially connected with a rotating shaft of the generator, the turbine is arranged in a turbine casing, the turbine casing is mounted on the generator casing through a base, at least one high-pressure air inlet is arranged on the turbine casing, at least one air pipe connecting seat is arranged on the tail nozzle, one end of the air pipe is mounted on the air pipe connecting seat, the other end of the air pipe is communicated with the high-pressure air inlet, and an electric flow control valve for flow regulation is arranged on the air pipe; the high-pressure air flow is guided into the turbine casing through the air guide pipe in the tail nozzle, the turbine is impacted, the rotating shaft of the generator is driven to rotate to generate electric energy, and the electric energy generated by the generator is output to the high-pressure air pump through the output plug.

4. The initiation integrated system for the micro turbojet engine as claimed in claim 3, wherein the gas guide pipe is further communicated with a high temperature gas cooling device for cooling and storing the high pressure gas flow.

5. The initiation integrating system for the micro turbojet engine as claimed in any one of claims 2 to 4, further comprising a bearing, wherein the inner ring of the bearing is in transition fit with the rotating shaft of the generator, and the outer ring of the bearing is fixed inside the base; the base is fixed on an end cover of the generator through a bolt; the turbine casing is mounted at the front end of the generator by a base.

6. The system as claimed in any one of claims 2 to 4, wherein the angle between the axis of the high pressure gas inlet and the bleed air of the turbine casing is 15 to 60 degrees.

7. The initiation integrated system for the micro turbojet engine as claimed in any one of claims 2 to 4, wherein the rotating shaft of the generator is arranged to extend out of the generator and the turbine is directly mounted on the rotating shaft of the generator.

8. The starting integrated system for the micro turbojet engine as claimed in any one of claims 2 to 4, wherein a voltage stabilizing integrated module for stabilizing current is connected in series between the generator and the output plug.

9. The starting integrated system for the micro turbojet engine as claimed in any one of claims 1 to 4, wherein an oil filter device is further communicated with the oil guide pipe between the oil tank and the oil pump.

10. The initiation integrating system for the micro turbojet engine as claimed in any one of claims 1 to 4, further comprising a display for displaying monitoring data, the display being electrically connected to the engine electronic control system; the microminiature turbojet engine is provided with a temperature sensor and a rotating speed sensor which transmit electronic signals to an engine electronic control system and display the electronic signals on an engine display.

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