CN110985215B - Integrated system for starting of micro turbojet engine - Google Patents
Integrated system for starting of micro turbojet engine Download PDFInfo
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- CN110985215B CN110985215B CN201911377596.6A CN201911377596A CN110985215B CN 110985215 B CN110985215 B CN 110985215B CN 201911377596 A CN201911377596 A CN 201911377596A CN 110985215 B CN110985215 B CN 110985215B
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- 238000002485 combustion reaction Methods 0.000 claims description 17
- 239000000446 fuel Substances 0.000 claims description 13
- 238000010248 power generation Methods 0.000 claims description 10
- 230000000087 stabilizing effect Effects 0.000 claims description 8
- 230000001276 controlling effect Effects 0.000 claims description 6
- 238000001816 cooling Methods 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims description 2
- 239000007858 starting material Substances 0.000 claims 3
- 230000037452 priming Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000000593 degrading effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000001914 filtration Methods 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/27—Fluid drives
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
- F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/30—Control of fuel supply characterised by variable fuel pump output
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention relates to an integrated starting system for a miniature turbojet engine, which comprises the turbojet engine and an engine electronic control system, wherein the miniature turbojet engine is provided with a compressor, the compressor is arranged in a compressor casing, high-pressure air flow entering the turbojet engine after pressurization enters the engine casing through a diffuser and is sprayed out from a tail nozzle, gas compressed by the turbojet engine drives a generator to generate electric energy, the electric energy is provided for a high-pressure air pump, high-pressure air generated by the high-pressure air pump is stored in a high-pressure air cylinder, and simultaneously, the rotor of the miniature turbojet engine is blown to rotate in an auxiliary or dominant mode by utilizing the high-pressure air in the high-pressure air cylinder so as to help the turbojet engine to quickly enter an idling state; the electronic control system of the engine monitors the state of the turbojet engine, a pneumatic starting system is started, and when the turbojet engine enters an idle state, the ignition system is controlled to complete ignition. The invention effectively improves the endurance and starting capability of the engine.
Description
Technical Field
The invention relates to a starting and generating integrated system for a miniature turbojet engine.
Background
The microminiature turbojet engine is used as one branch of a turbojet engine, has the advantages of high thrust-weight ratio and high flying speed relative to a piston engine, has the characteristics of high energy density and long endurance time relative to a battery, and is an important power direction of a future unmanned aerial vehicle. However, the existing miniature turbojet engine has no power generation system, has single function and cannot support more electric control functions; the fuel consumption rate is high, the energy utilization efficiency is low, the duration time is short, and the fuel consumption rate can only be maintained for 3-10 minutes; the long endurance operation needs to carry a large number of batteries, and the flight weight of the aircraft is high. The air flow of the turbojet engine compressed by the compressor has higher pressure. The effective utilization of the airflow to do work has very practical significance on energy conservation and emission reduction.
The starting characteristics of the gas turbine engine are: the air flow is firstly caused to flow, and then ignition combustion is carried out, namely the engine must be rotated first and then started. According to this starting feature, the engine must be rotated by another energy source prior to ignition combustion. On the former low-power engine, the power required for driving the engine to reach a certain rotating speed is small, and a starting motor is adopted to drive the engine to rotate, such as a vortex propeller 5 and a vortex propeller 6. However, with the advent of high thrust engines, such large amounts of energy have not been provided by the electric motor to drive the engine to the speed at which ignition is effected. And therefore requires a greater energy source to power the engine.
The existing engine has only one set of starting system, and has no alternative scheme when encountering special or emergency situations. The starting time of the existing starting system is 30s-60s, the starting is completed within 10 seconds under special or emergency conditions, and the existing starting mode is invalid. The existing starting system cannot finish starting in an air flight state due to the limitation of an ignition mode and an ignition environment; the existing high-pressure gas starting mode has the defects that the gas storage capacity of the gas cylinder is limited, and the gas cylinder can be started for a limited number of times; the gas in the gas cylinder cannot be independently replenished after being consumed; the empty gas cylinders and their systems become dead loads of the aircraft, degrading the aircraft performance.
Disclosure of Invention
The invention aims to avoid the defects of the prior art and provide an integrated starting system for the miniature turbojet engine, which can effectively utilize the air flow of the turbojet engine compressed by a compressor to generate electricity, and utilize a high-pressure air pump and a high-pressure air cylinder to realize the recycling of the high-pressure air cylinder, effectively improve the cruising ability and finish starting in 10 seconds under special or emergency conditions.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: the system comprises a turbojet engine and an engine electronic control system, wherein the miniature turbojet engine is provided with a compressor, the compressor is arranged in a compressor casing, air flow entering the turbojet engine is pressurized by the compressor, high-pressure air flow after pressurization enters an engine combustion chamber through a diffuser for combustion, the high-pressure air after combustion passes through an engine turbine and is sprayed out by a tail nozzle, the system further comprises a high-pressure air bottle, the high-pressure air bottle guides the high-pressure air flow into the compressor casing of the miniature turbojet engine through an air guide pipe, and the high-pressure air flow drives a compressor rotor to rotate, so that the miniature turbojet engine rapidly enters an idling state, and an electromagnetic valve is arranged on the air guide pipe; the oil tank is communicated with an oil injection pipe in the combustion chamber of the miniature turbojet engine through an oil guide pipe, a two-way valve is arranged on the oil guide pipe, an oil pump is also communicated on the oil guide pipe between the oil tank and the two-way valve, 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 miniature turbojet engine for ignition, the ignited oil heats high-pressure gas after the pressurization of the gas compressor at the same time, high-temperature high-pressure mixed gas is formed and is stably combusted in the combustion chamber, and the engine is enabled to be started quickly and kept to operate at high power; the high-pressure air pump is used for storing the generated high-pressure air into the high-pressure air cylinder through the air guide pipe; the electronic control system of the engine is electrically connected with the battery, and the two-way valve, the electromagnetic valve and the oil pump are respectively electrically connected with the electronic control system of the engine; the electronic engine control system is used for controlling the oil pump so as to control the aviation fuel flow and control the opening and closing of the two-way valve and the electromagnetic valve. The electronic control system of the engine is Xicoy ECU controllers.
Further, the power generation 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 arranged on the generator casing through a base, a high-pressure air inlet is formed in the turbine casing, a high-pressure air outlet is formed in 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 in the turbine casing through an air duct, the air duct is fixed on the engine casing through an air duct connecting seat, a flow electric control valve for flow regulation is arranged on the air duct, and the flow electric control valve can control the flow of air led into the turbine casing to drive the turbine according to the requirements of electric quantity under different working conditions of the engine; the high-pressure air flow is led into the turbine casing through the air duct, impacts the turbine and then drives 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.
Further, the power generation 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 arranged on the generator casing through a base, at least one high-pressure air inlet is formed in the turbine casing, at least one air pipe connecting seat is formed in the tail spray pipe, one end of an air pipe is arranged on the air pipe connecting seat, the other end of the air pipe is communicated with the high-pressure air inlet, and a flow electric control valve for regulating and controlling flow is arranged on the air pipe; the high-pressure air flow is led into the turbine casing through the air duct at the tail jet pipe, the turbine is impacted to drive the generator rotating shaft 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.
Further, a voltage stabilizing integrated module for stabilizing current is connected in series between the generator and the output plug. The voltage stabilizing integrated module is an integrated block formed by an analog circuit, is quite various in the market, has a small voltage stabilizing range and high precision, protects the circuit and stabilizes the current generated by the generator.
Furthermore, the air duct is also communicated with a high-temperature gas cooling device for cooling and storing the high-pressure air flow.
Further, the generator also comprises 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 in the base; the base is fixed on an end cover of the generator through bolts; the turbine casing is installed at the front end of the generator through the base. The bearing is used for supporting the mechanical rotating body, reducing the friction coefficient in the motion process and ensuring the rotation precision of the mechanical rotating body.
Further, the included angle between the axis of the high-pressure air inlet and the air entraining angle 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 arranged on the rotating shaft of the generator.
Furthermore, an oil filtering device is also communicated with an oil guide pipe between the oil tank and the oil pump.
Further, the engine monitoring system also comprises a display for displaying the monitoring data, and the display is electrically connected with the engine electronic control system; the miniature turbojet engine has temperature and rotation speed sensors that transmit electronic signals to an engine electronic control system and are displayed on an engine display.
The microminiature turbojet engine mainly comprises a gas compressor, an engine casing, a combustion chamber, a rotor shaft and a turbine, wherein the core engine is mainly used as a gas generator to provide high-temperature and high-pressure gas working medium.
The generator is mechanical equipment for converting high-pressure gas into electric energy, and is driven by a power machine, the energy of the high-pressure gas is converted into mechanical energy to be transmitted to the generator, and then the generator is used for converting the mechanical energy into the electric energy.
The beneficial effects of the invention are as follows:
1. the starting system is a starting system which is connected in parallel and has wider applicability and different types on the basis of the original engine starting system;
2. The highest pressure of high-pressure gas in the starting system can reach 3Mpa, and the engine can be started within 10 seconds no matter on the ground or in the air, so that the starting system is suitable for more complex use requirements;
3. The starting system can finish 10 seconds of starting in an air flight state, so that the use efficiency is greatly improved;
4. the starting system can continuously supplement gas for the high-pressure gas cylinder in the operation stage of the engine, can be used at any time, and improves the guarantee coefficient of the system;
5. the generating capacity of the generating device is 50-500 watts, and the generating capacity is adjustable through the flow electric control valve, so that the self power utilization of the engine is supported, and more electric control functions can be expanded;
6. The endurance time is not limited by the battery any more, and the single dead time is prolonged by more than 30% compared with the same model;
7. the extra load is reduced, the single flight time of the aircraft is increased by 30% -50% under the same take-off weight, the same fuel carrying amount is achieved, and the thrust-weight ratio of the aircraft is better.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic view showing the structure of a power generation device in embodiment 1 of the present invention;
FIG. 3 is a block diagram of the connection of the generator to the base in embodiment 1 of the present invention;
FIG. 4 is a structural view showing the connection of the generator rotating shaft to the base in embodiment 1 of the present invention;
Fig. 5 is a schematic structural diagram of the bleed angle between the axis of the high-pressure air inlet and the turbine casing 3 in embodiment 1 of the present invention;
fig. 6 is a schematic view of the structure of a power generation device in embodiment 2 of the present invention.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
Example 1: as shown in fig. 1-5, an integrated starting system for a micro turbojet engine comprises a turbojet engine 8 and an engine electronic control system 14, wherein the micro turbojet engine 3 is provided with a compressor 85, the compressor is arranged in a compressor casing, air flow entering the turbojet engine 8 is pressurized by the compressor 85, high-pressure air flow after pressurization enters an engine combustion chamber through a diffuser 86 to burn, the burnt high-pressure air passes through an engine turbine and is sprayed out by a tail nozzle, the integrated starting system further comprises a high-pressure air cylinder 2, the high-pressure air cylinder 2 guides the high-pressure air flow into the compressor casing of the micro turbojet engine 8 through an air duct, the high-pressure air flow drives a compressor rotor to rotate, so that the micro turbojet engine 8 quickly enters an idling state, and an electromagnetic valve 7 is arranged on the air duct; the engine is characterized by further comprising an oil tank 9, wherein the oil tank 9 is communicated with an oil injection pipe in a combustion chamber of the micro-turbojet engine 8 through an oil guide pipe, a two-way valve 12 is arranged on the oil guide pipe, an oil pump 11 is further communicated on the oil guide pipe between the oil tank 9 and the two-way valve 12, oil in the oil tank 9 is 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 for ignition, and the ignited oil heats high-pressure gas after the pressurization of the gas compressor to form high-temperature high-pressure mixed gas and stably burns in the combustion chamber, so that the engine is started quickly and keeps high-power operation; the high-pressure air pump 3 stores the generated high-pressure air into the high-pressure air cylinder 2 through an air duct; the electronic engine control system 14 is electrically connected with the battery 13, and the two-way valve 12, the electromagnetic valve 7 and the oil pump 11 are respectively electrically connected with the electronic engine control system 14; the electronic engine control system 14 is used for controlling the oil pump 11 to control the aviation fuel flow and to control the opening and closing of the two-way valve 12, the solenoid valve 7. An oil filter device 10 is also communicated with an oil guide pipe between the oil tank 9 and the oil pump 11. The system also comprises a display 15 for displaying monitoring data, wherein the display 15 is electrically connected with the engine electronic control system 14; the temperature and rotational speed sensors of the micro turbojet engine 8 transmit electronic signals to the engine electronic control system 14 and are displayed on the engine display 15. The engine electronic control system 14 is Xicoy ECU.
The power generation device 4 comprises a turbine 41 and a generator 42, a driving shaft of the turbine 41 is coaxially connected with a rotating shaft of the generator 42, the turbine 41 is arranged in a turbine casing 43, the turbine casing 43 is installed on the generator 42 casing through a base 44, a high-pressure air inlet 45 is arranged on the turbine casing 43, a high-pressure air outlet 81 is arranged on an engine casing at a high-pressure air outlet of the diffuser 86, the high-pressure air outlet 81 is communicated with the high-pressure air inlet 45 on the turbine casing 43 through an air duct, the air duct is fixed on the engine casing through an air duct connecting seat 82, and a flow electric control valve 49 for flow regulation is arranged on the air duct; the high-pressure air flow is led into the turbine casing 43 through the air duct, impacts the turbine 41 and drives the rotating shaft of the generator 42 to rotate to generate electric energy, and the electric energy generated by the generator 42 is output to the high-pressure air pump 3 through the output plug 46. A voltage stabilizing 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 arranged on the rotating shaft of the generator. The motor generator also comprises a bearing 47, wherein 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 secured to the end cap of the generator 42 by bolts 48; the turbine casing 43 is mounted at the front end of the generator by a pedestal 44.
The invention utilizes the gas compressed by the turbojet engine 8 to drive the generator 42 to generate electric energy, and provides the electric energy for the high-pressure air pump 3, the high-pressure air generated by the high-pressure air pump 3 is stored in the high-pressure air cylinder 2, and simultaneously, the rotor of the miniature turbojet engine is blown to rotate in an auxiliary or dominant way by utilizing the high-pressure air in the high-pressure air cylinder 2 so as to help the turbojet engine 8 to quickly enter an idle state; the state of the turbojet engine 8 is monitored by the electronic engine control system 14, a pneumatic starting system is started, and when the turbojet engine 8 enters an idle state, the ignition system is controlled to complete ignition.
The power generation device includes: according to the invention, the high-pressure air flow compressed by the air compressor of the turbojet engine 9 is introduced into the flow electric control valve 6 by utilizing the air duct 5, the flow electric control valve 6 controls the air flow introduced into the turbine casing 3 according to the electric quantity requirements of the turbojet engine 9 under different working conditions, so that the turbine 4 is driven to rotate, the energy of the high-pressure air is converted into the mechanical energy of the turbine 4, and then the mechanical energy is converted into electric energy by the generator, thereby realizing that the turbojet engine 8 can support more electric control functions while meeting the electric power requirements of each electronic unit in the running process, improving the cruising ability and reducing the fuel consumption rate.
The pneumatic starting system comprises: one-way valve 1, high-pressure gas cylinder 2, high-pressure gas pump 3, high-pressure electromagnetic 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 air flow in air and pumps the air into the high-pressure air cylinder 2 through the one-way valve 1, thereby realizing the recycling of the high-pressure air cylinder 2, and solving the problems that the air storage capacity of the air cylinder is limited and only the starting of limited times can be performed in the existing high-pressure air starting mode. When the starting system works, the high-pressure electromagnetic valve 7 is in an opening state, so that high-pressure gas in the high-pressure gas cylinder 2 is led into a compressor casing of the miniature turbojet engine 8 through a gas pipe, and further the rotor of the miniature turbojet engine is assisted or mainly blown to rotate, and the engine is helped to quickly enter an idling state. When the starting system is in the non-operating state, the high-pressure solenoid valve 7 is in the closed state.
The ignition system includes: the oil tank 9, the filter 10, the oil pump 11, and the two-way valve 12. When the ignition system is in operation, the aviation fuel in the oil tank 9 is led into the filter 10 through the oil pipe, and most of impurities in the aviation fuel are removed after the aviation fuel passes through the filter 10. The filtered aviation fuel is led into an oil pump 11 through an oil pipe, is pumped into a two-way valve 12 through the oil pump 11, and is further pumped into a combustion chamber of the micro turbojet engine 8. The two-way valve 12 of the present invention is a control valve having two lines, which corresponds to a line when in an open state, and which is capable of conducting fluid without obstruction, and which is capable of blocking fluid conduction when in a closed state.
The control system comprises: battery 13, engine electronic control system 14, engine display 15. The motor electronic control system 14 and the motor display 15 are powered by a battery 13. The engine operating conditions are monitored by an engine display 15 and signals are transmitted to the engine electronic control system 14. The oil pump 11 is controlled by the engine electronic control system 14 to control the aviation fuel flow; the electronic control system 14 of the engine controls the two-way valve 12 to open and close, so that aviation fuel pumped by the oil pump 11 enters the micro turbojet engine 8. The electrical energy stored by the battery 13 may be derived from electrical energy generated by the generator 42.
Embodiment 2, as shown in fig. 6, the same as embodiment 1, except that the power generation device 4 includes a turbine 41 and a generator 42, a driving shaft of the turbine 41 is coaxially connected with a rotating shaft of the generator 42, the turbine 41 is disposed in a turbine housing 43, the turbine housing 43 is mounted on the housing of the generator 42 through a base 44, at least one high-pressure air inlet 45 is disposed on the turbine housing 43, at least one air pipe connecting seat 84 is disposed on the tail pipe 83, one end of an air pipe is mounted on the air pipe connecting seat 84, the other end of the air pipe is communicated with the high-pressure air inlet 45, and a flow electric control valve 49 for flow regulation is disposed on the air pipe; the high-pressure air flow is led into the turbine casing 43 through the air duct at the tail nozzle 83, impacts the turbine 41 and drives the generator rotating shaft to rotate to generate electric energy, and the electric energy generated by the generator 42 is output to the high-pressure air pump 3 through the output plug 46. The air duct is also communicated with a high-temperature gas cooling device 50 for cooling and storing the high-pressure air flow.
Example 3: the same as in example 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 15 degrees.
Example 4 is the same as example 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.
Example 5 is the same as example 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 60 degrees.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (8)
1. The system is characterized by also comprising a high-pressure gas cylinder, the high-pressure gas cylinder guides the high-pressure gas flow into the compressor casing of the miniature turbojet engine through a gas guide pipe, and the high-pressure gas flow drives a rotor of the compressor to rotate so that the miniature turbojet engine quickly enters an idling state, and the gas guide pipe is provided with an electromagnetic valve; the oil tank is communicated with an oil injection pipe in a combustion chamber of the microminiature turbojet engine through an oil guide pipe, a two-way valve is arranged on the oil guide pipe, an oil pump is also communicated on the oil guide pipe between the oil tank and the two-way valve, 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 microminiature turbojet engine for ignition, and the ignited oil heats high-pressure gas after the pressurization of the gas compressor to form high-temperature high-pressure mixed gas and stably burn in the combustion chamber, so that the engine is quickly started and keeps high-power operation; the high-pressure air pump is used for storing the generated high-pressure air into the high-pressure air cylinder through the air guide pipe; the electronic control system of the engine is electrically connected with the battery, and the two-way valve, the electromagnetic valve and the oil pump are respectively electrically connected with the electronic control system of the engine; the electronic engine control system is used for controlling the oil pump so as to control the aviation fuel flow and control the opening and closing of the two-way valve and the electromagnetic valve; the power generation 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 arranged on the generator casing through a base, a high-pressure air inlet is formed in the turbine casing, a high-pressure air outlet is formed in the engine casing at a high-pressure air outlet of a diffuser, the high-pressure air outlet is communicated with the high-pressure air inlet in the turbine casing through an air duct, the air duct is fixed on the engine casing through an air duct connecting seat, and a flow electric control valve for regulating and controlling flow is arranged on the air duct; the high-pressure air flow is led into the turbine casing through the air duct, impacts the turbine and drives 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;
Or the power generation 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 arranged on the generator casing through a base, at least one high-pressure air inlet is formed in the turbine casing, at least one air pipe connecting seat is formed in the tail spray pipe, one end of an air pipe is arranged on the air pipe connecting seat, the other end of the air pipe is communicated with the high-pressure air inlet, and a flow electric control valve for regulating and controlling flow is arranged on the air pipe; the high-pressure air flow is led into the turbine casing through the air duct at the tail jet pipe, the turbine is impacted to drive the generator rotating shaft 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.
2. The integrated system for starting a micro-turbojet engine according to claim 1, wherein the air duct is further communicated with a high-temperature gas cooling device for cooling and storing high-pressure air flow.
3. The integrated system for starting a miniature turbojet engine of claim 1, further comprising a bearing, wherein an inner ring of the bearing is in transition fit with a rotating shaft of a generator, and an outer ring of the bearing is fixed inside the base; the base is fixed on an end cover of the generator through bolts; the turbine casing is installed at the front end of the generator through the base.
4. The integrated priming system for a miniature turbojet engine of claim 1, wherein the axis of the high pressure air intake is at an included angle of 15-60 degrees to the bleed air of the turbine casing.
5. The integrated starter system for a micro-turbojet engine of claim 1, wherein the rotating shaft of the generator extends out of the generator, and the turbine is directly mounted on the rotating shaft of the generator.
6. The integrated starter system for a micro-turbojet engine of claim 1, wherein a voltage stabilizing integrated module for stabilizing current is connected in series between the generator and the output plug.
7. The integrated system for the start-up of a micro-turbojet engine according to any one of claims 1 to 6, characterized in that an oil filter device is also in communication with the oil conduit between the oil tank and the oil pump.
8. The integrated starter system for a micro-turbojet engine of any one of claims 1-6, further comprising a display for displaying monitoring data, the display being electrically connected to the engine electronic control system; the temperature and rotation speed sensors of the microminiature turbojet engine transmit electronic signals to an electronic engine control system and are displayed on an engine display.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911377596.6A CN110985215B (en) | 2019-12-27 | 2019-12-27 | Integrated system for starting of micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911377596.6A CN110985215B (en) | 2019-12-27 | 2019-12-27 | Integrated system for starting of micro turbojet engine |
Publications (2)
| Publication Number | Publication Date |
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| CN110985215A CN110985215A (en) | 2020-04-10 |
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| CN111751078A (en) * | 2020-08-10 | 2020-10-09 | 成都志胜空天动力科技有限公司 | Method for simulating performance parameters of turbine engine in test and multi-electric high-temperature turbine simulator |
| CN116771434A (en) * | 2021-12-01 | 2023-09-19 | 西安觉天动力科技有限责任公司 | Working medium driven micro turbine power generation device |
| CN114235421B (en) * | 2021-12-06 | 2023-12-26 | 中国科学院工程热物理研究所 | Device and method for measuring maximum fuel flow limit line of turbojet engine |
| CN114872908B (en) * | 2022-06-08 | 2024-03-26 | 中国航空发动机研究院 | Jet pipe device and aeroengine |
| CN114954964B (en) * | 2022-06-08 | 2024-04-16 | 中国航空发动机研究院 | Jet pipe device and aeroengine |
| CN116374179B (en) * | 2023-06-05 | 2023-09-15 | 中国航发四川燃气涡轮研究院 | Series hybrid electric propulsion system |
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