CN110985215A - Starting and launching integrated system for micro turbojet engine - Google Patents
Starting and launching integrated system for micro turbojet engine Download PDFInfo
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- CN110985215A CN110985215A CN201911377596.6A CN201911377596A CN110985215A CN 110985215 A CN110985215 A CN 110985215A CN 201911377596 A CN201911377596 A CN 201911377596A CN 110985215 A CN110985215 A CN 110985215A
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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
Abstract
The invention relates to a starting and starting integrated system for a micro-turbojet engine, which comprises the turbojet engine and an engine electronic control system, wherein the micro turbojet engine is provided with a gas compressor, the gas compressor is arranged in a gas compressor casing, high-pressure gas flow after entering the turbojet engine and being pressurized enters the engine casing through a diffuser and is sprayed out from a tail spray pipe, gas compressed by the turbojet engine drives a generator to generate electric energy and provides the electric energy to a high-pressure gas pump, the high-pressure gas generated by the high-pressure gas pump is stored in a high-pressure gas bottle, and meanwhile, the high-pressure gas in the high-pressure gas bottle is used for assisting or leading a rotor of the micro turbojet engine to rotate so as to help the turbojet engine to rapidly enter an idling state; the electronic control system of the engine monitors the state of the turbojet engine, the pneumatic starting system is started, and after the turbojet engine enters an idle state, the ignition system is controlled to finish ignition. The invention effectively improves the cruising ability and the starting ability of the engine.
Description
Technical Field
The invention relates to a starting and power generating integrated system for a micro turbojet engine.
Background
The microminiature turbojet engine is used as a branch of the 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 the future unmanned aerial vehicle. However, the existing micro turbojet engine has no power generation system and single function, and cannot support more electric control functions; the fuel consumption rate is high, the energy utilization efficiency is low, the endurance time is short, and the duration can be maintained for only 3-10 minutes; and a large number of batteries are required to be carried for long-endurance operation, and the flying weight of the aircraft is large. 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 for energy conservation and emission reduction.
The starting characteristics of the gas turbine engine are: the air flow is made to flow and then the combustion is ignited, i.e. the engine must be started after being rotated. According to this starting feature, the engine must be rotated by another energy source before ignition combustion. On the former low-power engine, the power required for driving the engine to reach a certain rotating speed is low, and a starting motor is adopted to drive the engine to rotate, such as a turboprop 5 and a 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 power the engine to the speed at which ignition and combustion occur. And therefore a greater energy source is required to power the engine.
The existing engine only has one set of starting system, and no alternative is available in special or emergency situations. The starting time of the existing starting system is 30-60 s, the starting is required to be completed within 10 seconds under special or emergency conditions, and the existing starting mode is invalid. Limited by an ignition mode and an ignition environment, the conventional starting system cannot complete starting in an air flight state; the gas storage capacity of the existing high-pressure gas starting mode gas cylinder is limited, and only limited starting times can be carried out; the gas in the gas cylinder cannot be independently supplemented after being consumed; the spent cylinders and their systems become the ineffective load on the aircraft, reducing aircraft performance.
Disclosure of Invention
The invention aims to avoid the defects of the prior art and provide an initiation integrated system for a micro turbojet engine, which effectively utilizes the airflow of the turbojet engine compressed by a compressor to generate electricity, utilizes a high-pressure air pump and a high-pressure air bottle to realize the recycling of the high-pressure air bottle, effectively improves the endurance capacity and can finish the startup within 10 seconds under special or emergency conditions.
In order to achieve the purpose, the invention adopts the technical scheme that: a starting and starting integrated system for a micro turbojet engine comprises the turbojet engine and an engine electronic control system, wherein the micro turbojet engine is provided with a gas compressor, the gas compressor is arranged in a gas compressor casing, gas flow entering the turbojet engine is pressurized by the gas compressor, the pressurized high-pressure gas flow enters a combustion chamber of the engine through a diffuser for combustion, and the combusted high-pressure gas passes through a turbine of the engine and is sprayed out from a tail nozzle; the oil in the oil tank is pumped into the two-way valve through the oil pump and then pumped into a combustion chamber of the micro turbojet engine for ignition, and the ignited oil simultaneously 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 quickly started and keeps high-power operation; 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. The electronic control system of the engine is an Xicoy ECU controller.
Furthermore, the power generation device comprises a turbine and a generator, wherein 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 installed 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 an engine casing at a high-pressure air flow outlet of the diffuser, the high-pressure air outlet is communicated with the high-pressure air inlet in the turbine casing through an air guide pipe, the air guide pipe is fixed on the engine casing through an air guide pipe connecting seat, a flow electric control valve for flow regulation is arranged on the air guide pipe, and the flow electric control valve can control the flow of air introduced into the turbine casing to drive the turbine according to the requirements of the engine on electric quantity under different working conditions; 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.
Furthermore, 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 installed 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 arranged on the tail spray pipe, one end of an air guide pipe is installed on the air pipe connecting seat, the other end of the air guide pipe is communicated with the high-pressure air inlet, and a flow electric control valve for flow regulation is arranged on the air guide 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.
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, has a plurality of types on the market, 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 gas flow.
Furthermore, the generator also comprises a bearing, an inner ring of the bearing is in transition fit with a rotating shaft of the generator, and an outer ring of the bearing is fixed in 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. The bearing is used for supporting the mechanical rotating body, reducing the friction coefficient in the moving process of the mechanical rotating body and ensuring the rotation precision of the mechanical rotating body.
Furthermore, the included angle between the axis of the high-pressure air inlet and the bleed air of the turbine casing is 15-60 degrees.
Furthermore, the rotating shaft of the generator extends out of the generator, and the turbine is directly mounted on the rotating shaft of the generator.
Furthermore, an oil filter device is communicated with an oil guide pipe between the oil tank and the oil pump.
Further, the monitoring system also comprises a display for displaying the monitoring data, wherein the display is electrically connected with the electronic control system of the engine; the micro turbojet engine is provided with a temperature and rotating speed sensor which transmits an electronic signal to an engine electronic control system and displays the electronic signal on an engine display.
The micro turbojet engine mainly comprises a gas compressor, an engine casing, a combustion chamber, a rotor shaft and a turbine, and the core mainly serves as a gas generator and provides high-temperature and high-pressure gas working media.
The generator is mechanical equipment for converting high-pressure gas into electric energy, is driven by power machinery, converts the energy of the high-pressure gas into mechanical energy and transmits the mechanical energy to the generator, and then converts the mechanical energy into the electric energy by the generator.
The invention has the beneficial effects that:
1. the starting system is a starting system which is accessed in parallel on the basis of the original engine starting system and has different types and wider applicability;
2. the high-pressure gas pressure in the starting system can reach 3Mpa at most, and the starting of the engine can be finished 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 at the running stage of the engine, and can be used at any time, so that the guarantee coefficient of the system is improved;
5. the generating set has the generating capacity of 50-500 watts, is adjustable through the flow electric control valve, supports the self power consumption of the engine, and can expand more electric control functions;
6. the endurance time is not limited by a battery any more, and the single-time dead time is prolonged by more than 30 percent compared with the same type;
7. the redundant load is reduced, the single flight time of the aircraft is increased by 30% -50% under the same takeoff weight, the fuel carrying capacity is the same, and the thrust-weight ratio of the aircraft is better.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of a power generating apparatus in embodiment 1 of the present invention;
FIG. 3 is a structural view of a generator to be connected to a base in embodiment 1 of the present invention;
FIG. 4 is a structural view of a connection between a rotating shaft of a generator and a base in embodiment 1 of the present invention;
fig. 5 is a schematic structural diagram of an 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 invention;
fig. 6 is a schematic structural view of a power generation device in embodiment 2 of the present invention.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Example 1: as shown in fig. 1-5, an initiation integrated 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 gas compressor 85, the gas compressor is arranged in a gas compressor casing, gas flow entering the turbojet engine 8 is pressurized by the gas compressor 85, the pressurized high-pressure gas flow enters an engine combustion chamber through a diffuser 86 for combustion, the combusted high-pressure gas passes through an engine turbine and is ejected by a tail nozzle, the initiation integrated system further comprises a high-pressure gas cylinder 2, the high-pressure gas cylinder 2 guides the high-pressure gas flow into the gas compressor casing of the micro turbojet engine 8 through a gas guide pipe, the high-pressure gas flow drives a gas compressor rotor to rotate, so that the micro turbojet engine 8 rapidly enters an idling state, and the gas guide pipe is provided with an electromagnetic valve 7; 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, the oil guide pipe is provided with a two-way valve 12, the oil guide pipe between the oil tank 9 and the two-way valve 12 is also communicated with an oil pump 11, 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 pressurized by a gas compressor at the same time to form high-temperature high-pressure mixed gas and stably combust in the combustion chamber, so that the engine is quickly started and keeps high-power operation; the high-pressure gas pump is characterized by further comprising a power generation device 4, wherein the power generation device 4 provides power for the high-pressure gas pump 3, and the high-pressure gas pump 3 stores the generated high-pressure gas into the high-pressure gas bottle 2 through a gas guide pipe; the engine electronic 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 engine electronic control system 14; the electronic engine control system 14 is used for controlling the oil pump 11 to control the aviation fuel flow and controlling the opening and closing of the two-way valve 12 and the electromagnetic valve 7. An oil filter device 10 is also communicated on an oil guide pipe between the oil tank 9 and the oil pump 11. The monitoring device also comprises a display 15 for displaying monitoring data, wherein the display 15 is electrically connected with the electronic engine control system 14; the micro turbojet engine 8 has temperature and speed sensors that 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 an Xicoy ECU controller.
The power generation device 4 comprises a turbine 41 and a generator 42, wherein 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 the engine casing at a high-pressure air flow outlet of a 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 guide pipe, the air guide pipe is fixed on the engine casing through an air guide pipe connecting seat 82, and a flow electric control valve 49 for flow regulation is arranged on the air guide pipe; the high-pressure air flow is guided 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 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 installed on the rotating shaft of the generator. The generator also comprises 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 in the base 44; the base 44 is fixed on the end cover of the generator 42 through bolts 48; the turbine case 43 is mounted to the front end of the generator by a base 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 bottle 2, and meanwhile, the high-pressure air in the high-pressure air bottle 2 is utilized to assist or lead the rotor of the micro turbojet engine to rotate so as to help the turbojet engine 8 to rapidly enter an idling state; the electronic control system 14 of the engine monitors the state of the turbojet engine 8, starts the pneumatic starting system, and controls the ignition system to finish ignition after the turbojet engine 8 enters an idle state.
The power generation device includes: according to the invention, the high-pressure airflow compressed by the compressor of the turbojet engine 9 is introduced into the flow electric control valve 6 by using the air guide pipe 5, the flow electric control valve 6 controls the airflow flow led into the turbine box 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 the electric energy by the generator, so that the turbojet engine 8 can meet the electric power requirements of each electronic unit in the operation process, simultaneously support more electric control functions, improve the cruising ability and reduce the oil consumption rate.
The pneumatic starting system comprises: the device comprises a check valve 1, a high-pressure gas cylinder 2, a high-pressure gas pump 3 and a high-pressure electromagnetic valve 7. The electric energy that generator 42 produced can supply with high-pressure gas pump 3, makes high-pressure gas pump 3 compress the air current in with the air to in going into high-pressure gas cylinder 2 through check valve 1 pump, realize high-pressure gas cylinder 2's cyclic utilization, it is limited to have solved current high-pressure gas starting mode gas cylinder gas storage volume, can only carry out the problem of the start-up of limited number of times. When the starting system works, the high-pressure electromagnetic valve 7 is in an open state, so that high-pressure gas in the high-pressure gas bottle 2 is led into a compressor casing of the micro turbojet engine 8 through a gas pipe, and then the micro turbojet compressor rotor is assisted or mainly blown to rotate, and the engine is helped to rapidly enter an idle state. When the starting system is in a non-working state, the high-pressure electromagnetic valve 7 is in a 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 fuel tank 9 is guided into the filter 10 through the oil pipe, and most impurities in the aviation fuel are removed after passing through the filter 10. The filtered aviation fuel is then led into the oil pump 11 through the oil pipe, pumped into the two-way valve 12 through the oil pump 11, and further pumped into the combustion chamber of the micro turbojet engine 8. The two-way valve 12 of the present invention is a control valve having two pipes, and is equivalent to a pipe in an open state, and can conduct a fluid without hindrance, and can block the fluid conduction in a closed state.
The control system includes: a battery 13, an engine electronic control system 14 and an engine display 15. The engine electronic control system 14 and the engine display 15 are powered by a battery 13. The engine operating conditions are monitored by the engine display 15 and signals are transmitted to the engine electronic control system 14. The oil pump 11 is controlled by the electronic engine control system 14 to control the aviation fuel flow; the electronic control system 14 of the engine controls the two-way valve 12 to be opened and closed, so that the 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 the electrical energy generated by the generator 42.
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: and 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 above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A starting and starting integrated system for a micro turbojet engine comprises the turbojet engine and an engine electronic control system, wherein the micro turbojet engine is provided with a gas compressor, the gas compressor is arranged in a gas compressor casing, gas flow entering the turbojet engine is pressurized by the gas compressor, the pressurized high-pressure gas flow enters a combustion chamber of the engine through a diffuser for combustion, and the combusted high-pressure gas passes through a turbine of the engine and is sprayed out from a tail nozzle; the oil in the oil tank is pumped into the two-way valve through the oil pump and then pumped into a combustion chamber of the micro turbojet engine for ignition, and the ignited oil heats high-pressure gas pressurized by the compressor at the same time to form high-temperature high-pressure mixed gas and stably combust in the combustion chamber, so that the engine is quickly started and keeps high-power operation; 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 micro turbojet engine is provided with a temperature and rotating speed sensor which transmits an electronic signal to an engine electronic control system and displays the electronic signal on an engine display.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911377596.6A CN110985215A (en) | 2019-12-27 | 2019-12-27 | Starting and launching integrated system for micro turbojet engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911377596.6A CN110985215A (en) | 2019-12-27 | 2019-12-27 | Starting and launching integrated system for micro turbojet engine |
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| CN110985215A true CN110985215A (en) | 2020-04-10 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114235421A (en) * | 2021-12-06 | 2022-03-25 | 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 |
| CN114872908A (en) * | 2022-06-08 | 2022-08-09 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114954964A (en) * | 2022-06-08 | 2022-08-30 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN116374179A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Series hybrid electric propulsion system |
| 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 |
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- 2019-12-27 CN CN201911377596.6A patent/CN110985215A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN114235421A (en) * | 2021-12-06 | 2022-03-25 | 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 |
| 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 |
| CN114872908A (en) * | 2022-06-08 | 2022-08-09 | 中国航空发动机研究院 | Spray pipe device and aircraft engine |
| CN114954964A (en) * | 2022-06-08 | 2022-08-30 | 中国航空发动机研究院 | Spray pipe device and aircraft 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 |
| CN116374179A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Series hybrid electric propulsion system |
| 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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