CN109339952B - Engine starting system and airborne energy management system of helicopter - Google Patents
Engine starting system and airborne energy management system of helicopter Download PDFInfo
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- CN109339952B CN109339952B CN201811144178.8A CN201811144178A CN109339952B CN 109339952 B CN109339952 B CN 109339952B CN 201811144178 A CN201811144178 A CN 201811144178A CN 109339952 B CN109339952 B CN 109339952B
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- 239000010687 lubricating oil Substances 0.000 claims abstract description 44
- 230000005540 biological transmission Effects 0.000 claims abstract description 34
- 239000000446 fuel Substances 0.000 claims abstract description 34
- 239000000295 fuel oil Substances 0.000 claims abstract description 14
- 238000002485 combustion reaction Methods 0.000 claims description 16
- 239000007858 starting material Substances 0.000 claims description 11
- 230000007613 environmental effect Effects 0.000 claims description 8
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 7
- 238000005057 refrigeration Methods 0.000 claims description 5
- 230000017525 heat dissipation Effects 0.000 claims description 3
- 239000000314 lubricant Substances 0.000 claims 11
- 238000005086 pumping Methods 0.000 claims 1
- 230000001050 lubricating effect Effects 0.000 abstract description 6
- 239000003921 oil Substances 0.000 abstract description 4
- 238000005265 energy consumption Methods 0.000 abstract description 3
- 238000010248 power generation Methods 0.000 abstract description 2
- 238000000034 method Methods 0.000 description 5
- 230000005611 electricity Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
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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
- F02C7/06—Arrangements of bearings; Lubricating
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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
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/50—Application for auxiliary power units (APU's)
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The invention discloses an engine starting system and an airborne energy management system of a helicopter, wherein the airborne energy management system comprises an engine starting system, an oil lubricating system, a fuel system and a hydraulic system; the engine starting system comprises an engine, an electric power system, a transmission gear box and an auxiliary power device; the auxiliary power device is used for providing electric energy for electric equipment of the engine room before the engine is started, providing air pressure energy for the engine when the air temperature is lower than a set temperature, and continuously generating the electric energy and storing the electric energy to the electric power system after the engine is started; the electric power system respectively provides electric energy for the lubricating oil system, the fuel oil system and the hydraulic system. The scheme of the invention can eliminate the electric transmission part of the engine in the existing helicopter, thereby improving the energy consumption of the engine caused by power generation. And the lubricating oil system, the fuel oil system and other systems are not started by using part of mechanical energy transmitted to the engine through the accessory gearbox any more, so that the accessory gearbox can be omitted, and the weight of the helicopter is reduced.
Description
Technical Field
The invention relates to the technical field of airplane recorded energy management, in particular to an engine starting system and an airborne energy management system of a helicopter.
Background
The existing typical helicopter airborne electromechanical system is started by part of mechanical energy of an engine through a transmission gearbox, and the airborne equipment can work normally. Fig. 1 shows the operation of the power system of a typical helicopter. Reference numeral 110 is an engine, 105 is a transmission gearbox, 106 is an electric system; before the engine 110 is started, the storage battery of the power system 106 generates electric energy to start the motor through the bus bar, the electric energy is converted into mechanical energy, and the mechanical energy is transmitted to the engine shaft through electric transmission in the transmission gear box 105 to drive the engine 110 to rotate; after the engine 110 is started, a part of the mechanical energy of the engine 110 is transmitted to the power system 106 through the transmission gearbox 105, and the power system 106 converts the mechanical energy into electric energy to output for the equipment to work. However, in a high-cold and low-temperature environment, the starting motor cannot effectively start the engine, the environmental control system adopts a simple air refrigeration system, the comprehensive performance is low, and the air bleed amount from the engine is large, so that large compensation loss of the engine can be caused. The engine is used for generating power, and the engine is used for driving the accessory gearbox to drive the hydraulic pump, the lubricating oil pump, the fuel pump and the like to work, so that the mechanical energy loss of the engine is caused.
When the helicopter flies in a high and cold low-temperature environment, the work of an engine of the helicopter is limited to a certain extent, and the airborne equipment, the environmental control system, the lubricating oil system, the fuel system and the hydraulic system of the helicopter are powered by the engine, so that the mechanical energy loss of the engine is relatively large, and how to improve the energy management of the helicopter is a problem to be solved urgently in the field.
Disclosure of Invention
The invention aims to provide an engine starting system of a helicopter, which aims to solve the problems that when the existing helicopter flies in a high-cold low-temperature environment, a starting motor cannot effectively start an engine, an environment control system adopts a simple air refrigerating system, the comprehensive performance is lower, and the air bleed amount from the engine is larger, so that the larger compensation loss of the engine is caused.
The invention also aims to provide an onboard energy management system of a helicopter, which solves the problem of mechanical energy loss of an engine caused by the fact that an engine is used for generating power and an engine is used for driving an accessory gearbox to drive a hydraulic pump, a lubricating oil pump, a fuel pump and the like to work in the existing helicopter.
In order to achieve the first object, the invention provides an engine starting system of a helicopter, which comprises an engine, an electric power system, a transmission gear box and an auxiliary power device, wherein the transmission gear box and the auxiliary power device are respectively connected with the engine;
the electric power system is connected with the transmission gear box, when the air temperature is not lower than a set temperature, the electric power system provides electric energy for the transmission gear box, the transmission gear box converts the electric energy into mechanical energy, transmits the mechanical energy to the engine, and starts the engine;
the auxiliary power device is connected with the electric power system, when the air temperature is lower than a set temperature, the electric power system provides electric energy for the auxiliary power device, the auxiliary power device converts the electric energy into air pressure energy, the air pressure energy is transmitted to the engine, and the engine is started.
Optionally, the power system includes a battery, a bus bar connected to the motor in the transmission gear box, and a power line connected to the auxiliary power device.
Optionally, the auxiliary power unit comprises a starting motor, a first combustion chamber, a turbine, a compressor, an air supply system, an accessory gearbox and a generator,
the starting motor is connected with a rotor of the turbine, the turbine is connected with the air compressor, and an air pressure energy air-entraining channel of the air compressor is connected with an air turbine starter of the engine;
the starting motor converts electric energy from the electric power system into mechanical energy to drive a rotor of an engine of the auxiliary power device to rotate, when the rotating speed of the rotor of the engine of the auxiliary power device reaches a starting rotating speed, fuel oil in the first combustion chamber is combusted to drive the turbine to rotate, the mechanical energy of the turbine is transmitted to the air compressor, the air compressor converts the mechanical energy of the turbine into air pressure energy to be transmitted to an air turbine starter of the engine, and the air turbine starter of the engine converts the air pressure energy into mechanical energy for driving a core engine rotor of the engine to rotate to start the engine; and when the engine enters a stable running state after being started, the air pressure of the air compressor can close the air entraining channel.
Optionally, the starting motor converts the electric energy from the power system into mechanical energy to drive the engine rotor of the auxiliary power device to rotate, when the rotational speed of the engine rotor of the auxiliary power device reaches the starting rotational speed, the fuel oil in the first combustion chamber combusts and drives the turbine to rotate, the mechanical energy of the turbine is transmitted to the generator through a gear to generate electric energy, and the generator transmits the electric energy to the power system to store the electric energy.
To achieve the second object, the invention also provides an onboard energy management system of a helicopter, which comprises the engine starting system, the lubricating oil system, the fuel system and the hydraulic system;
the engine starting system comprises an engine, an electric power system, a transmission gear box and an auxiliary power device, wherein the transmission gear box and the auxiliary power device are respectively connected with the engine;
the electric power system is respectively connected with the lubricating oil system, the fuel oil system and the hydraulic system and respectively provides electric energy for the lubricating oil system, the fuel oil system and the hydraulic system;
the auxiliary power device comprises a starting motor, a first combustion chamber, a turbine, a gas compressor, a gas supply system, an accessory gearbox and a generator, wherein the starting motor converts electric energy from the electric power system into mechanical energy to drive a rotor of an engine of the auxiliary power device to rotate;
the auxiliary power device is used for providing electric energy for electric equipment of the engine room before the engine is started, providing air pressure energy for the engine when the air temperature is lower than a set temperature, and continuously generating the electric energy and storing the electric energy to the electric power system after the engine is started.
Optionally, the lubricating oil system determines the amount of lubricating oil required by the engine according to the temperature difference of the engine and the heat dissipation amount of the lubricating oil, the electric power system provides electric energy for a lubricating oil pump in the lubricating oil system according to the amount of lubricating oil required by the engine, the lubricating oil pump converts the electric energy into mechanical energy, and the lubricating oil flows through a bearing part of the engine and the transmission gear box in sequence, is cooled by a lubricating oil-ram air heat exchanger after absorbing heat, and then flows back to a lubricating oil tank in the lubricating oil system.
Optionally, the fuel system includes a fuel pump storing fuel and a second combustion chamber, the fuel pump is connected to the electric power system, the fuel pump operates by using electric energy provided by the electric power system, and rotates at a rotation speed corresponding to a required fuel flow determined by the electric power system according to a flight mode of the helicopter, so as to pump fuel into the second combustion chamber according to the required fuel flow.
Optionally, the hydraulic system includes a hydraulic pump, the hydraulic pump is connected to the electric power system, the hydraulic pump converts electric energy provided by the electric power system into hydraulic energy to drive the hydraulic system to operate, and the hydraulic system adjusts the helicopter control action to control the flight attitude of the helicopter.
Optionally, the system further includes an environment control system, the environment control system includes an environment control package and a water separator, after the engine is started, external ram air sequentially flows into a first-stage compressor, a second-stage compressor, a high-pressure turbine and a free turbine of the engine, so that the external ram air is compressed and expanded, a part of the compressed and expanded air flows into the environment control package after flowing through a heat exchanger, the gas in the environment control package exchanges heat with the external ram air entering the environment control package, the gas after heat exchange enters the water separator, the gas after heat exchange exchanges heat with the external ram air by passing through the water separator and a part of the ram air flowing through a lubricating oil-ram air heat exchanger, and the gas after heat exchange flows into the cabin.
Optionally, the system further includes an electronic cabin, the electric equipment in the electronic cabin is connected to the power system, and the evaporation refrigeration circulator in the electronic cabin exchanges heat between heat generated in the electronic cabin and outside ram air, and discharges the heat out of the electronic cabin.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects: the engine starting system and the airborne energy management system of the helicopter provided by the invention are both additionally provided with the Auxiliary Power Unit (APU), the APU is started by utilizing the electric energy stored by the storage battery in the power generation system in the environment with high cold and low temperature, and the engine can be started by the air pressure of the APU after the APU is started, so that the problems that the engine cannot be effectively started by a starting motor when the existing helicopter flies in the environment with high cold and low temperature, the comprehensive performance is lower because the environment control system adopts a simple air refrigeration system, and the air bleed amount from the engine is larger, so that the larger engine compensation loss can be caused are solved.
And after the engine is started, the mechanical energy generated by the APU is completely converted into electric energy through the APU whole-course generator and is transmitted to the electric power system, and the electricity is generated in the whole flight process to be required by the normal work of the airborne equipment, so that the electric transmission part of the engine in the existing helicopter can be eliminated, and the energy consumption of the engine due to the electricity generation is improved.
After the engine is started, the hydraulic system, the lubricating oil system and the fuel system are started by electric energy of the electric power system, and are not started by utilizing part of mechanical energy transmitted to the engine through the accessory gearbox, so that the accessory gearbox can be omitted, and the weight of the helicopter is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a block diagram of a prior art on-board energy management system;
fig. 2 is a block diagram of an onboard energy management system according to an embodiment of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
As shown in fig. 2, the engine starting system of the helicopter provided in the present embodiment includes an engine 215, an electric power system 207, and a transmission gearbox 209 and an auxiliary power unit 206 respectively connected to the engine 215.
The power system 207 is connected to the transmission gear box 209, and when the air temperature is not lower than the set temperature, the power system 207 provides the transmission gear box 209 with electric energy, and the transmission gear box 209 converts the electric energy into mechanical energy and transmits the mechanical energy to the engine 215 to start the engine 215. In this embodiment, the power system 207 includes a battery, a bus bar connected to the motor in the transmission gear box 209, and a power line connected to the auxiliary power unit 206.
The auxiliary power device 206 is connected to the power system 207, when the air temperature is lower than a set temperature, the power system 207 provides electric energy for the auxiliary power device 206, and the auxiliary power device 206 converts the electric energy into air pressure energy and transmits the air pressure energy to the engine 215 to start the engine 215.
Specifically, the auxiliary power unit in this embodiment includes a starter motor, a first combustion chamber, a turbine, a compressor, an air supply system, an accessory gearbox, and a generator.
The starting motor is connected with a rotor of the turbine, the turbine is connected with the air compressor, and an air pressure energy air-entraining channel of the air compressor is connected with an air turbine starter of the engine;
the starting motor converts the electric energy from the electric power system 207 into mechanical energy to drive a rotor of an engine of the auxiliary power device to rotate, when the rotating speed of the rotor of the engine of the auxiliary power device reaches a starting rotating speed, fuel oil in the first combustion chamber is combusted to drive the turbine to rotate, the mechanical energy of the turbine is transmitted to the compressor, the compressor converts the mechanical energy of the turbine into air pressure energy to be transmitted to an air turbine starter of the engine 215, and the air turbine starter of the engine 215 converts the air pressure energy into mechanical energy for driving a core machine rotor of the engine 215 to rotate to start the engine 215; when the engine 215 enters a stable operation state after being started, the air pressure of the air compressor can close the air-entraining channel.
The starting motor converts the electric energy from the electric power system 207 into mechanical energy to drive an engine rotor of the auxiliary power device to rotate, when the rotating speed of the engine rotor of the auxiliary power device reaches a starting rotating speed, fuel oil in the first combustion chamber is combusted to drive the turbine to rotate, the mechanical energy of the turbine is transmitted to the generator through a gear to generate electric energy, and the generator transmits the electric energy to the electric power system 207 to store the electric energy.
In the environment of high and cold low temperature, because the system is additionally provided with the APU206, before the engine 215 of the helicopter is started, the APU206 is started by a storage battery in the power system 207, after the APU206 is started, a bleed air channel of the APU206 is opened, the outside ram air 204 flows into the APU206, and the engine 215 can be started by the air pressure of the APU 206; after the engine 215 is started, the bleed air channel of the APU206 is closed, and the mechanical energy generated by its normal operation is fully converted into electrical energy by the APU206 generator and stored in the power system 207.
The onboard energy management system of the helicopter provided by the embodiment comprises the engine starting system, the lubricating oil system, the fuel system and the hydraulic system. I.e. comprising an engine 215, an electric power system 207, a transmission gearbox 209 and an auxiliary power unit 206 connected to said engine 215, respectively, and a lubricating oil system 216, a fuel oil system 217 and a hydraulic system 218.
The onboard energy management system adopts the APU206 to generate power in the whole process, and provides energy for an onboard electromechanical system of the helicopter. The electrical system 207 transfers electrical energy to the on-board equipment, hydraulic system 218, oil system 216, and fuel system 217 for proper operation. By adopting the scheme, the energy consumption compensation problem of the helicopter can be effectively improved, the energy compensation of the engine 215 for generating power and supplying power to the lubricating oil system 216, the fuel oil system 217 and the hydraulic system 218 is reduced, the energy conversion efficiency of the engine is improved, the utilization rate of the APU206 is improved, the APU206 is additionally arranged, and an electric transmission gear and an accessory gear box are simultaneously cancelled, so that the weight of the helicopter is reduced.
The APU206 is added, and the APU generates electricity in the whole process to respectively provide energy for the lubricating oil system 216, the fuel oil system 217, the hydraulic system 218 and the on-board equipment, and the energy supply pipeline process is as follows:
after the engine 215 is started, the bleed air channel of the APU206 is closed, and the mechanical energy generated by normal operation is converted into electric energy by the APU206 generator, so that the electric energy is required for normal operation of the oil system 216, the fuel system 217, the hydraulic system 218, the on-board equipment and the like.
(1) Ring control part
After the engine 215 is started, the external ram air 204 sequentially flows into the primary compressor 211, the secondary compressor 212, the high-pressure turbine 213 and the free turbine 214 of the engine 215, so that the external ram air 204 is compressed and expanded, a part of the compressed and expanded gas flows into the environmental control package 202 after flowing through the heat exchanger 201, the gas exchanges heat with the external ram air 204 entering the environmental control package 202 in the environmental control package 202, the heat-exchanged gas enters the water separator 203, the gas passing through the water separator 203 exchanges heat with a part of the ram air flowing through the lubricating oil-ram air heat exchanger 208 and flows into the cabin 205.
(2) Lubricating oil system
After the engine 215 is started, the lubricating oil system 216 determines the amount of lubricating oil required by the engine 215 according to the temperature difference of the engine 215 and the heat dissipation amount of the lubricating oil, the electric power system 207 provides electric energy for a lubricating oil pump in the lubricating oil system 216 according to the amount of lubricating oil required by the engine 215, the lubricating oil pump converts the electric energy into mechanical energy, the lubricating oil sequentially flows through the bearing part of the engine 215 and the transmission gear box 209, and the lubricating oil flows back to a lubricating oil tank in the lubricating oil system 216 after being cooled by the lubricating oil-ram air heat exchanger 208 after absorbing heat. The mechanical energy of the APU206 is completely converted into electric energy by the generator of the APU206 and transmitted to the power system 207; the lubricating oil system 216 operates the lubricating oil pump by the electric energy in the electric system 207 and converts the lubricating oil into mechanical energy, and the lubricating oil flows through the engine bearing part and the transmission gear box 209 in sequence under the driving of the lubricating oil pump, absorbs heat, is cooled by the lubricating oil-ram air heat exchanger 208, and then flows back to the lubricating oil system 216.
(3) Fuel system
After the engine 215 is started, the fuel pump in the fuel system 217 operates by using the electric energy provided by the electric power system 207, and pumps fuel into the second combustion chamber according to the required fuel flow rate to supply power to the helicopter by rotating at a rotation speed corresponding to the required fuel flow rate determined by the electric power system 207 according to the flight mode of the helicopter.
(4) Hydraulic system
After the engine 215 is started, the mechanical energy of the APU206 is completely converted into electric energy by the APU206 generator and transmitted to the power system 207; the mechanical energy generated by the APU206 is converted into electrical energy by the power system 207 and transferred to the hydraulic pump, which converts the electrical energy into hydraulic energy to drive the hydraulic system 218 to operate and supply power to the helicopter. The hydraulic system realizes the adjustment of the operation action of the helicopter so as to control the flight attitude of the helicopter.
(5) Electric power system
Before the engine 215 is started, the storage battery in the power system 207 firstly enables the APU206 to run through electric energy, the outside ram air 204 enters the APU206, and the air pressure of the APU206 can be transmitted to the engine 215 to enable the engine 215 to work; after the engine 215 is started, the bleed air channel of the APU206 is closed, and the mechanical energy generated by the APU206 is converted into electric energy by the generator of the APU206 and transmitted to the electric power system 207 for the operation of the electric power system 207, so as to provide electric energy for the oil system 216, the fuel system 217, the hydraulic system 218 and the on-board equipment, and enable the on-board equipment to work normally.
(6) Electronic cabin
The electric equipment in the electronic compartment 219 is connected to the power system 207, and the evaporative refrigeration cycle in the electronic compartment 219 exchanges heat between the heat generated in the electronic compartment 219 and the outside ram air 204, and discharges the heat out of the electronic compartment 219.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (9)
1. An engine starting system for a helicopter, said system comprising an engine, an electrical system, and a transmission gearbox and an auxiliary power unit connected to said engine, respectively;
the electric power system is connected with the transmission gear box, when the air temperature is not lower than a set temperature, the electric power system provides electric energy for the transmission gear box, the transmission gear box converts the electric energy into mechanical energy, transmits the mechanical energy to the engine, and starts the engine;
the auxiliary power device is connected with the electric power system, when the air temperature is lower than a set temperature, the electric power system provides electric energy for the auxiliary power device, the auxiliary power device converts the electric energy into air pressure energy, the air pressure energy is transmitted to the engine, and the engine is started;
the auxiliary power device comprises a starting motor, a first combustion chamber, a turbine, a gas compressor, a gas supply system, an accessory gearbox and a generator,
the starting motor is connected with a rotor of the turbine, the turbine is connected with the air compressor, and an air pressure energy air-entraining channel of the air compressor is connected with an air turbine starter of the engine; the starting motor converts electric energy from the electric power system into mechanical energy to drive a rotor of an engine of the auxiliary power device to rotate, when the rotating speed of the rotor of the engine of the auxiliary power device reaches a starting rotating speed, fuel oil in the first combustion chamber is combusted to drive the turbine to rotate, the mechanical energy of the turbine is transmitted to the air compressor, the air compressor converts the mechanical energy of the turbine into air pressure energy to be transmitted to an air turbine starter of the engine, and the air turbine starter of the engine converts the air pressure energy into mechanical energy for driving a core engine rotor of the engine to rotate to start the engine; and when the engine enters a stable running state after being started, the air pressure of the air compressor can close the air entraining channel.
2. An engine starting system for a helicopter as set forth in claim 1 wherein said electrical system includes a battery, a bus bar connected to said motor in said transmission gearbox, and a power line connected to said auxiliary power unit.
3. An engine starting system for a helicopter as set forth in claim 1 wherein said starter motor converts electrical energy from said electrical power system to mechanical energy to rotate the engine rotor of said auxiliary power unit, the rotation of the engine rotor of said auxiliary power unit reaching a start-up speed causes fuel in said first combustion chamber to combust and rotate said turbine, the mechanical energy of said turbine is transmitted through a gear to said generator to generate electrical energy, and said generator transmits said electrical energy to said electrical power system to store said electrical energy.
4. An on-board energy management system for a helicopter, said system comprising an engine starting system, a lubricating oil system, a fuel system and a hydraulic system according to any one of claims 1 to 3;
the engine starting system comprises an engine, an electric power system, a transmission gear box and an auxiliary power device, wherein the transmission gear box and the auxiliary power device are respectively connected with the engine;
the electric power system is respectively connected with the lubricating oil system, the fuel oil system and the hydraulic system and respectively provides electric energy for the lubricating oil system, the fuel oil system and the hydraulic system;
the auxiliary power device comprises a starting motor, a first combustion chamber, a turbine, a gas compressor, a gas supply system, an accessory gearbox and a generator, wherein the starting motor converts electric energy from the electric power system into mechanical energy to drive a rotor of an engine of the auxiliary power device to rotate;
the auxiliary power device is used for providing electric energy for electric equipment of the engine room before the engine is started, providing air pressure energy for the engine when the air temperature is lower than a set temperature, and continuously generating the electric energy and storing the electric energy to the electric power system after the engine is started.
5. The system of claim 4, wherein the lubricant system determines a required amount of lubricant for the engine based on a temperature difference between the engine and a heat dissipation amount of the lubricant, the power system provides electrical energy to a lubricant pump in the lubricant system based on the required amount of lubricant for the engine, the lubricant pump converts the electrical energy to mechanical energy, and causes the lubricant to flow through the bearing portion of the engine and the transmission gearbox in sequence, and after absorbing heat, the lubricant is cooled by the lubricant-ram air heat exchanger and then flows back to a lubricant tank in the lubricant system.
6. An on-board energy management system for a helicopter as set forth in claim 4 wherein said fuel system includes a fuel pump containing stored fuel and a second combustion chamber, said fuel pump being connected to said electrical system, said fuel pump being operable by electrical energy provided by said electrical system and pumping fuel into said second combustion chamber at a desired fuel flow rate as said electrical system rotates at a rotational speed corresponding to said desired fuel flow rate as determined by the manner in which said helicopter is flying.
7. An on-board energy management system for a helicopter as claimed in claim 4, wherein said hydraulic system includes a hydraulic pump connected to said electrical system, said hydraulic pump converting electrical energy provided by said electrical system into hydraulic energy to drive said hydraulic system to operate, said hydraulic system effecting modulation of maneuvering of said helicopter to control attitude of said helicopter.
8. The system of claim 4, further comprising an environmental control system that includes an environmental control package and a water separator, wherein when the engine is started, the ram air from the outside flows sequentially into the first compressor, the second compressor, the high pressure turbine and the free turbine of the engine, so that the ram air from the outside is compressed and expanded, a portion of the compressed and expanded ram air flows into the environmental control package through a heat exchanger, the ram air from the environment control package exchanges heat with the ram air from the outside, the ram air from the water separator exchanges heat with the ram air from the outside, and the ram air from the oil-ram air heat exchanger flows into the cabin after the heat exchange.
9. An on-board energy management system for a helicopter as set forth in claim 4 and further comprising an electronics bay, electrical equipment within said electronics bay being connected to said electrical power system, an evaporative refrigeration cycle within said electronics bay exchanging heat generated within said electronics bay for ambient ram air and removing heat from said electronics bay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811144178.8A CN109339952B (en) | 2018-09-29 | 2018-09-29 | Engine starting system and airborne energy management system of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811144178.8A CN109339952B (en) | 2018-09-29 | 2018-09-29 | Engine starting system and airborne energy management system of helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109339952A CN109339952A (en) | 2019-02-15 |
| CN109339952B true CN109339952B (en) | 2020-01-21 |
Family
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| CN111268140B (en) * | 2020-02-10 | 2021-06-01 | 南京航空航天大学 | Green environmental control system of aircraft |
| CN112228221B (en) * | 2020-09-11 | 2023-03-24 | 中国航空工业集团公司成都飞机设计研究所 | Auxiliary power generation system driven by stamping turbine and use method |
| CN112537453B (en) * | 2020-11-06 | 2022-04-22 | 南京航空航天大学 | Energy comprehensive management system for hybrid electric propulsion aircraft |
| CN112623233B (en) * | 2020-12-24 | 2022-09-06 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Self-adaptive power and heat management system for airplane |
| CN113323757B (en) * | 2021-06-01 | 2022-12-20 | 北京清软创想信息技术有限责任公司 | Disconnect-type atmospheric pressure type auxiliary power air piping system |
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| CN103097696A (en) * | 2010-08-25 | 2013-05-08 | 涡轮梅坎公司 | Method for optimizing the control of a free turbine power package for an aircraft, and control for implementing same |
| CN103154472A (en) * | 2010-08-25 | 2013-06-12 | 涡轮梅坎公司 | Method for optimizing the operability of an aircraft propulsive unit, and self-contained power unit for implementing same |
| CN104379450A (en) * | 2012-06-15 | 2015-02-25 | 涡轮梅坎公司 | Method and architecture for the optimized transfer of power between an auxiliary power motor and the main engines of a helicopter |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103097696A (en) * | 2010-08-25 | 2013-05-08 | 涡轮梅坎公司 | Method for optimizing the control of a free turbine power package for an aircraft, and control for implementing same |
| CN103154472A (en) * | 2010-08-25 | 2013-06-12 | 涡轮梅坎公司 | Method for optimizing the operability of an aircraft propulsive unit, and self-contained power unit for implementing same |
| CN104379450A (en) * | 2012-06-15 | 2015-02-25 | 涡轮梅坎公司 | Method and architecture for the optimized transfer of power between an auxiliary power motor and the main engines of a helicopter |
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