CN116986000A - Electric auxiliary emergency helicopter power system and transmission method - Google Patents

Electric auxiliary emergency helicopter power system and transmission method Download PDF

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Publication number
CN116986000A
CN116986000A CN202310770465.4A CN202310770465A CN116986000A CN 116986000 A CN116986000 A CN 116986000A CN 202310770465 A CN202310770465 A CN 202310770465A CN 116986000 A CN116986000 A CN 116986000A
Authority
CN
China
Prior art keywords
power
helicopter
auxiliary
turboshaft engine
emergency
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202310770465.4A
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Chinese (zh)
Inventor
阮华波
郭青林
苏志敏
王旭
成本林
李维
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hunan Aviation Powerplant Research Institute AECC
Original Assignee
Hunan Aviation Powerplant Research Institute AECC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hunan Aviation Powerplant Research Institute AECC filed Critical Hunan Aviation Powerplant Research Institute AECC
Priority to CN202310770465.4A priority Critical patent/CN116986000A/en
Publication of CN116986000A publication Critical patent/CN116986000A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • 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
    • 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
    • B64D2041/002—Mounting arrangements for auxiliary power units (APU's)

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

The invention relates to an auxiliary emergency helicopter power system and a transmission method. The helicopter power system comprises a turboshaft engine unit, the turboshaft engine unit comprises a plurality of turboshaft engines, the turboshaft engines comprise a turboshaft engine body and an electric starter rotationally connected with the turboshaft engine body, and the turboshaft engine body is rotationally connected with a transmission system and further comprises an auxiliary motor and an onboard power unit. The invention can meet the requirements of emergency power, starting power and helicopter power by arranging the onboard power unit, and simultaneously can reduce the weight and design complexity of the turboshaft engine and the transmission system; the vortex shaft engine and the onboard power unit form a fuel-electric hybrid propulsion system, so that the fuel utilization rate can be effectively improved, and the range of the helicopter is further improved.

Description

Electric auxiliary emergency helicopter power system and transmission method
Technical Field
The invention belongs to the technical field of helicopter engines, and particularly relates to an electric auxiliary emergency helicopter power system and a transmission method.
Background
At present, a helicopter power system mainly comprises a turboshaft engine and a transmission system, so that the helicopter has unique performances of vertical take-off and landing, hovering, high maneuverability and the like, and is widely applied to military fields such as investigation, attack, transportation and the like, and civil fields such as rescue and relief work, geological exploration, oil field development and the like. The vortex shaft engine is mainly used as a power device of the helicopter and mainly outputs power; the transmission system transmits power generated by the turboshaft engine to the rotor and tail rotor.
In addition to the light helicopter, the general helicopter is provided with 2 or more vortex shaft engines as power, and the power output shaft of the vortex shaft engines is connected with a helicopter transmission system through a coupler, so that the transmission system has a speed reduction transmission effect because the power output shaft of the vortex shaft engines is usually higher in rotating speed and the rotating speed of a helicopter rotor is lower.
The reliability of a helicopter in a double-shot configuration is higher than that of a helicopter in a single-shot configuration because the probability of failure of all 2 engines is lower. When a double-engine helicopter fails to stop in a single-engine mode, another engine which works normally can increase power output under normal conditions so as to meet the requirement of the helicopter for returning to the landing, which is called an emergency state, wherein the power of the engine in the emergency state is 5% higher than the maximum continuous power, but the emergency state of the engine is limited in time at most, and the power of the engine in the emergency state is 30 minutes at most. And the existing power system has the following problems:
(1) In order to meet the requirements of safety and navigability, most turboshaft engines and transmission systems generally need to be designed into an emergency state, and when one engine fails, the power required by the helicopter to fly is switched from the rest of the engines to the emergency state. The emergency situation causes an increased difficulty in designing the engine and the transmission system and an increased weight.
(2) When the load capacity of a helicopter of a traditional power system is small (such as air-vehicle return, etc.), the required engine power is far lower than the engine design power, so that the working state of the engine is low and the fuel utilization rate is low.
(3) The general traditional turboshaft engine is provided with a starting generator, and a special power supply is needed to start the engine through the starting generator; when the engine runs, the engine core engine power is extracted by starting the generator to provide power for the helicopter, namely the motor can be used as a starter and also can be used as a generator. Therefore, the motor needs to be connected with a gas generator rotor of the turboshaft engine to achieve the purpose, when the motor is used as a generator, an engine working point can be caused to move towards a surge boundary, the surge margin of the engine is reduced, and the surge is more likely to occur.
Based on the above, the invention provides a helicopter power system for assisting emergency and a transmission method.
Disclosure of Invention
Aiming at the problems, the invention provides an auxiliary emergency helicopter power system and a transmission method.
The first object of the present invention can be achieved by the following technical scheme:
the utility model provides an auxiliary emergency's helicopter power system, includes the turboshaft engine unit, the turboshaft engine unit includes a plurality of turboshaft engines, the turboshaft engine includes the turboshaft engine body and with the electric starter of turboshaft engine body swivelling joint, the turboshaft engine body still swivelling joint has transmission system, still includes auxiliary motor and airborne power unit;
the auxiliary motor is rotationally connected with the transmission system;
the onboard power unit is electrically connected with the electric starter;
the auxiliary motor is electrically connected with the on-board power unit.
Further, the number of turboshaft engines in the turboshaft engine block is at least 2.
Further, electric energy is bidirectionally transmitted between the auxiliary motor and the onboard power unit.
Further, the turboshaft engine body includes a housing, a power turbine rotor, and a gas generator rotor;
the power turbine rotor is fixedly connected with a power output shaft;
the gas generator rotor is fixedly connected with an auxiliary rotating shaft;
the power output shaft and the auxiliary rotating shaft are respectively and rotatably connected with the shell.
Further, the output end of the electric starter is rotatably connected with the auxiliary rotating shaft.
Further, the power output shaft is rotatably connected with the transmission system.
The second object of the present invention can be achieved by the following technical scheme:
a transmission method of a helicopter power system for assisting an emergency, comprising:
the onboard power unit provides electric energy for an electric starter, and the electric starter rotates to start the turboshaft engine body;
the scroll engine body drives a transmission system.
The transmission method of the auxiliary emergency helicopter power system further comprises the following steps:
the turboshaft engine body drives a transmission system, and the transmission system drives an auxiliary motor.
The transmission method of the auxiliary emergency helicopter power system further comprises the following steps:
the onboard power unit electrically drives an auxiliary motor, which drives a transmission system.
According to the transmission method of the auxiliary emergency helicopter power system, the onboard power unit provides power for the helicopter flight control system and the environmental control system.
The invention has the beneficial effects that:
according to the auxiliary emergency helicopter power system and the transmission method, the emergency power requirement, the starting power requirement and the helicopter power requirement can be met through the arrangement of the onboard power unit, and meanwhile, the weight and the design complexity of the turboshaft engine and the transmission system can be reduced;
the vortex shaft engine and the onboard power unit form a fuel-electricity hybrid propulsion system, so that the fuel utilization rate can be effectively improved, and the range of the helicopter is further improved;
through the combination setting of the onboard power unit, the auxiliary motor and the turboshaft engine, various transmission methods (paths) are realized, and the following purposes are achieved:
when the turboshaft engine is started, the electric starter is driven by the energy supply of the onboard power unit, so that the turboshaft engine is started;
when the turboshaft engine runs, the airborne power unit supplies power for a helicopter ring control system and the like, so that the electric power extracted from a core engine of the turboshaft engine is reduced, the surge margin of the engine can be effectively improved, and the safety is further improved;
when the helicopter is in an emergency state, the onboard power unit electrically drives the auxiliary motor, and the auxiliary motor drives the transmission system to provide power for the helicopter rotor wing, so that the power requirement of the emergency state is met, the turboshaft engine and the transmission system do not need to be in an emergency state, and the service lives of the turboshaft engine and the transmission system are prolonged;
when the helicopter works in a smaller power range, the turboshaft engine body drives a transmission system, the transmission system drives an auxiliary motor, the auxiliary motor charges an onboard power unit, the engine load is effectively improved, the working state of the turboshaft engine is improved, and therefore the turboshaft engine works in a high-efficiency area, and the fuel utilization rate is improved;
when the helicopter works in a high power range, the onboard power unit supplies energy to drive the electric starter to bear the working power of the turboshaft engine, and at the moment, the onboard power unit plays a role in regulating the system power, so that the turboshaft engine can work in a high-efficiency area for a long time, and the problem of low fuel utilization efficiency when the turboshaft engine runs in a low state is solved.
The onboard power unit can be charged when the load of the turboshaft engine is small, and also can be charged in the off-line state of the helicopter, so that the carbon emission is effectively reduced;
the auxiliary emergency helicopter power system can be applied to double-engine and above multiple helicopters, and has a wide application range.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 illustrates a frame construction of a helicopter power system for auxiliary emergency according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a helicopter power system for assisting in emergency according to an embodiment of the invention;
FIG. 3 shows a schematic diagram of a turboshaft engine in accordance with an embodiment of the present invention;
in the figure:
10. a scroll engine body; 11. a gas generator rotor; 12. a housing; 13. a power turbine rotor; 14. a power output shaft; 15. a secondary rotation shaft; 20. an electric starter; 30. an onboard power unit; 40. an auxiliary motor; 50. a transmission system; 60. helicopter rotor.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1, an auxiliary emergency helicopter power system according to an embodiment of the invention comprises a turboshaft engine unit, a transmission system 50, an auxiliary motor 40 and an on-board power unit 30;
the transmission system 50 is fixedly connected with the helicopter rotor 60, and the transmission system 50 comprises a plurality of gears and a plurality of gear shafts, has a deceleration effect and drives the helicopter rotor 60 again;
as shown in fig. 2, the turboshaft engine unit comprises a plurality of turboshaft engines, the turboshaft engines comprise a turboshaft engine body 10 and an electric starter 20, the electric starter 20 is rotatably connected with the turboshaft engine body 10, and the electric starter 20 is used for starting the turboshaft engine body 10;
the vortex shaft engine body 10 is rotationally connected with the transmission system 50, and the vortex shaft engine body 10 and the transmission system 50 can be mutually driven;
the auxiliary motor 40 is rotatably connected with the transmission system 50, and the auxiliary motor 40 and the transmission system 50 can be mutually driven;
the on-board power unit 30 is electrically connected to the electric starter 20, and the on-board power unit 30 supplies power to the electric starter 20, as indicated by an arrow (the arrow indicates a power transmission direction) in fig. 1;
the auxiliary motor 40 is electrically connected to the on-board power unit 30, and the auxiliary motor 40 and the on-board power unit 30 bidirectionally transmit electric power therebetween, as indicated by an arrow (the arrow indicates a power transmission direction) in fig. 1.
In this embodiment, the number of turboshaft engines in the turboshaft engine unit is 2; the number of the vortex shaft engines in the vortex shaft engine unit can be any number of more than 2, such as 3, 4, 5, 6 and … …, and the number of the vortex shaft engines in the vortex shaft engine unit can be designed in a variable mode according to helicopter design power.
In the present embodiment, as shown in fig. 3, the scroll engine body 10 includes a housing 12, a power turbine rotor 13, and a gas generator rotor 11;
the power turbine rotor 13 is fixedly connected with a power output shaft 14, and the power output shaft 14 is rotationally connected with the transmission system 50
The gas generator rotor 11 is fixedly connected with an auxiliary rotating shaft 15;
the power output shaft 14 and the auxiliary rotating shaft 15 are respectively connected with the shell 12 in a rotating way;
the output end of the electric starter 20 is rotationally connected with the auxiliary rotating shaft 15, when the electric starter 20 obtains electric energy, the output end of the electric starter 20 rotates to drive the auxiliary rotating shaft 15 to rotate, so that the gas generator rotor 11 rotates to realize the starting of the turboshaft engine body 10;
the gas generator rotor 11 sends rotation and drives the auxiliary rotating shaft 15 to rotate again, the turboshaft engine body 10 comprises a shell 12 to generate air flow, the power turbine rotor 13 is driven to rotate, the power output shaft 14 is driven to rotate, the transmission system 50 is finally driven, the helicopter rotor 60 is further driven to rotate, and the operation of the turboshaft engine is achieved.
In some embodiments of the present invention, a transmission method of a helicopter power system for assisting an emergency is provided, including:
when the turboshaft engine is started, the onboard power unit 30 provides electric energy for the electric starter 20, and an output shaft of the electric starter 20 rotates, so that the auxiliary rotating shaft 15 is driven to rotate to start the turboshaft engine body 10;
the vortex shaft engine body 10 drives the transmission system 50 through the power output shaft 14, so that the rotation of the helicopter rotor 60 is realized, and the take-off of the helicopter is realized.
The transmission method of the auxiliary emergency helicopter power system further comprises the following steps:
when the helicopter works in a smaller power range (less than 50% of takeoff power state), the turboshaft engine body 10 drives the transmission system 50, the transmission system 50 drives the auxiliary motor 40, the auxiliary motor 40 charges the airborne power unit 30, the engine load is effectively improved, the working state of the turboshaft engine is improved, and therefore the turboshaft engine works in a high-efficiency area, and the fuel utilization rate is improved.
The transmission method of the auxiliary emergency helicopter power system further comprises the following steps:
when one turboshaft engine fails, the onboard power unit 30 electrically drives the auxiliary motor 40, and the auxiliary motor 40 drives the transmission system 50 to provide power for the helicopter rotor 60, so as to meet the power requirement in an emergency state.
The transmission method of the auxiliary emergency helicopter power system further comprises the following steps:
when the engine is operated in the high power range, the auxiliary motor 40 provides power for the on-board power unit 30, drives the electric starter 20, drives the turboshaft engine body 10 to rotate, and bears part of the working power of the turboshaft engine.
In the embodiment of the present invention, the on-board power unit 30 provides a power backup for the turboshaft engine control system and provides power for the helicopter flight control system and the environmental control system;
the on-board power unit 30 includes a battery and an energy control module, which are common knowledge to those skilled in the art, and the description of the present embodiment is omitted herein;
the size of the airborne power unit 30 can be adjusted according to the emergency power demand, and the application range is wide.
Although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims (10)

1. The utility model provides an auxiliary emergency's helicopter power system, includes the turboshaft engine unit, the turboshaft engine unit includes a plurality of turboshaft engines, the turboshaft engine includes turboshaft engine body (10) and with electrical starter (20) of turboshaft engine body (10) swivelling joint, turboshaft engine body (10) still swivelling joint has transmission system (50), characterized by still includes auxiliary motor (40) and airborne power unit (30);
the auxiliary motor (40) is rotationally connected with the transmission system (50);
the on-board power unit (30) is electrically connected with the electric starter (20);
the auxiliary motor (40) is electrically connected with the on-board power unit (30).
2. The auxiliary emergency helicopter power system of claim 1 wherein the number of turboshaft engines in said turboshaft engine block is at least 2.
3. An auxiliary emergency helicopter power system according to claim 1, characterized in that said auxiliary motor (40) and said on-board power unit (30) are bi-directionally powered.
4. -an auxiliary emergency helicopter power system according to any of claims 1-3, characterized in that said turboshaft engine block (10) comprises a housing (12), a power turbine rotor (13) and a gas generator rotor (11);
the power turbine rotor (13) is fixedly connected with a power output shaft (14);
the gas generator rotor (11) is fixedly connected with an auxiliary rotating shaft (15);
the power output shaft (14) and the auxiliary rotating shaft (15) are respectively connected with the shell (12) in a rotating way.
5. The auxiliary emergency helicopter power system according to claim 4, wherein the output of said electric starter (20) is in rotational connection with said secondary rotating shaft (15).
6. The auxiliary emergency helicopter power system according to claim 4, wherein said power take-off shaft (14) is rotatably connected to said transmission system (50).
7. A method of transmission of an auxiliary emergency helicopter power system, the auxiliary emergency helicopter power system comprising the auxiliary emergency helicopter power system of claims 1-6, comprising:
the on-board power unit (30) provides electric energy for an electric starter (20), and the electric starter (20) rotates to start the turboshaft engine body (10);
the scroll engine body (10) drives a drive train (50).
8. The method of transmission of a helicopter power system for assisting an emergency according to claim 7, further comprising:
the turboshaft engine body (10) drives a transmission system (50), and the transmission system (50) drives an auxiliary motor (40).
9. The method of transmission of a helicopter power system for assisting an emergency according to claim 7, further comprising:
the on-board power unit (30) electrically drives an auxiliary motor (40), the auxiliary motor (40) driving a transmission system (50).
10. A transmission method of an auxiliary emergency helicopter power system according to any of claims 7-9, characterized in that said on-board power unit (30) provides power to helicopter flight control systems and loop control systems.
CN202310770465.4A 2023-06-27 2023-06-27 Electric auxiliary emergency helicopter power system and transmission method Pending CN116986000A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310770465.4A CN116986000A (en) 2023-06-27 2023-06-27 Electric auxiliary emergency helicopter power system and transmission method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310770465.4A CN116986000A (en) 2023-06-27 2023-06-27 Electric auxiliary emergency helicopter power system and transmission method

Publications (1)

Publication Number Publication Date
CN116986000A true CN116986000A (en) 2023-11-03

Family

ID=88527460

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310770465.4A Pending CN116986000A (en) 2023-06-27 2023-06-27 Electric auxiliary emergency helicopter power system and transmission method

Country Status (1)

Country Link
CN (1) CN116986000A (en)

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