CN117208212A - Rotorcraft hybrid power system based on working medium driving - Google Patents

Abstract

The invention belongs to a rotorcraft hybrid power system based on working medium driving, which comprises a turbine engine and a rotor device, wherein the rotor devices are symmetrically arranged around a rotorcraft body in pairs, the rotorcraft hybrid power system comprises a rotor and an inner casing, the rotor is arranged at one end of the inner casing, a turbine is arranged in a cavity at the other end of the inner casing, a turbine shaft of the turbine is arranged on a support in the inner casing through a bearing, the end part of the turbine shaft is connected with the rotor through a speed reducer, a volute matched with the turbine is arranged in the cavity of the inner casing, and an inner jet pipe is further communicated with one end of an air inlet of the volute; the turbine engine guides high-temperature and high-pressure working medium into the volute of the rotor wing device through the working medium generating device and the working medium transmission pipe, and the volute is used for gathering high-pressure hot gas to drive the turbine shaft to rotate. The invention adopts a system for driving the rotor wing by high-temperature high-pressure working medium, and gives consideration to the improvement of the endurance time and stability of the vertical take-off and landing aircraft.

Description

Rotorcraft hybrid power system based on working medium driving

Technical Field

The invention relates to an aviation power system, in particular to a working medium driven vertical take-off and landing power system.

Background

With the progress of aviation industry technology, vertical take-off and landing aircrafts are correspondingly developed in the military and civil fields, but the problems of short endurance time, small maximum load and the like still restrict the wider application of the vertical take-off and landing aircrafts. The above problems can be effectively ameliorated by improving the power of a vertical takeoff and landing aircraft.

With the progress of aviation industry technology, multi-rotor unmanned aerial vehicle has been developed correspondingly in military and civil fields, but the problems of short endurance time, small maximum load and the like still restrict the wider application of vertical take-off and landing aircraft.

At present, a multi-rotor unmanned aerial vehicle mostly adopts a battery-motor system as power. Because the energy density of the battery is low, and the power density of the motor and the control and regulation system thereof is relatively insufficient, the weight proportion of the motor and the battery in the total weight of the aircraft is high, and the load weight and the flight time of the aircraft are limited, so that the multi-rotor aircraft is difficult to meet the increasing dead time and load demands.

The vertical take-off and landing power system based on electric drive is short in endurance time due to the lack of high-density energy storage equipment, and the development difficulty of the high-density energy storage equipment is high; the vertical take-off and landing aircraft based on the fuel oil driven vertical take-off and landing power system has long endurance time, and the power system has poor long-time working stability and speed regulation accuracy.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provide a rotor wing driving system adopting a high-temperature high-pressure working medium, which is a rotor wing hybrid power system based on working medium driving and is provided for improving the endurance time and stability of a vertical take-off and landing aircraft.

In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: a rotorcraft hybrid power system based on working medium driving comprises a turbine engine and a rotor device, wherein the rotor device is arranged around a rotor body in a pairwise symmetrical manner by taking the axis of the rotor body as the center, and at least two pairs are arranged;

the rotor wing device comprises a rotor wing and an inner casing, wherein the rotor wing is arranged at one end of the inner casing, a turbine is arranged in a cavity at the other end of the inner casing, a turbine shaft of the turbine is arranged on a support in the inner casing through a bearing, the end part of the turbine shaft is connected with the rotor wing through a speed reducer, a volute matched with the turbine is arranged in the cavity of the inner casing, and an inner culvert spray pipe is further communicated with one end of an air inlet of the volute; the turbine shaft and the inner casing are coaxially arranged;

the turbine engine guides high-temperature and high-pressure working medium into the volute of the rotor wing device through the working medium generating device and the working medium transmission pipe, the volute is used for collecting high-pressure hot gas to drive the turbine shaft to rotate, so that the rotor wing rotates, and power is provided for the rotorcraft.

Further, the device also comprises a motor which is coaxially arranged with the turbine shaft, one end of a motor shaft of the motor is fixed on the bracket through a bearing, and the other end of the motor is connected with the turbine shaft; the rotary wing aircraft is also provided with a storage battery, the motor is electrically connected with the storage battery through a wire, and the storage battery is used for driving the turbine to rotate and accelerate to start when the turbine is at a low speed; and when the turbine is at high speed, the turbine drives the motor to generate electricity and the electricity is stored in the storage battery through a lead.

Further, the working medium generating device comprises a gas collecting device and a heat returning device, a gas compressor and a diffuser are coaxially arranged in the casing at the cold air inlet of the turbine engine in sequence along the cold air direction, and the gas collecting device is arranged in the casing at the cold air outlet of the diffuser; a centripetal turbine and a rectifying cone are sequentially arranged in a casing at a high-pressure hot gas outlet of a combustion chamber of the turbine engine along the hot gas direction, and a heat returning device is communicated with a tail nozzle at the hot gas outlet direction of the rectifying cone; the gas collecting device is used for collecting part of cold gas entering the turbine engine and guiding the cold gas to a cold gas inlet of the heat regenerating device, and the heat regenerating device is used for exchanging heat between the cold gas entering the heat regenerating device and high-pressure hot gas in the tail nozzle and transmitting the exchanged hot gas to the generator through the working medium transmission pipe;

one end of the working medium transmission pipe is communicated with the hot gas outlet of the heat regeneration device, and the other end of the working medium transmission pipe is communicated with the turbine volute device.

Further, the gas collecting device comprises a gas collecting ring which is provided with an annular cavity and is U-shaped in section, at least four gas guide pipes are uniformly communicated on the same annular surface of the gas collecting ring, regulating valves are arranged on the gas guide pipes, and the gas collecting ring is communicated with a cold air inlet of the heat regenerating device through the gas guide pipes;

the U-shaped opening of the gas collecting ring is positioned on the inner ring surface of the gas collecting ring, the gas collecting ring is fixedly connected and communicated with the casing through two side walls at the U-shaped opening, so that the gas collecting ring and the casing jointly form an outer ring channel of the outlet air flow of the gas compressor, the outlet air flow channel of the gas compressor is an inner ring channel, cold air flowing in from the outer ring channel enters the heat recovery device through the gas collecting ring and the air guide pipe, and cold air flowing in from the inner ring channel enters the cold air input end of the combustion chamber.

Further, the heat regenerating device comprises an annular air inlet pipe and an annular air outlet pipe, and a plurality of inlet air collecting transverse pipes are arranged on the same annular surface of the annular air inlet pipe in a circumferential direction; a plurality of outlet gas collecting transverse pipes are arranged on the same annular surface of the annular gas outlet pipe in the circumferential direction; the inlet gas-collecting horizontal pipe is communicated with the outlet gas-collecting horizontal pipe through a heat exchange pipe row;

the gas collecting device is communicated with the annular gas inlet pipe through a gas guide pipe, the collected cold gas is led into the annular gas inlet pipe by the gas collecting device, so that the cold gas sequentially enters the inlet gas collecting transverse pipe and the heat exchange pipe row, the cold gas in the heat exchange pipe row exchanges heat with the high-pressure hot gas at the outlet end of the centripetal turbine and the rectifying cone hot gas, and the exchanged hot gas is led into the annular gas outlet pipe through the outlet gas collecting transverse pipe and is led into the working medium transmission pipe through the annular gas outlet pipe.

Further, the pipe diameter of the annular air inlet pipe is smaller than that of the annular air outlet pipe, so that an annular cavity is formed between the inlet gas collecting transverse pipe and the outlet gas collecting transverse pipe, the heat exchange pipe row is arranged in the annular cavity and consists of a plurality of pipelines circumferentially arranged along the annular cavity;

and high-pressure hot gas at the hot gas outlet ends of the centripetal turbine and the rectifying cone passes through gaps of the heat exchange tube row, and meanwhile, cold gas entering from the inlet gas collecting transverse tube flows through the heat exchange tube row from outside to inside along the radial direction of the annular cavity, so that efficient heat exchange is realized.

Furthermore, the heat exchange tube row is composed of at least one row of pipelines which are arranged side by side, and a row of parallel pipelines which are axially distributed are arranged in the annular cavity in an Archimedes spiral way in a gradually outwards extending way by taking the inner diameter of the annular cavity as a starting point.

Further, the speed reducer is a planetary gear speed reducer, and a sun gear of the planetary gear speed reducer is sleeved at the end part of the turbine shaft; the rotor wing is sleeved on an outer gear ring of the planetary gear reducer; the speed reducer is used for matching the rotating speed of the rotor wing and the rotating speed of the turbine.

Further, the speed reducer is a planetary gear speed reducer, and a sun gear of the planetary gear speed reducer is sleeved at the end part of the motor shaft; the rotor wing is sleeved on an outer gear ring of the planetary gear reducer; the speed reducer is used for matching the rotating speed of the rotor wing and the rotating speed of the turbine.

Further, the working medium transmission pipe comprises a main transmission pipe and a branch transmission pipe, one end of the main transmission pipe is communicated with a working medium outlet of the working medium generating device, and the other end of the main transmission pipe is respectively communicated with a volute of the rotor wing device through the branch transmission pipe.

The beneficial effects of the invention are as follows: the invention adopts the gas turbine engine to generate high-energy working medium through the internal thermodynamic cycle, and the high-energy working medium collecting device is arranged on the gas turbine engine core machine and collects the redundant high-energy working medium generated by the high-energy working medium collecting device. The output end of the high-energy working medium collecting device is connected with the high-efficiency working medium transmission device, and the high-energy working medium is transmitted to the turbine device through the high-efficiency working medium transmission channel, so that the rotor wing is driven to rotate. Meanwhile, the rotor wing device is also provided with a motor and a turbine which are coaxially driven to rotate, electricity in the motor is collected, and the state of the rotary wing aircraft is regulated and controlled.

Compared with the existing rotor power system, the rotor power system has the greatest advantages that the vertical take-off and landing power system is realized by adopting a mode of combining working medium driving and electric driving, the high performance of the existing fuel driving and the high control precision of the electric driving are considered, the dependence of the rotor power system based on electric driving on high-energy-density energy storage equipment can be overcome, and the applicability of the vertical take-off and landing power system is improved; and secondly, the problems of poor speed regulation accuracy and insufficient flight stability in the vertical take-off and landing power system based on fuel drive can be solved, the flight stability is improved, the limitations of the existing rotor power system in technologies such as mechanical structure, electric energy storage and the like are eliminated, a primary structure is adopted, and a regenerative link is added, so that higher system efficiency and lower fuel consumption rate are obtained.

The invention further improves the efficiency of the existing rotor power system, reduces carbon emission, saves energy and protects environment, and simultaneously improves the realizability of the power system driven by working media, thereby filling the blank of the hybrid aircraft driven by working media.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic overall structure of embodiment 2 of the present invention;

FIG. 3 is a schematic diagram of the structure of the working medium generating device of the present invention;

FIG. 4 is a schematic view of the engine of the present invention;

FIG. 5 is a schematic structural view of the generator of the present invention;

FIG. 6 is a schematic view of the structure of the gas collecting device of the present invention;

FIG. 7 is a schematic view of a partially cut-away structure of a gas collecting apparatus of the present invention;

fig. 8 is a schematic view of an axial side structure of the regenerator of the present invention;

fig. 9 is a schematic view of a front view of a regenerator of the present invention;

figure 10 is a schematic cross-sectional view of a rotor assembly of the present invention;

FIG. 11 is a schematic cross-sectional view of a rotor assembly according to embodiment 2 of the present invention.

In the figure: 1. a turbine engine; 11. a compressor; 12. a diffuser; 13. a combustion chamber; 14. a centripetal turbine; 15. a rectifying cone; 16. a tail nozzle; 17. a casing; 2. a working medium generating device; 21. a gas collecting device; 211. a gas collecting ring; 212. an air duct; 213. a regulating valve; 214. an air-introducing pipe; 215. a bleed valve; 22. a heat returning device; 221. an annular air inlet pipe; 222. an inlet gas collection transverse pipe; 223. an annular air outlet pipe; 224. an outlet gas collection transverse pipe; 225. a heat exchange tube row; 4. a working medium transmission pipe; 41. a main transfer pipe; 42. a branch transmission pipe; 5. a generator; 51. a generator turbine; 52. a volute; 53. a motor housing; 54. a motor rotor; 55. stator windings; 56. a generator shaft; 7. a rotor device; 7-1, a rotor wing; 7-2, an inner casing; 7-3, a motor; 7-4, a turbine; 7-5, a bearing; 7-6, a bracket; 7-7, turbine shaft; 7-8, a speed reducer; 7-9, a volute; 7-10, connotation spray pipe; 81. a storage battery; 82. and (5) conducting wires.

Detailed Description

The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.

Example 1: as shown in fig. 1 and fig. 3-10, a rotorcraft hybrid power system based on working medium driving comprises a turbine engine 1 and a rotor device 7, wherein the rotor device 7 is arranged around a rotor body in a pairwise symmetrical manner by taking the axis of the rotor body as the center, and at least two pairs are arranged;

the rotor device 7 comprises a rotor 7-1 and an inner casing 7-2, wherein the rotor 7-1 is arranged at one end of the inner casing 7-2, a turbine 7-4 is arranged in a cavity at the other end of the inner casing 7-2, a turbine shaft 7-7 of the turbine 7-4 is arranged on a support 7-6 in the inner casing 7-2 through a bearing 7-5, the end part of the turbine shaft 7-7 is connected with the rotor 7-1 through a speed reducer 7-8, a volute 7-9 matched with the turbine 7-4 is arranged in the cavity of the inner casing 7-2, and an inclusion spray pipe 7-10 is further communicated with one end of an air inlet of the volute 7-9; the turbine shaft 7-7 is coaxially arranged with the inner casing 7-2;

the turbine engine 1 introduces high-temperature and high-pressure working medium into the spiral casing 7-9 of the rotor wing device 7 through the working medium generating device 2 and the working medium transmission pipe 4, the spiral casing 7-9 is used for gathering the high-temperature and high-pressure working medium, and the high-temperature and high-pressure working medium drives the turbine 7-4 and drives the turbine shaft 7-7 to rotate so as to enable the rotor wing 7-1 to rotate, and power is provided for the rotorcraft.

The working medium generating device 2 comprises a gas collecting device 21 and a heat regenerating device 22, wherein a gas compressor 11 and a diffuser 12 are coaxially arranged in sequence along the direction of cold air in a casing at the cold air inlet of the turbine engine 1, and the gas collecting device 21 is arranged in a casing 17 at the cold air outlet of the diffuser 12; a centripetal turbine 14 and a rectifying cone 15 are sequentially arranged in a casing 17 at a high-pressure hot gas outlet of a combustion chamber 13 of the turbine engine 1 along the hot gas direction, and a heat regenerative device 22 is communicated with a tail nozzle 16 at the hot gas outlet direction of the rectifying cone 15; the gas collecting device 21 is used for collecting part of cold gas entering the turbine engine 1 and guiding the cold gas to a cold gas inlet of the heat recovery device 22, and the heat recovery device 22 is used for exchanging heat between the cold gas entering the heat recovery device 22 and high-pressure hot gas in the tail nozzle 16 and transmitting the exchanged hot gas to the generator 5 through the working medium transmission pipe 4;

one end of the working medium transmission pipe 4 is communicated with a hot gas outlet of the heat regeneration device 22, and the other end of the working medium transmission pipe 4 is communicated with the turbine volute device.

The gas collecting device 21 comprises a gas collecting ring 211 with an annular cavity and a U-shaped section, at least four gas guide pipes 212 are uniformly communicated on the same annular surface of the gas collecting ring 211, regulating valves 213 are arranged on the gas guide pipes 212, and the gas collecting ring 211 is communicated with a cold air inlet of the heat regenerating device 22 through the gas guide pipes 212;

the U-shaped opening of the gas collecting ring 211 is positioned on the inner ring surface of the gas collecting ring 211, and the gas collecting ring 211 is fixedly connected and communicated with the casing 17 through two side walls at the U-shaped opening, so that the gas collecting ring 211 and the casing 17 jointly form an outer ring channel of the outlet air flow of the compressor 11, the outlet air flow channel of the compressor 11 is an inner ring channel, cold air flowing in from the outer ring channel enters the heat regenerating device 22 through the gas collecting ring 21 and the air guide pipe 22, and the cold air flowing in from the inner ring channel enters the cold air input end of the combustion chamber 13.

The heat recovery device 22 comprises an annular air inlet pipe 221 and an annular air outlet pipe 223, and a plurality of inlet air collection transverse pipes 222 are arranged on the same annular surface of the annular air inlet pipe 221 in a circumferential direction; a plurality of outlet gas collecting cross pipes 224 are arranged on the same annular surface circumference of the annular gas outlet pipe 223; the inlet gas-collecting horizontal pipe 222 is communicated with the outlet gas-collecting horizontal pipe 224 through a heat exchange pipe row 225;

the gas collecting device 21 is communicated with the annular gas inlet pipe 221 through the gas guide pipe 212, the gas collecting device 21 guides the collected cold gas into the annular gas inlet pipe 221, so that the cold gas sequentially enters the inlet gas collecting transverse pipe 222 and the heat exchange pipe row 225, the cold gas in the heat exchange pipe row 225 exchanges heat with the high-pressure hot gas at the hot gas outlet ends of the centripetal turbine 14 and the rectifying cone 15, the exchanged hot gas is guided into the annular gas outlet pipe 223 through the outlet gas collecting transverse pipe 224, and the hot gas is guided into the working medium transmission pipe 4 through the annular gas outlet pipe 223.

The pipe diameter of the annular air inlet pipe 221 is smaller than that of the annular air outlet pipe 223, so that an annular cavity is formed between the inlet gas collecting transverse pipe 222 and the outlet gas collecting transverse pipe 224, a heat exchange pipe row 225 is arranged in the annular cavity, and the heat exchange pipe row 225 consists of a plurality of pipelines circumferentially arranged along the annular cavity;

the high-pressure hot gas at the hot gas outlet ends of the centripetal turbine 14 and the rectifying cone 15 passes through the gaps of the heat exchange tube row 225, and meanwhile, the cold gas entering from the inlet gas collecting transverse tube 222 flows through the heat exchange tube row 225 from outside to inside along the radial direction of the annular cavity, so that efficient heat exchange is realized.

The heat exchange tube row 225 is formed by at least one row of parallel tubes, and one row of parallel tubes which are axially distributed takes the inner diameter of the annular cavity as a starting point and is gradually and outwardly arranged in the annular cavity in an extending manner in an archimedes spiral manner.

The speed reducer 7-8 is a planetary gear speed reducer, and a sun gear of the planetary gear speed reducer is sleeved at the end part of the turbine shaft 7-7; rotor 7-1 is sleeved on the outer gear ring of the planetary gear reducer; the speed reducer 7-8 is used for matching the rotational speed of the rotor 7-1 with the rotational speed of the turbine 7-4.

The working medium transmission pipe 4 comprises a main transmission pipe 41 and a branch transmission pipe 42, one end of the main transmission pipe 41 is communicated with a working medium outlet of the working medium generating device 2, and the other end of the main transmission pipe 41 is respectively communicated with the spiral case 7-9 of the rotor wing device 7 through the branch transmission pipe 42.

The working mode of the embodiment is as follows:

the turbine engine 1 generates a high-energy working medium by utilizing the brayton cycle occurring therein, and the compressor 11 sucks in and compresses the flowing air. The compressed air is split into two streams at the output end of the core compressor 11, one stream enters the gas collecting ring 211 from the input end of the gas collecting ring 211, and the other stream enters the combustion chamber 13 to be mixed with fuel for combustion, so that high-temperature and high-pressure fuel gas is formed. The gas expands in the centripetal turbine 14 to do work and pushes the compressor 11 to operate. The high-temperature and high-pressure gas after the centripetal turbine 14 continues to exchange heat with the compressed air through the heat recovery device 22. The combustion gases are discharged from the tail pipe 16.

Air collected by the air collecting ring 211 is transferred to the annular air inlet pipe 221 through the air guide pipe 212. The air flow enters the heat exchange tube row 225 through an inlet air collection cross tube 222 connected with the annular air inlet tube 221. The hot gas flows through the gaps of the heat exchange tube row 225 and exchanges heat with the compressed air in the heat exchange tube row 225 through the tube wall. The hot air after heat exchange is collected to the hot air annular air outlet pipe 223 through the outlet air collecting transverse pipe 224 connected with the pipe outlet, and enters the working medium transmission pipe 4.

The compressed air with high temperature and high pressure is discharged from the main transmission pipe 41 of the working medium transmission pipe 4 and is transmitted to the rotor devices 7 through the branch transmission pipe 42, and the turbine 7-4 in the rotor devices 7 is driven to rotate by the high temperature and high pressure air, so that the rotor 7-1 connected with the turbine shaft 7-7 is driven to rotate, and power is provided for the rotorcraft.

Example 2: as shown in fig. 2 and 11, the embodiment 1 is the same except that the turbine shaft 7-7 is provided with a motor 7-3 coaxially with the turbine shaft 7-7, one end of a motor shaft of the motor 7-3 is fixed on the bracket 7-6 through a bearing, and the other end of the motor 7-3 is connected with the turbine shaft 7-7; a battery 81 is also provided on the rotorcraft, and the motor 7-3 is electrically connected to the battery 81 by a wire 82.

The speed reducer 7-8 is a planetary gear speed reducer, and a sun gear of the planetary gear speed reducer is sleeved at the end part of a motor shaft; rotor 7-1 is sleeved on the outer gear ring of the planetary gear reducer; the speed reducer 7-8 is used for matching the rotor 7-1 with the rotation speed of the motor shaft.

The working procedure of this embodiment is: when the turbine 7-4 is at a low speed, the motor 7-3 is used for driving the turbine 7-4 to rotate and accelerate to start; at a high speed of the turbine 7-4, the turbine 7-4 drives the motor 7-3 to generate electricity, and the electricity is stored in the storage battery 81 through the lead 82.

The foregoing is only illustrative of the present invention and is not to be construed as limiting thereof, but rather as various modifications, equivalent arrangements, improvements, etc., within the spirit and principles of the present invention.

Claims (10)

1. The rotorcraft hybrid power system based on working medium driving is characterized by comprising a turbine engine (1) and a rotor wing device (7), wherein the rotor wing device (7) is symmetrically arranged around the rotor wing body in pairs with the axis of the rotor wing body as the center, and at least two pairs of rotor wing devices are arranged;

the rotor wing device (7) comprises a rotor wing (7-1) and an inner casing (7-2), wherein the rotor wing (7-1) is arranged at one end of the inner casing (7-2), a turbine (7-4) is arranged in a cavity at the other end of the inner casing (7-2), a turbine shaft (7-7) of the turbine (7-4) is arranged on a support (7-6) in the inner casing (7-2) through a bearing (7-5), the end part of the turbine shaft (7-7) is connected with the rotor wing (7-1) through a speed reducer (7-8), a volute (7-9) matched with the turbine (7-4) is arranged in the cavity of the inner casing (7-2), and an inner culvert spray pipe (7-10) is further arranged at one end of an air inlet of the volute (7-9) in a communicating manner; the turbine shaft (7-7) and the inner casing (7-2) are coaxially arranged;

the turbine engine (1) guides high-temperature and high-pressure working medium into the volute (7-9) of the rotor wing device (7) through the working medium generating device (2) and the working medium transmission pipe (4), and the volute (7-9) is used for collecting high-pressure hot gas to drive the turbine (7-4) to drive the turbine shaft (7-7) to rotate, so that the rotor wing (7-1) rotates and power is provided for the rotorcraft.

2. The rotorcraft hybrid power system based on working medium driving according to claim 1, further comprising a motor (7-3) coaxially arranged with the turbine shaft (7-7), wherein one end of a motor shaft of the motor (7-3) is fixed on the bracket (7-6) through a bearing, and the other end of the motor (7-3) is connected with the turbine shaft (7-7); the rotary wing aircraft is also provided with a storage battery (81), the motor (7-3) is electrically connected with the storage battery (81) through a lead (82), and the storage battery (81) is used for driving the turbine (7-4) to rotate and accelerate to start by using the motor (7-3) when the turbine (7-4) is at a low speed; when the turbine (7-4) is at a high speed, the turbine (7-4) drives the motor (7-3) to generate electricity, and the electricity is stored in the storage battery (81) through the lead wire (82).

3. The rotorcraft hybrid power system based on working medium driving according to claim 1, wherein the working medium generating device (2) comprises a gas collecting device (21) and a heat regenerating device (22), a gas compressor (11) and a diffuser (12) are coaxially arranged in sequence along the cold air direction in a casing at the cold air inlet of the turbine engine (1), and the gas collecting device (21) is arranged in a casing (17) at the cold air outlet of the diffuser (12); a centripetal turbine (14) and a rectifying cone (15) are sequentially arranged in a casing (17) at a high-pressure hot gas outlet of a combustion chamber (13) of the turbine engine (1) along the hot gas direction, and a heat regenerative device (22) is communicated with a tail nozzle (16) at the hot gas outlet direction of the rectifying cone (15); the gas collecting device (21) is used for collecting part of cold gas entering the turbine engine (1) and guiding the cold gas to a cold gas inlet of the heat regenerating device (22), and the heat regenerating device (22) is used for exchanging heat between the cold gas entering the heat regenerating device (22) and high-pressure hot gas in the tail nozzle (16) and transmitting the exchanged hot gas to the generator (5) through the working medium transmission pipe (4);

one end of the working medium transmission pipe (4) is communicated with a hot gas outlet of the heat regeneration device (22), and the other end of the working medium transmission pipe (4) is communicated with the turbine volute device.

4. A rotorcraft hybrid power system based on working medium driving as claimed in claim 3, wherein the gas collecting device (21) comprises a gas collecting ring (211) with a ring-shaped cavity and a U-shaped section, at least four gas guide pipes (212) are uniformly communicated on the same ring surface of the gas collecting ring (211), regulating valves (213) are arranged on the gas guide pipes (212), and the gas collecting ring (211) is communicated with a cold air inlet of the heat regenerating device (22) through the gas guide pipes (212);

the U-shaped opening of the gas collecting ring (211) is positioned on the inner ring surface of the gas collecting ring (211), the gas collecting ring (211) is fixedly connected and communicated with the casing (17) through two side walls at the U-shaped opening, so that the gas collecting ring (211) and the casing (17) jointly form an outer ring channel of the outlet airflow of the compressor (11), an outlet airflow channel of the compressor (11) is an inner ring channel, cold air flowing in from the outer ring channel enters the heat regenerating device (22) through the gas collecting ring (21) and the air guide pipe (22), and cold air flowing in from the inner ring channel enters the cold air input end of the combustion chamber (13).

5. A rotorcraft hybrid power system based on working medium driving as claimed in claim 3, wherein the heat regenerating device (22) comprises an annular air inlet pipe (221) and an annular air outlet pipe (223), and a plurality of inlet air collecting cross pipes (222) are arranged on the same annular surface of the annular air inlet pipe (221) in a circumferential direction; a plurality of outlet gas collecting transverse pipes (224) are arranged on the same annular surface circumference of the annular gas outlet pipe (223); the inlet gas-collecting horizontal pipe (222) is communicated with the outlet gas-collecting horizontal pipe (224) through a heat exchange pipe row (225);

the gas collecting device (21) is communicated with the annular gas inlet pipe (221) through the gas guide pipe (212), the gas collecting device (21) guides the collected cold gas into the annular gas inlet pipe (221), so that the cold gas in the inlet gas collecting transverse pipe (222) and the heat exchange pipe row (225) sequentially enter the heat exchange pipe row (225), the cold gas in the heat exchange pipe row (225) exchanges heat with the high-pressure hot gas at the hot gas outlet end of the centripetal turbine (14) and the rectifying cone (15), and the exchanged hot gas is guided into the annular gas outlet pipe (223) through the outlet gas collecting transverse pipe (224) and is guided into the working medium transmission pipe (4) through the annular gas outlet pipe (223).

6. The rotorcraft hybrid power system based on actuation of a working medium according to claim 5, wherein the pipe diameter of the annular air inlet pipe (221) is smaller than the pipe diameter of the annular air outlet pipe (223), so that an annular cavity is formed between the inlet air collecting cross pipe (222) and the outlet air collecting cross pipe (224), the heat exchange pipe row (225) is arranged in the annular cavity, and the heat exchange pipe row (225) is composed of a plurality of pipes circumferentially arranged along the annular cavity;

the high-pressure hot gas at the hot gas outlet ends of the centripetal turbine (14) and the rectifying cone (15) passes through the gaps of the heat exchange tube rows (225), and meanwhile, cold gas entering from the inlet gas collecting transverse tube (222) flows through the heat exchange tube rows (225) from outside to inside along the radial direction of the annular cavity, so that efficient heat exchange is realized.

7. The rotorcraft hybrid power system driven by a working medium according to claim 5, wherein said heat exchange tube row (225) is composed of at least one row of parallel tubes arranged side by side, and a row of axially distributed parallel tubes is arranged in said annular cavity in an archimedes spiral form extending gradually outwards from the inside diameter of said annular cavity.

8. The rotorcraft hybrid power system based on working medium driving according to claim 1, wherein the speed reducer (7-8) is a planetary gear speed reducer, and a sun gear of the planetary gear speed reducer is sleeved at the end part of the turbine shaft (7-7); the rotor wing (7-1) is sleeved on an outer gear ring of the planetary gear reducer; the speed reducer (7-8) is used for matching the rotating speed of the rotor (7-1) and the rotating speed of the turbine (7-4).

9. The rotorcraft hybrid power system based on working medium driving according to claim 2, wherein the speed reducer (7-8) is a planetary gear speed reducer, and a sun gear of the planetary gear speed reducer is sleeved at the end part of the motor shaft; the rotor wing (7-1) is sleeved on an outer gear ring of the planetary gear reducer; the speed reducer (7-8) is used for matching the rotating speed of the rotor (7-1) and the rotating speed of the turbine (7-4).

10. The rotorcraft hybrid power system based on the actuation of working medium according to any one of claims 1-9, wherein the working medium transmission pipe (4) comprises a main transmission pipe (41) and a branch transmission pipe (42), one end of the main transmission pipe (41) is communicated with the working medium outlet of the working medium generating device (2), and the other end of the main transmission pipe (41) is respectively communicated with the spiral case (7-9) of the rotorcraft device (7) through the branch transmission pipe (42).