Composite driving method for large load rotor system

Abstract

The present application relates to the technical field of starting control of large load rotor system, and particularly relates to a composite driving method of large load rotor system, which comprises the following steps: after receiving a starting instruction, a control unit drives a gas turbine unit to work, gas output by the gas turbine is guided to be sprayed from a rotor nozzle at the end of a rotor, so that the rotor starts to rotate; when the rotating speed of the gas turbine of the gas turbine unit reaches a self-sustaining rotating speed, the gas turbine provides gas for a piston engine unit, drives the piston engine to start, and the mechanical torque output by the piston engine is transmitted to the rotor through a main transmission shaft, and the gas output by the piston engine is guided to be sprayed from the rotor nozzle; the control unit adjusts the engagement degree of a clutch of the piston engine unit according to the rotating speed of the rotor, and when the rotating speed of the rotor reaches a preset working rotating speed, the clutch is completely tightened, and the starting of the large load rotor system is completed; the present application can realize reliable starting of the large load rotor system.

Description

Technical Field

[0001] This invention relates to the field of starting control technology for high-load rotor systems, and more specifically to a composite drive method for high-load rotor systems. Background Technology

[0002] As a new type of special-purpose aircraft, the tip-jet gyroplane employs a combined propulsion principle of "rotor lift + tip-jet assistance," enabling both vertical takeoff and landing and high-speed forward flight. To meet the requirements of high power-to-weight ratio, high fuel economy, and high-speed performance, a certain model innovatively adopts a turbojet-piston hybrid power system. However, during the start-up phase of this system, how to reliably and efficiently drive the large-inertia rotor system from a standstill to its operating speed has become a key technical challenge.

[0003] Currently, there are two main technical approaches to starting high-load rotor systems: one is a single piston engine mechanical drive scheme. This scheme directly connects the piston engine crankshaft output to the main drive shaft via a clutch, mechanically transmitting torque to the rotor. Due to the large rotational inertia of the rotor system, significant static friction and aerodynamic drag must be overcome during startup. The piston engine needs to output extremely high peak torque, which places high demands on the strength, rigidity, and fatigue life of mechanical components such as the drive shaft, gears, and clutch. Therefore, high-strength special materials and complex structural reinforcement designs are required, significantly increasing the weight, complexity, and manufacturing cost of the transmission system. The other approach is a single gas turbine jet drive scheme. This scheme utilizes high-temperature, high-pressure gas generated by a gas generator, which is led to the rotor tip nozzle through a hollow main shaft. The jet reaction force generates driving torque, achieving non-contact torque transmission. This avoids the peak load problem of the mechanical transmission system and enhances the output capacity of the gas generator through engine exhaust energy and booster fuel. However, this scheme has low gas generation efficiency in the low speed range, and it is difficult to overcome the stationary inertia of the rotor quickly by relying solely on the tip jet, resulting in a slow start-up acceleration process. In addition, the system requires a centrifugal supercharger, a gas generator and a fuel supply system, which increases the system complexity and control difficulty. At the same time, because the gas energy accumulation takes a certain amount of time, there is a significant lag in the power response at the beginning of the start-up, which makes it difficult to meet the requirements for rapid start-up.

[0004] In summary, existing starting schemes based on a single power source all have obvious limitations: the mechanical drive scheme of piston engines puts excessive load on the transmission system, which is not conducive to system lightweighting and cost control; while the pure jet drive scheme of gas turbines suffers from insufficient starting torque and poor acceleration performance.

[0005] Therefore, there is an urgent need in this field for an innovative composite drive method that can organically combine mechanical transmission and jet drive paths, giving full play to the low-speed, high-torque characteristics of piston engines and the high-energy gas injection advantages of gas turbines, so as to achieve torque complementarity, load balancing and performance optimization during the starting process. Summary of the Invention

[0006] In view of the above problems, the present invention provides a composite drive method for a large load rotor system, which solves the technical problems of large load rotor systems being not lightweight enough, costing high and having limited reliability in the prior art.

[0007] This invention provides a composite drive method for a high-load rotor system, the high-load rotor system comprising: a piston engine unit, a gas turbine unit, a main drive shaft, and a rotor 20; The main drive shaft includes a central inner tube 18 and an outer bypass pipe 19. The rotor 20 has an air passage inside, and the outer bypass pipe 19 is connected to the air passage inside the rotor 20. The piston engine unit is mechanically connected to the central inner tube 18, and the outlet of the piston engine unit is connected to the outer bypass pipe 19. The gas turbine unit's outlet is connected to the outer bypass pipe 19. The gas turbine unit has a compressor outlet, which is connected to the piston engine unit's inlet. The composite drive method for the high-load rotor system includes the following steps: Step S1: After receiving the start command, the starter 7 of the control unit drives the compressor 8 to work. The gas output from the gas turbine is guided and ejected from the rotor nozzle 21 at the end of the rotor 20, causing the rotor to start rotating. Step S2: When the gas turbine speed of the gas turbine unit reaches the self-sustaining speed, the gas turbine provides gas to the piston engine 1 of the piston engine unit, driving the piston engine 1 to ignite and run. The mechanical torque output by the piston engine 1 is transmitted to the rotor 20 through the main drive shaft, and the gas output by the piston engine 1 is guided out from the rotor nozzle 21. Step S3: The control unit monitors the rotor speed in real time and adjusts the engagement degree of the clutch 3 of the piston engine unit according to the rotor speed. When the rotor speed reaches the preset operating speed, the clutch 3 is fully engaged to complete the start-up of the heavy load rotor system.

[0008] Preferably, the piston engine unit includes a piston engine 1, a piston engine crankshaft 2, a clutch 3, and a commutator 4; The piston machine 1 is a piston engine. The output end of the piston machine 1 is the piston machine crankshaft 2. The piston machine crankshaft 2 is connected to one end of the clutch 3. The other end of the clutch 3 is connected to the drive end of the commutator 4 through a rotating shaft. The driven end of the commutator 4 is connected to the main drive shaft. The main drive shaft is connected to the rotor 20. The gas turbine unit includes a compressor 8, a combustion chamber 9, and a turbine 10, which are connected in sequence. The inner central tube 18 and the outer bypass pipe 19 are connected together. The inner central tube 18 is used for transmission, and the outer bypass pipe 19 can introduce gas into the internal air passage of the rotor 20. The rotor 20 has a rotor nozzle 21 at its end; the gas in the rotor 20 air passage is ejected through the rotor nozzle 21, generating torque to drive the rotor to rotate.

[0009] Preferably, the high-load rotor system further includes a gas distribution unit; the gas distribution unit includes: a compressor intake duct 16, a piston engine intake duct 6, a piston engine exhaust duct 5, a gas turbine exhaust duct 11, a gas turbine intake pipeline 15, and a gas turbine exhaust duct 14. The compressor outlet of compressor 8 is connected to the inlet of piston machine 1 via compressor slurry 16, first solenoid valve 17 and piston machine inlet 6 in sequence; the outlet of piston machine 1 is connected to the outer bypass pipe 19 via piston machine exhaust pipe 5 and is connected to the outer bypass pipe 19; the gas turbine outlet is connected to the outer bypass pipe 19 via gas turbine slurry 11, second solenoid valve 12 and gas turbine slurry 15 in sequence; the gas turbine outlet is connected to the gas turbine exhaust pipe 14 via gas turbine slurry 11 and third solenoid valve 13 in sequence.

[0010] Preferably, the high-load rotor system further includes a control unit; the control unit includes: a starter 7, a first solenoid valve 17, a second solenoid valve 12, and a third solenoid valve 13; the starter 7 is connected to the gas turbine unit and is used to drive the compressor 8 to work, and the first solenoid valve 17, the second solenoid valve 12, and the third solenoid valve 13 are all used to control the on / off state of their respective gas paths.

[0011] Preferably, in step S1, when the starter 7 of the control unit drives the gas turbine unit to work, the control unit controls the first solenoid valve 17 to remain closed, so that all the gas from the compressor 8 enters the combustion chamber 9 to burn and do work. The specific steps of guiding the gas output from the gas turbine to be ejected from the rotor nozzle 21 include: the control unit controlling the second solenoid valve 12 to remain open; the gas output from the gas turbine enters the outer bypass pipe 19 of the main drive shaft through the gas turbine gas passage 11 and the second solenoid valve 12, and is finally ejected from the rotor nozzle 21, generating the initial tip jet torque, causing the rotor to start rotating slowly.

[0012] Preferably, in step S2, the step of the gas turbine providing gas to the piston engine 1 specifically includes: the control unit opening the first solenoid valve 17, and the gas generated by the compressor 8 sequentially passing through the compressor intake duct 16, the first solenoid valve 17, and the piston engine intake duct 6 into the piston engine 1.

[0013] Preferably, in step S2, the step of transmitting the mechanical torque output by the piston machine 1 to the rotor through the main drive shaft specifically includes: the mechanical torque output by the piston crankshaft 2 of the piston machine 1 passes sequentially through the clutch 3, the commutator 4 and the main drive shaft to drive the rotor 20 to rotate.

[0014] Preferably, in step S2, the step of guiding the gas output by the piston machine 1 to be ejected from the rotor nozzle 21 specifically includes: the gas is discharged from the outlet of the piston machine 1, the gas enters the outer bypass pipe 19 through the piston machine exhaust passage 5, and is finally ejected from the rotor nozzle 21.

[0015] Preferably, in step S3, the step of adjusting the engagement degree of the clutch 3 according to the rotor speed specifically includes: Adjust the engagement degree of clutch 3 so that the engagement degree of clutch 3 is positively correlated with the rotor speed.

[0016] Preferably, in step S3, during the process of adjusting the engagement degree of the clutch 3, the control unit adjusts the opening degree of the second solenoid valve 12 and the third solenoid valve 13 according to the rotor speed feedback.

[0017] Compared with the prior art, the present invention has at least the following beneficial effects: (1) This invention combines the mechanical transmission of the piston engine with the jet drive of the gas turbine through a composite drive method, and provides the main shaft torque and jet torque simultaneously during the start-up phase, thereby achieving coordinated power output, overcoming the problem of insufficient start-up capability of a single power source, and improving the start-up reliability and efficiency of the system.

[0018] (2) The present invention utilizes the jet torque of the propeller tip to share the starting load, which greatly reduces the peak load of the main drive system and creates favorable conditions for lightweight design. At the same time, the direct injection of gas into the propeller tip avoids the complex problem of speed matching, eliminates the need for traditional large reducers, simplifies the system structure, and reduces maintenance costs and failure risks.

[0019] (3) This invention achieves precise timing matching and smooth torque transition of mechanical and jet drive through the coordinated management of clutch and air circuit valve by intelligent control unit, which can ensure smooth start-up process, improve power-to-weight ratio and start-up response speed, and meet the strict requirements of modern aircraft for rapid take-off and efficient power conversion. Attached Figure Description

[0020] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention.

[0021] Figure 1 A flowchart of the composite drive method for a high-load rotor system provided by the present invention.

[0022] Figure 2 The structural diagram of the high-load rotor system provided by the present invention.

[0023] Figure 3 A detailed flowchart of the composite drive method for a high-load rotor system provided by the present invention.

[0024] Reference numerals: 1-Piston engine, 2-Piston engine crankshaft, 3-Clutch, 4-Reversing gear, 5-Piston engine exhaust port, 6-Piston engine intake port, 7-Starter, 8-Compressor, 9-Combustion chamber, 10-Turbine, 11-Gas turbine intake port, 12-Second solenoid valve, 13-Third solenoid valve, 14-Gas turbine exhaust port, 15-Gas turbine bleed air line, 16-Compressor bleed air line, 17-First solenoid valve, 18-Central inner pipe, 19-Outer bypass pipe, 20-Rotor, 21-Rotor nozzle. Detailed Implementation

[0025] To better understand the above-described objectives, features, and advantages of the present invention, the invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other. Furthermore, the present invention can be implemented in other ways different from those described herein; therefore, the scope of protection of the present invention is not limited to the specific embodiments disclosed below.

[0026] This invention employs a composite drive method, organically integrating the mechanical transmission path of a piston engine with the propeller tip jet drive path of a gas turbine. During the startup phase, it simultaneously outputs main shaft torque and jet torque, forming a synergistic drive effect and effectively overcoming the shortcomings of insufficient startup capability of a single power source. By sharing the startup load through propeller tip jet torque, the peak load of the main transmission system is significantly reduced, thereby promoting lightweight system design. Furthermore, the drive method of directly drawing gas to the propeller tip achieves precise timing matching and smooth torque transition between mechanical and jet drives, ensuring the stability of the startup process. This invention fully leverages the advantages of both power sources, achieving power complementarity during the startup phase, significantly improving the system's power-to-weight ratio and startup response speed, meeting the requirements of modern aircraft for rapid takeoff and efficient power conversion.

[0027] To illustrate the effectiveness of the method proposed in this invention, the following detailed description of the above technical solution is provided through a specific embodiment, such as... Figure 1 , Figure 2 , Figure 3 As shown, a composite drive method for a high-load rotor system is disclosed and applied to the high-load rotor system.

[0028] The high-load rotor system includes: a piston engine unit, a gas turbine unit, a main drive shaft, a rotor 20, a gas distribution unit, and a control unit.

[0029] The piston engine unit includes a piston engine 1, a piston engine crankshaft 2, a clutch 3, and a commutator 4.

[0030] The piston engine 1 is a piston engine. The output end of the piston engine 1 is the piston engine crankshaft 2. The piston engine crankshaft 2 is connected to one end of the clutch 3. The other end of the clutch 3 is connected to the drive end of the commutator 4 through a rotating shaft. The driven end of the commutator 4 is connected to the main drive shaft, and the main drive shaft is connected to the rotor 20. The piston engine 1 has an air inlet and an air outlet.

[0031] The gas turbine unit includes a compressor 8, a combustion chamber 9, and a turbine 10, which are connected in sequence. The compressor 8 has a compressor outlet, and the gas turbine unit has a gas turbine outlet.

[0032] The main drive shaft has a central inner tube 18 and an outer bypass pipe 19, which are sleeved together. The central inner tube 18 is used for transmission, and the outer bypass pipe 19 can introduce gas into the rotor 20.

[0033] The rotor 20 has a rotor nozzle 21 at its end; the rotor 20 has an air passage inside, and the gas in the rotor 20 air passage is ejected through the rotor nozzle 21 to generate the torque that drives the rotor to rotate.

[0034] The gas distribution unit includes: a compressor intake duct 16, a piston engine intake duct 6, a piston engine exhaust duct 5, a gas turbine intake duct 11, a gas turbine intake pipeline 15, and a gas turbine exhaust duct 14.

[0035] The compressor outlet of compressor 8 is connected to the air inlet of piston machine 1 via compressor intake duct 16, first solenoid valve 17 and piston machine intake duct 6.

[0036] The outlet of the piston machine 1 is connected to the outer bypass pipe 19 through the piston machine exhaust passage 5, and is in communication with the outer bypass pipe 19.

[0037] The gas turbine outlet is connected to the outer bypass pipe 19 via the gas turbine air passage 11, the second solenoid valve 12, and the gas turbine bleed air pipeline 15.

[0038] The gas turbine outlet is connected to the gas turbine exhaust duct 14 via gas turbine inlet 11 and third solenoid valve 13. The third solenoid valve 13 is used to regulate the flow rate of the gas turbine exhaust duct 14.

[0039] The control unit includes: a starter 7, a first solenoid valve 17, a second solenoid valve 12, and a third solenoid valve 13.

[0040] The starter 7 is connected to the gas turbine unit and is used to drive the compressor 8. The first solenoid valve 17, the second solenoid valve 12 and the third solenoid valve 13 are all used to control the opening and closing of the gas circuit.

[0041] The control unit can also control the engagement state of the clutch 3.

[0042] Gas turbine pre-start: The starter drives the gas turbine to its self-sustaining speed. During this period, the first solenoid valve 17 at the compressor outlet is closed. The gas turbine exhaust enters the main drive shaft through the gas turbine gas passage and is ejected from the rotor nozzle to generate the initial tip jet torque. Gas start-up and initial loading of piston engine: After the gas turbine reaches its self-sustaining speed, the first solenoid valve 17 at the compressor outlet is opened to introduce high-pressure gas to drive the piston engine to ignite; then the controllable clutch 3 is gradually tightened to transmit the output torque of the piston engine to the main drive shaft, forming the main shaft torque; Tip jet auxiliary drive: Piston engine exhaust enters the main drive shaft, mixes with gas turbine exhaust, and is ejected together through the rotor nozzle to enhance tip jet torque; Composite torque drive and intelligent clutch management: The main shaft torque and the propeller tip jet torque together constitute a composite drive torque, which works together to accelerate the rotor; the control unit dynamically adjusts the clutch engagement degree according to the rotor speed until the rotor speed reaches the predetermined value, the clutch is fully engaged, and the start-up phase is completed.

[0043] The specific implementation steps of the composite drive method for the high-load rotor system are as follows: Step S1: After receiving the start command, the starter 7 drives the gas turbine unit to work. The gas output from the gas turbine is guided and ejected from the rotor nozzle 21, causing the rotor to start rotating. In this step, the starter motor 7 is first activated to drive the gas turbine to rotate. Specifically, the control unit controls the first solenoid valve 17 to remain closed, allowing all the gas from the compressor 8 to enter the combustion chamber 9 for combustion and work.

[0044] The specific steps of guiding the gas output from the gas turbine to be ejected from the rotor nozzle 21 include: the control unit controlling the second solenoid valve 12 to remain open; the gas output from the gas turbine enters the outer bypass pipe 19 of the main drive shaft through the gas turbine gas passage 11 and the second solenoid valve 12, and is finally ejected from the rotor nozzle 21, generating the initial tip jet torque, causing the rotor to start rotating slowly.

[0045] Step S2: When the gas turbine reaches its self-sustaining speed, the gas turbine provides gas to the piston engine 1, driving the piston engine 1 to ignite and operate. The mechanical torque output by the piston engine 1 is transmitted to the rotor through the main drive shaft, and the gas output by the piston engine 1 is guided out from the rotor nozzle 21. In this step, when the gas turbine speed reaches the self-sustaining speed, the specific steps of the gas turbine supplying gas to the piston machine 1 include: the control unit opens the first solenoid valve 17, and the gas generated by the compressor 8 enters the piston machine 1 through the compressor intake duct 16, the first solenoid valve 17 and the piston machine intake duct 6 in sequence.

[0046] The specific steps of transmitting the mechanical torque output by the piston engine 1 to the rotor via the main drive shaft include: the mechanical torque output by the piston crankshaft 2 of the piston engine 1 passes sequentially through the clutch 3, the commutator 4 and the main drive shaft, driving the rotor 20 to rotate.

[0047] The specific steps of guiding the gas output from the piston engine 1 to be ejected from the rotor nozzle 21 include: the gas is discharged from the outlet of the piston engine 1, the gas enters the outer bypass pipe 19 through the piston engine exhaust passage 5, and is finally ejected from the rotor nozzle 21.

[0048] Through the above steps, the present invention enables the rotor to accelerate rotation under the combined action of the main shaft torque and the propeller tip jet torque.

[0049] Step S3: The control unit monitors the rotor speed in real time and adjusts the engagement degree of the clutch 3 according to the rotor speed. When the rotor speed reaches the preset working speed, the clutch 3 is fully engaged to complete the start-up of the heavy load rotor system.

[0050] In this step, the step of adjusting the engagement degree of clutch 3 according to the rotor speed specifically includes: The engagement degree of clutch 3 is positively correlated with the rotor speed. At low speeds, the clutch engagement degree is low to avoid excessive impact on the transmission system. As the speed increases, the clutch engagement degree is gradually increased until the rotor speed reaches the preset operating speed, at which point the clutch is fully engaged. After this, the additional energy required for the rotor system to start is entirely provided by the gas turbine, completing the start-up of the high-load rotor system.

[0051] In some embodiments, during the process of adjusting the engagement degree of the clutch 3, the control unit can adjust the opening degree of the second solenoid valve 12 and the third solenoid valve 13 according to the rotor speed feedback, and adjust the jet energy in real time.

[0052] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0053] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0054] In this invention, the terms "first," "second," "third," and "fourth" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. The term "multiple" refers to two or more unless otherwise expressly defined.

[0055] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A composite drive method for a high-load rotor system, characterized in that, The high-load rotor system includes: a piston engine unit, a gas turbine unit, a main drive shaft, and a rotor (20); The main drive shaft includes a central inner tube (18) and an outer bypass pipe (19). The rotor (20) has an air passage inside, and the outer bypass pipe (19) is connected to the air passage inside the rotor (20). The piston engine unit is mechanically connected to the central inner tube (18), and the outlet of the piston engine unit is connected to the outer bypass pipe (19). The gas turbine unit's outlet is connected to the outer bypass pipe (19). The gas turbine unit has a compressor outlet, which is connected to the piston engine unit's inlet. The composite drive method for the high-load rotor system includes the following steps: Step S1: After receiving the start command, the starter (7) of the control unit drives the gas turbine unit to work. The gas output from the gas turbine is guided and ejected from the rotor nozzle (21) at the end of the rotor (20), so that the rotor starts to rotate. Step S2: When the gas turbine speed of the gas turbine unit reaches the self-sustaining speed, the gas turbine provides gas to the piston (1) of the piston engine unit, drives the piston (1) to ignite and run, and the mechanical torque output by the piston (1) is transmitted to the rotor (20) through the main drive shaft, and the gas output by the piston (1) is guided out from the rotor nozzle (21). Step S3: The control unit monitors the rotor speed in real time and adjusts the engagement degree of the clutch (3) of the piston engine unit according to the rotor speed. When the rotor speed reaches the preset working speed, the clutch (3) is fully engaged to complete the start-up of the large load rotor system.

2. The composite drive method for a large-load rotor system according to claim 1, characterized in that: The piston engine unit includes a piston engine (1), a piston engine crankshaft (2), a clutch (3), and a commutator (4); The piston machine (1) is a piston engine. The output end of the piston machine (1) is the piston machine crankshaft (2). The piston machine crankshaft (2) is connected to one end of the clutch (3). The other end of the clutch (3) is connected to the drive end of the commutator (4) through a rotating shaft. The driven end of the commutator (4) is connected to the main drive shaft. The main drive shaft is connected to the rotor (20). The gas turbine unit includes a compressor (8), a combustion chamber (9), and a turbine (10), which are connected in sequence. The central inner tube (18) and the outer bypass pipe (19) are connected. The central inner tube (18) is used for transmission, and the outer bypass pipe (19) can introduce gas into the internal air passage of the rotor (20). The rotor (20) is provided with a rotor nozzle (21) at the end; the gas in the rotor (20) air passage is ejected through the rotor nozzle (21) to generate torque that drives the rotor to rotate.

3. The composite drive method for a large-load rotor system according to claim 2, characterized in that: The high-load rotor system also includes a gas distribution unit; the gas distribution unit includes: compressor sump (16), piston engine inlet (6), piston engine exhaust (5), gas turbine sump (11), gas turbine sump (15) and gas turbine exhaust (14); The compressor outlet of the compressor (8) is connected to the inlet of the piston machine (1) via the compressor intake duct (16), the first solenoid valve (17) and the piston machine intake duct (6) in sequence; the outlet of the piston machine (1) is connected to the outer bypass pipe (19) via the piston machine exhaust duct (5) and is connected to the outer bypass pipe (19); the gas turbine outlet is connected to the outer bypass pipe (19) via the gas turbine intake duct (11), the second solenoid valve (12) and the gas turbine intake duct (15) in sequence; the gas turbine outlet is connected to the gas turbine exhaust duct (14) via the gas turbine intake duct (11) and the third solenoid valve (13) in sequence.

4. The composite drive method for a large-load rotor system according to claim 3, characterized in that: The high-load rotor system also includes a control unit; the control unit includes: a starter (7), a first solenoid valve (17), a second solenoid valve (12) and a third solenoid valve (13); the starter (7) is connected to the gas turbine unit and is used to drive the gas turbine unit to work; the first solenoid valve (17), the second solenoid valve (12) and the third solenoid valve (13) are all used to control the opening and closing of the gas path.

5. The composite drive method for a large-load rotor system according to any one of claims 1-4, characterized in that: In step S1, when the starter (7) of the control unit drives the gas turbine unit to work, the control unit controls the first solenoid valve (17) to remain closed, so that all the gas from the compressor (8) enters the combustion chamber (9) to burn and do work. The specific steps of guiding the gas output from the gas turbine to be ejected from the rotor nozzle (21) include: the control unit controls the second solenoid valve (12) to remain open; the gas output from the gas turbine enters the outer bypass pipe (19) of the main drive shaft through the gas turbine gas passage (11) and the second solenoid valve (12), and is finally ejected from the rotor nozzle (21), generating the initial tip jet torque, causing the rotor to start rotating slowly.

6. The composite drive method for a large-load rotor system according to claim 5, characterized in that: In step S2, the step of the gas turbine providing gas to the piston machine (1) specifically includes: the control unit opens the first solenoid valve (17), and the gas generated by the compressor (8) enters the piston machine (1) through the compressor intake channel (16), the first solenoid valve (17) and the piston machine intake channel (6) in sequence.

7. The composite drive method for a large-load rotor system according to claim 6, characterized in that: In step S2, the step of transmitting the mechanical torque output by the piston machine (1) to the rotor through the main drive shaft specifically includes: the mechanical torque output by the piston crankshaft (2) of the piston machine (1) passes through the clutch (3), commutator (4) and main drive shaft in sequence to drive the rotor (20) to rotate.

8. The composite drive method for a large-load rotor system according to claim 7, characterized in that: In step S2, the step of guiding the gas output by the piston machine (1) to be ejected from the rotor nozzle (21) specifically includes: the gas is discharged from the outlet of the piston machine (1), the gas enters the outer bypass pipe (19) through the piston machine exhaust passage (5), and finally is ejected from the rotor nozzle (21).

9. The composite drive method for a large-load rotor system according to claim 8, characterized in that: In step S3, the step of adjusting the engagement degree of the clutch (3) according to the rotor speed specifically includes: Adjust the engagement degree of the clutch (3) so that the engagement degree of the clutch (3) is positively correlated with the rotor speed.

10. The composite drive method for a large-load rotor system according to claim 9, characterized in that: In step S3, during the process of adjusting the engagement degree of the clutch (3), the control unit adjusts the opening degree of the second solenoid valve (12) and the third solenoid valve (13) according to the rotor speed feedback.

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