A gas pipeline with voltage stabilizing and intelligent temperature control functions and a supporting device thereof

Abstract

This invention discloses a gas pipeline and its supporting device with pressure stabilization and intelligent temperature control functions, belonging to the field of gas transportation. The gas pipeline includes a diffuser, a cylindrical pressure stabilizing chamber, an induced draft assembly, and an exhaust assembly connected in sequence. The diffuser adopts a conical design with a specific expansion angle to decelerate and pressurize the gas; the pressure stabilizing chamber buffers sudden pressure changes; the induced draft assembly has a guide plate inside the bend to optimize the flow field and reduce flow losses; the exhaust assembly outlet has an adjustable vent valve to prevent gas backflow. Furthermore, the gas temperature can be precisely controlled by a centrifugal atomizing nozzle located in the diffuser, and the pipeline connection uses flanges with sinus grooves to accommodate different assembly angles. This invention can significantly improve the stability of gas pressure and temperature, reduce flow losses, adapt to the complex working conditions of ground tests of tip-jet hybrid propulsion systems, and ensure test safety and data reliability.

Description

Technical Field

[0001] This invention relates to the field of pressure-stabilized gas pipelines, and more particularly to a gas pipeline and its support device that have pressure stabilization and intelligent temperature control functions. Background Technology

[0002] This invention addresses the gas delivery requirements of a tip-jet hybrid propulsion system, focusing on the technical challenges of the combined pipeline system during the ground testing phase. In a tip-jet hybrid propulsion system, the gas turbine subsystem is one of the core power sources, continuously outputting high-temperature, high-pressure gas during operation. This gas needs to be delivered to the jet rotor subsystem via a combined pipeline system to drive the rotor. However, existing combined pipeline systems have the following key technical deficiencies when adapted to this hybrid propulsion system: 1) Insufficient diffusion and pressure stabilization capabilities can easily lead to system failures. The existing combined pipeline lacks a dedicated high-efficiency diffusion structure. After the high-speed gas discharged from the gas turbine directly enters the pipeline, it is difficult to achieve effective deceleration and pressurization, resulting in unstable gas parameters (pressure and flow rate) at the jet rotor inlet. At the same time, no targeted pressure stabilization and buffer structure is set up. When the gas turbine set speed is adjusted, the gas pressure and temperature in the pipeline are prone to sudden changes, causing discontinuous gas flow distribution between the rotors of the jet rotor subsystem, which in turn causes rotor vibration, affecting the safety of the test and the accuracy of the data.

[0003] 2) Backflow at the tail of the gas turbine is prone to occur during the rotor start-up phase. Because the gas turbine requires a small gas flow rate at low speed, while the output flow rate of the gas turbine is relatively fixed, the existing pipeline is not designed with an adjustable exhaust diversion structure. Excess gas cannot be discharged in time and is prone to backflow at the tail of the gas turbine. This not only reduces the working efficiency of the gas turbine, but may also cause the gas turbine to overheat or degrade in performance, hindering the smooth start-up of the rotor.

[0004] 3) The pipeline has large flow losses and low gas transmission efficiency. The bends in the combined pipeline are the key areas of airflow disturbance. The existing pipeline has not taken targeted flow field optimization measures. When the gas flows through the bends, flow separation is likely to occur, resulting in a large amount of flow loss and reducing the energy utilization rate of the gas. At the same time, the flow field disturbance may further aggravate the rotor speed fluctuation.

[0005] 4) Poor compatibility of pipeline installation and difficulty in ensuring assembly accuracy. Ground tests of the composite power system require frequent adjustments to the docking angle between the pipeline and the rotor and gas turbine. The existing pipeline segment connection uses ordinary flanges without angle adjustment structure, which makes it difficult to adapt to the installation requirements under different test conditions. Forced assembly can easily lead to pipeline deformation or interface sealing failure, increasing the risk of gas leakage. Summary of the Invention

[0006] In view of the above problems, the present invention provides a gas pipeline and its support device with pressure stabilization and intelligent temperature control functions, which can stably control the flow rate, pressure and temperature of the gas output from the gas turbine, and can reduce flow losses.

[0007] This invention provides a gas pipeline with pressure stabilization and intelligent temperature control functions, comprising: A diffuser tube, wherein the diffuser tube is a conical tube and its inlet end is used to connect to a gas turbine; The pressure stabilizing chamber has its inlet end connected to the outlet end of the diffuser tube; The bleed air assembly, whose inlet end is connected to the first outlet of the pressure stabilizing chamber, is used to guide the gas to the jet rotor; The exhaust assembly has its inlet end connected to the second outlet of the pressure stabilizing chamber, and its outlet end is equipped with an adjustable vent valve. The air intake assembly includes at least one bend, within which a flow guide structure is provided for suppressing flow separation.

[0008] Optionally, the expansion angle of the diffuser is 4° to 8°, and it includes a front section, a middle section and a rear section of the diffuser in sequence along the airflow direction.

[0009] Optionally, it also includes a cooling system assembly, which includes a water tank, a water supply pipe, a flow control valve, and a centrifugal atomizing nozzle; the centrifugal atomizing nozzle is connected to the middle section of the diffuser pipe and is connected to the water tank through the water supply pipe and the flow control valve.

[0010] Optionally, the outlet of the pressure stabilizing chamber adopts a multi-outlet diversion design, with one outlet connected to the bleed air assembly and the other connected to the exhaust assembly.

[0011] Optionally, a guide vane is provided inside the bend of the air intake assembly. Since the air intake assembly contains two 45° bends, there is a large pressure loss. The guide vane reduces the pressure loss at the bend by restricting the flow and avoids uneven airflow distribution.

[0012] Optionally, the vent valve is a steplessly adjustable disc valve mechanism, which adjusts the flow area of ​​the exhaust assembly by changing the valve disc opening.

[0013] Optionally, the connection between each pipeline section adopts a high-temperature resistant flange, which has a sinus-shaped groove in the circumference for adjusting the installation angle and is connected by high-temperature resistant bolts.

[0014] Optionally, the outlet end of the bleed air assembly is provided with an interface flange for connecting the jet rotor. An adjustment shim can be installed inside the interface flange to control the flow area of ​​the rotor inlet.

[0015] On the other hand, the present invention also discloses a support device for the aforementioned gas pipeline, including a pipeline support frame, a diffuser pipe support, and a pressure stabilizing chamber support. The pipeline support frame is used to fix the diffuser pipe support and the pressure stabilizing chamber support; the diffuser pipe support and the pressure stabilizing chamber support are used to support the diffuser pipe and the pressure stabilizing chamber, respectively.

[0016] Compared with the prior art, the present invention has at least the following beneficial effects: 1. The diffuser of the gas pipeline in this invention is based on core parameters such as the gas turbine outlet velocity and total temperature. Through dimensionless velocity coefficient, dense flow function calculation, and CFD simulation verification, a 7° expansion angle and a three-section conical expansion structure are determined. This allows for the continuous deceleration and pressurization of the high-speed subsonic gas discharged from the gas turbine. While reducing airflow losses, it ensures the diffusion effect of the pipeline and significantly improves the stability of gas parameters. Combined with the pressure buffering effect of the cylindrical pressure stabilizing chamber, it can quickly balance the pressure and temperature changes caused by the adjustment of the gas turbine speed, ensure the continuous distribution of gas flow between the rotors, completely eliminate rotor vibration problems, and ensure the accuracy of ground test data and the safety of the test process.

[0017] 2. The gas pipeline of the present invention has three water spray holes arranged at 120° intervals in the middle section of the diffuser, which, together with the independently controlled flow valve and centrifugal atomizing nozzle, can achieve precise control of gas temperature by adjusting the cooling water flow rate, and adapt to the gas temperature requirements under different test conditions.

[0018] 3. The cylindrical pressure stabilizing chamber of the gas pipeline of the present invention can buffer the sudden changes in pressure and temperature caused by changes in the speed of the gas turbine, balance the gas flow in the pipeline, ensure the continuity of flow distribution between the rotors of the jet rotor subsystem, completely avoid the problem of rotor vibration, and ensure the reliability of test data.

[0019] 4. In the low-speed start-up phase of the rotor, the gas pipeline of the present invention discharges excess gas by increasing the opening of the disc valve, thus preventing gas from accumulating and flowing back at the tail of the gas turbine; as the rotor speed increases, the opening of the disc valve is gradually reduced to guide the gas flow smoothly to the bleed pipe, thereby achieving a smooth transition of the rotor from start-up to stable operation.

[0020] 5. The gas pipeline compensator of the present invention can absorb the thermal deformation during pipeline operation in real time, avoiding stress concentration in the pipeline; a guide plate is set at the center of the bend of the gas pipeline, and through flow field optimization design (matching the gas flow characteristics), the flow separation phenomenon of gas flowing through the bend can be effectively suppressed, significantly reducing flow loss, improving the gas delivery efficiency in the pipeline, reducing pipeline flow loss, improving gas energy utilization, ensuring that more gas energy is used to drive the rotor, and reducing energy waste.

[0021] 6. The gas pipeline of this invention uses high-temperature resistant bolted flanges (flange sealing uses fireproof sealant) at the joint pipeline section, which further reduces the risk of gas leakage and ensures long-term stable operation of the system; and the flange has a reserved sinus groove, which can flexibly adjust the pipeline installation angle according to the test assembly requirements, adapt to the docking requirements of gas turbine, rotor and pipeline under different working conditions, and eliminate the need to design pipelines separately for different test objects, which significantly reduces the investment and maintenance costs of test equipment.

[0022] 7. Adjustable shims can be installed inside the interface flange between the gas inlet pipe and the rotor inlet of the gas pipeline of the present invention. By replacing shims of different thicknesses, the rotor inlet area can be precisely controlled, the rotor operating parameters can be flexibly adjusted, and the adaptability of the system to different test objects can be improved.

[0023] 8. The integrated pipeline system of the present invention integrates pressure stabilization, flow diversion, flow field optimization and installation adjustment functions. It can stably control the pressure, flow rate and flow state of the gas output from the gas turbine, providing stable gas supply conditions for ground tests of the tip jet hybrid power system. At the same time, through high-temperature resistant structure and sealing design, it reduces the risk of gas leakage and ensures test safety. Attached Figure Description

[0024] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of the invention.

[0025] Figure 1 This is an overall schematic diagram of the gas pipeline and its supporting device of the present invention; Figure 2 This is a schematic diagram of the gas pipeline of the present invention; Figure 3 This is a schematic diagram of the internal structure of the air outlet section of the present invention; Figure 4 This is a schematic diagram of the pipeline support device and cooling system of the present invention; Figure 5 This is a schematic diagram of the piston-gas turbine combined power system provided by the present invention; Figure 6 The control system logic diagram provided for this invention; Figure 7 Flowcharts of the four mode control methods provided by this invention; Figure 8 This is a schematic diagram of the exhaust flow regulating valve based on flow equivalent of the present invention; Figure 9 This is a schematic diagram illustrating the principle of the regulating valve of the present invention applied to a gas turbine-jet rotor test system.

[0026] Explanation of reference numerals in the attached figures: 1-Diffuser, 11-Diffuser front section, 12-Diffuser middle section, 13-Diffuser end section, 2-Pressure stabilizing chamber, 3-Bleed air assembly, 31-Bleed air inlet section, 32-Bleed air compensator, 33-Bleed air transition section, 34-Bleed air outlet section, 4-Exhaust assembly, 41-Exhaust pipe inlet section, 42-Exhaust pipe compensator, 43-Exhaust pipe turning section, 44-Exhaust pipe body, 45-Break air 5-Valve, 5-Cooling system assembly, 51-Water tank, 52-Water supply pipe, 53-Flow control valve, 54-Centrifugal atomizing nozzle, 6-Pipeline support device, 61-Pipeline support frame, 62-Diffuser tube support, 63-Pressure stabilizing chamber support; 701 is the valve shaft; 711, 712, 714, and 715 are all sealing ring grooves; 713 is the fixing threaded hole for the valve shaft and butterfly plate; 702 is the upper support for the regulating valve; 721 is the motor mounting hole; 722 is the threaded hole connecting the upper support and the valve body; 703 is the valve body; 731 is the threaded hole connecting the regulating valve and the gas turbine bleed air pipe; 732 is the valve body expansion threaded hole; 704 is the butterfly plate; 741 is the vent hole; 742 is the threaded hole connecting the butterfly plate and the valve shaft; 705 is the upper floating bearing; 706 is the lower floating bearing; 707 is the lower cover plate; 801 is the piston engine; 802 is the clutch; 803 is the steering gear; 804 is the rotor system; 805 is the clutch stepper motor; 806 is the fuel supply system; 807 is the fuel supply system stepper motor; 808 is the gas turbine; 809 is the compressor bleed air pipe; 810 is the gas turbine bleed air pipe; 811 is the starter; 812 is the exhaust flow regulating valve; 813 is the fuel flow regulating valve; 814 is the compressor bleed air pipe solenoid valve. Detailed Implementation

[0027] 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.

[0028] A specific embodiment of the present invention, such as Figure 1-4 The present invention discloses a gas pipeline with pressure stabilization and intelligent temperature control functions, including a diffuser 1, a pressure stabilizing chamber 2, a bleed gas assembly 3 and an exhaust gas assembly 4; the outlet of the diffuser 1 is connected to one end of the pressure stabilizing chamber 2; the bleed gas assembly 3 and the exhaust gas assembly 4 are located at the other end of the pressure stabilizing chamber 2.

[0029] Furthermore, diffuser 1 is an expanding conical pipe structure. The inlet of diffuser 1 is connected to the gas turbine, and the inlet area of ​​diffuser 1 is the same as that of the gas turbine. The outlet area of ​​diffuser 1 is... The expression is: (1) (2) (3) in, The total pressure recovery coefficient of the diffuser is . For diffuser flow rate, It is the total temperature at the diffuser outlet. The gas constant is The dimensionless velocity coefficient at the diffuser outlet. The dense flow function at the diffuser outlet. This is the total outlet pressure of the gas turbine (i.e., the total inlet pressure of the diffuser). The adiabatic index of the gas. This is the outlet pressure of the diffuser (determined based on gas supply demand).

[0030] Furthermore, the diffuser 1 includes a front section 11, a middle section 12, and a rear section 13. In the middle section 12, there are three water spray holes spaced 120° apart, which are connected to centrifugal atomizing nozzles 54. The centrifugal atomizing nozzles 54 are connected to the water tank 51 below through a water supply pipe 52. Three control valves 53 are provided at the connection between the water tank outlet and the water supply pipe, which can control the cooling water flow rate of the three water supply positions respectively, and indirectly control the temperature of the high-temperature gas by controlling the water flow rate.

[0031] Furthermore, the cooling system assembly 5 includes a water tank 51, a water supply pipe 52, a flow control valve 53, and a centrifugal atomizing nozzle 54. The water tank 51 has an outlet at the bottom side, which is connected to the water supply pipe 52. The water supply pipe 52 is divided into three branch pipes, each connected by threads. Each branch pipe corresponds to a spray hole in the second section 12 of the diffuser pipe. The flow control valve 53 is installed on the branch pipe. The end of each branch pipe is connected to the centrifugal atomizing nozzle 54 by threads. After tightening, the nozzle is sealed to ensure no leakage. During the test, the opening of the valve 53 is adjusted according to the temperature of the gas entering the rotor to control the cooling water flow and achieve precise control of the gas temperature.

[0032] Furthermore, the pressure stabilizing chamber 2 is a cylindrical cavity with the same cross-sectional area as the outlet area of ​​the diffuser pipe 1, which can form an effective pressure buffer space. When the gas turbine set speed adjustment causes sudden changes in pressure and temperature, the pressure stabilizing chamber can quickly balance the gas flow in the pipeline, avoid interruption of flow distribution between the rotors of the jet rotor subsystem, and eliminate the risk of rotor vibration.

[0033] Furthermore, the outlet of the pressure stabilizing chamber adopts an upper and lower split design, with the upper part being the bleed air assembly 3 and the lower part being the exhaust assembly 4. The end of the bleed air assembly 3 and the connecting flange of the rotor inlet are reserved with a gap. By adding adjusting shims of different thicknesses, the flow area of ​​the rotor inlet can be precisely controlled to flexibly adapt to the working parameter requirements of different rotor specifications. The outlet end of the exhaust assembly 4 is equipped with a steplessly adjustable disc valve mechanism. By rotating the valve disc of the disc valve mechanism, the flow area can be changed (adjustment range 0%-100%). During the low-speed start-up phase of the rotor, the opening is increased to discharge excess gas and avoid backflow at the tail of the gas turbine. As the rotor speed increases, the opening is gradually reduced to smoothly guide the gas flow to the bleed air pipe, achieving a smooth transition from start-up to stable operation.

[0034] Furthermore, the bleed air assembly 3 includes a bleed air inlet section 31, a bleed air compensator 32, a bleed air transition section 33, and a bleed air outlet 34. The bleed air assembly 3 is divided into two flow paths by the inner pipe, which supply air to the two-stage jet rotors respectively. A guide plate 35 is welded and fixed in the bend of the bleed air assembly 3. The thickness and cross angle of the guide plate are optimized by flow field simulation, which can divide the gas flow in the bend into a uniform flow stream, effectively suppress the flow separation and vortex generated when the gas flows through the bend, significantly reduce local flow loss, and improve the gas energy utilization rate.

[0035] Furthermore, the exhaust assembly 4 includes an exhaust pipe inlet section 41, an exhaust pipe compensator 42, an exhaust pipe steering section 43, an exhaust pipe body 44, and a bleed valve 45.

[0036] Furthermore, the various pipe sections of this invention are connected using high-temperature resistant alloy flanges. The flanges have uniformly spaced grooves around their circumference (the groove width matches the bolt diameter, and the groove depth meets the angle adjustment requirements). Combined with high-temperature resistant bolts, the pipe installation angle can be finely adjusted according to the test assembly requirements, ensuring precise connection between the gas turbine, pipes, and rotor, and avoiding pipe deformation or interface sealing failure caused by forced assembly. The entire system is fixed to the test bench by a pipe support frame, the height of which is finely adjustable, further ensuring the horizontality and coaxiality of the pipe installation.

[0037] Furthermore, the vent valve 45 is located at the outlet of the exhaust assembly 4 and is used for venting the pipeline before the test and for pressure control during the test. Together with the high-temperature resistant sealing design of each component (the flange seal uses fireproof sealant), it forms a safe and reliable gas supply closed loop to ensure the stable conduct of the ground test.

[0038] Furthermore, the expansion angle of diffuser 1 (the angle formed by the centerline and edgeline of the diffuser) is determined based on the exhaust parameters of the gas turbine and the intake requirements of the rotor. With the inlet and outlet areas fixed, the size of the expansion angle determines the length of diffuser 1. If the expansion angle is too small, the diffuser 1 will be too long. Since all three sections of the tube are rolled, excessive length will significantly increase the processing difficulty, potentially causing pipe deviation and failing to meet the limitations of the test conditions. On the other hand, if the expansion angle is too large, it will cause airflow separation, resulting in a large pressure loss. Through simulation verification of diffusers with different expansion angles, the expansion angle is set to 7°. At this time, diffuser 1 can continuously decelerate and pressurize the high-speed gas discharged from the gas turbine. While ensuring that the airflow does not separate, it also prevents the pipe from being too long, meeting the test conditions and process limitations, effectively improving the pressure and velocity stability of the gas at the inlet of the jet rotor, and meeting the gas supply pressure requirements of the jet rotor.

[0039] Furthermore, the total length of the diffuser 1's front section 11, middle section 12, and final section 13 is 1790 mm; among which, the front section 11 is 562 mm long, with an inlet inner diameter of 160 mm and an outlet inner diameter of 300 mm; the middle section 12 is 613 mm long, with an outlet inner diameter of 450 mm; and the final section 13 is 615 mm long, with an outlet inner diameter of 600 mm. The three sections are connected by flanges, with a smooth transition in the internal flow channel to reduce airflow disturbance. The inlet of the diffuser 1 is connected to the gas turbine exhaust port through a flange. The three sections of the pipeline are connected sequentially through flanges, and bolts are inserted into the sinus groove for initial fixation. After adjusting the coaxiality of each section, the bolts are tightened. The flanges are sealed with fire-resistant sealant, and the bolts are high-temperature resistant alloy bolts.

[0040] Furthermore, the pressure stabilizing chamber 2 is a cylindrical cavity with an inner diameter of 600mm and a length of 600mm. Its cross-sectional area is the same as that of the diffuser outlet area, which can provide sufficient buffer space. Flanges are welded at both ends of the pressure stabilizing chamber. The inlet flange is connected to the outlet flange of the last section 13 of the diffuser. The upper outlet flange is welded and fixed to the inlet section 31 of the bleed air pipe. The lower outlet flange is connected to the flange of the inlet section 41 of the exhaust pipe.

[0041] Furthermore, the total length of the air intake section 31, air intake compensator 32, air intake transition section 33, and air intake outlet section 34 of the air intake pipe 3 is 1730mm, and the inner diameter is 200mm. The length of the air intake section 31 is 450mm, with a flange welded to one end, which is connected to the upper flange of the outlet of the pressure stabilizing chamber 2. The other end is connected to the air intake compensator 32 through a flange. The air intake compensator 32 is connected to the air intake transition section 34 through a flange. The air intake transition section 34 and the air intake outlet section 33 are 45° bends. The weld of the guide plate is ground smooth, and a circular tube is provided inside to divide the flow path into two flow paths, inner and outer, which supply air to the two-stage jet rotors respectively. The gap between the air intake outlet section 33 and the rotor inlet flange is reserved, and the flow path area can be precisely controlled by replacing the high-temperature resistant metal adjusting shim.

[0042] Furthermore, the total length of the exhaust pipe 4, including the exhaust pipe inlet section 41, exhaust pipe compensator 42, exhaust pipe turning section 43, exhaust pipe body 44, and vent valve 45, is 4840mm, and the inner diameter is 166mm. The exhaust pipe inlet section 41 is 400mm long, with a welded flange at one end, which connects to the lower flange at the outlet of the pressure stabilizing chamber 2, and the other end is connected to the flange of the compensator 42. The exhaust pipe compensator 42 is a bellows compensator, which is connected to the turning section 43 via a flange. The turning section 43 is connected to the exhaust pipe body 44 via a flange. A butterfly valve is installed near the outlet of the exhaust pipe body 44 via a flange to adjust the exhaust flow rate. By controlling the exhaust flow rate, the stability of the gas supply pressure is ensured.

[0043] When the gas turbine starts up, the high-temperature and high-pressure gas is continuously decelerated and pressurized through the diffuser pipe 1. The cooling system valve 53 is adjusted according to the temperature of the gas entering the rotor to spray water into the diffuser pipe to control the temperature. The gas enters the pressure stabilizing chamber 2 for buffering and balancing pressure fluctuations. At this time, the rotor is in a low-speed state and the required gas flow is small. The control system opens the butterfly valve to a certain degree, and the excess gas is quickly discharged through the exhaust pipe 4 to avoid backflow at the tail of the gas turbine. At the same time, the two flow paths of the bleed pipe 3 deliver stable gas to the two-stage rotor, driving the rotor to gradually accelerate. During the stable operation phase of the rotor, when the rotor speed reaches the target stable speed, the control system gradually reduces the butterfly valve opening to match the gas flow rate with the rotor demand. The gas flow is divided into uniform streams by the guide plates in the bleed pipe transition section 33 and the bleed pipe outlet section 34, significantly suppressing flow separation at bends and reducing flow losses. The pressure stabilizing chamber 2 continuously buffers gas pressure fluctuations, ensuring uniform flow distribution between the two rotor stages. The bleed pipe compensator 32 and the exhaust pipe compensator 42 absorb thermal deformation in real time, preventing stress concentration in the pipeline, and the support device maintains the pipeline's horizontal stability. If switching to another rotor test condition is required, the gas turbine is shut down, and after the pipeline temperature drops to room temperature, the corresponding thickness of the adjusting shim is replaced, and the above test procedure is repeated.

[0044] Through the above-mentioned refined optimization of the structural design, assembly process and operation flow of gas pipelines and their supporting devices with pressure stabilization and intelligent temperature control functions, the working conditions of gas transmission for ground testing of the tip jet hybrid propulsion system can be fully adapted. Compared to traditional combined gas pipeline systems, the specific implementation of this invention significantly improves the high-temperature resistance, sealing performance, and assembly precision of the pipeline, eliminating the risk of gas leakage from a hardware perspective. The deceleration and pressurization design of the three-section diffuser and the flow field optimization structure of the guide plate at the bend of the intake pipe, combined with the pressure buffering effect of the pressure stabilizing chamber, effectively reduce pipeline flow losses, stabilize the pressure and velocity parameters of the inlet gas of the jet rotor, and avoid rotor vibration problems. The angle fine-tuning design of the sinus groove flange, the adaptation scheme of multi-specification adjustment shims, and the height-adjustable pipeline support frame greatly improve the system's adaptability to rotor tests under different operating conditions, eliminating the need for separate pipeline design and reducing the investment and maintenance costs of test equipment. The precise temperature control of the cooling system, the heat deformation absorption of the corrugated compensator, and the control of gas backflow by the butterfly valve further ensure the reliability and safety of the system throughout the entire process from startup to stable operation.

[0045] Another embodiment of the present invention discloses a support device for supporting the aforementioned gas pipeline with pressure stabilization and intelligent temperature control functions, including a diffuser pipe support 61, a pressure stabilizing chamber support 62, and a pipeline support frame 63; both the diffuser pipe support 61 and the pressure stabilizing chamber support 62 are "L"-shaped brackets, with the bottom fixed to the test bench by expansion bolts, and the top fixed with a high-temperature resistant clamp, which fits against the outer wall.

[0046] Thirdly, see Figure 5-7 It also discloses a comprehensive adjustment and control method for a piston-gas engine hybrid power system, such as... Figure 5 As shown, the composite power system includes a piston engine 801, a rotor system 804, a gas turbine 808, a compressor bleed air duct 809, and a control system. The output end of the piston engine 801 provides rotational power to the rotor shaft of the rotor system 804; the rotor of the rotor system 804 has an air bleed pipe, and the gas generated by the gas turbine 808 enters the air bleed pipe of the rotor and is ejected from the tip of the rotor to provide rotational power to the rotor; the gas turbine 808 provides high-pressure gas to the piston engine 801 through the compressor air bleed pipe 809.

[0047] The control system of the present invention includes an engine control unit (ECU), a gas turbine engine control unit, and a piston engine control unit; the engine control ECU is communicatively connected to the gas turbine ECU and the piston engine ECU; the gas turbine ECU and the piston engine ECU control the power of the gas turbine 808 and the piston engine 801, respectively.

[0048] The composite power system of the present invention further includes: Clutch 802, steering gear 803, clutch stepper motor 805, oil supply system 806, oil supply system stepper motor 807, gas turbine bleed air pipeline 810, starter 811, exhaust flow regulating valve 812, fuel flow regulating valve 813, and compressor bleed air pipeline solenoid valve 814.

[0049] Furthermore, the gas turbine bleed air duct 810 includes a diffuser 1, a pressure stabilizing chamber 2, and a bleed air assembly 3; the exhaust flow regulating valve 812 and the gas turbine bleed air duct 810 are disposed in the exhaust assembly 4; The oil supply system 806 is connected to the oil supply system stepper motor 807 and the piston motor 801 respectively; the clutch 802 is connected to the piston motor 801, the clutch stepper motor 805 and the steering gear 803 respectively, and the steering gear 803 is connected to the rotor system 804.

[0050] The piston engine ECU is communicatively connected to the oil supply system stepper motor 807 and the clutch stepper motor 805 respectively; the piston engine ECU controls the oil supply system 806 through the oil supply system stepper motor 807, thereby controlling the power of the piston engine 801; the piston engine ECU controls the tension of the clutch 802 through the clutch stepper motor 805, thereby controlling the output power of the piston engine to the rotor system 804.

[0051] The gas turbine 808 is connected to the compressor bleed air pipe 809, the gas turbine bleed air pipe 810 and the starter 811 respectively. The gas turbine 808 is equipped with a fuel flow regulating valve, the gas turbine bleed air pipe 810 is equipped with an exhaust flow regulating valve 812, and the bleed air pipe 809 is equipped with a compressor bleed air pipe solenoid valve 814.

[0052] The gas turbine ECU is communicatively connected to the exhaust flow regulating valve 812 and the fuel flow regulating valve 813. The gas turbine ECU controls the opening of the gas turbine bleed air pipe 810 via the exhaust flow regulating valve 812, thereby controlling the output power of the gas turbine 808 to the rotor system 804. The gas turbine ECU controls the power of the gas turbine via the fuel flow regulating valve 813. The compressor bleed air pipe 809 has its opening controlled by the compressor bleed air pipe solenoid valve 814.

[0053] Further, see Figure 8-9 The exhaust flow regulating component 812 includes a valve shaft 701, an upper support 702, a valve housing 703, a butterfly plate 704, an upper floating bearing 705, a lower floating bearing 706, and a lower support 707.

[0054] Furthermore, the valve housing 703 includes an annular plate one, an annular plate two, and a connecting column; the inner ring of the connecting column is cylindrical, and the outer ring is a symmetrical polygon, which is composed of multiple rectangular surfaces connected end to end in sequence; annular plate one and annular plate two are respectively disposed on the two end faces of the connecting column; annular plate one, annular plate two, and the connecting column form a hollow area for placing the butterfly plate 704 and the valve shaft 701.

[0055] Furthermore, the outer ring has a total of 8 rectangular faces; Furthermore, the upper support 702 is disposed on the connecting column of the valve body 703, and the longitudinal axis of the upper support 702 is perpendicular to the longitudinal axis of the connecting column; the upper support 702 and the connecting column are connected by bolts in the threaded hole 722, and the upper floating bearing 705 is pressed and fixed between the upper support 702 and the connecting column, and a sealing ring is placed in the sealing ring groove 712 to prevent air leakage.

[0056] Furthermore, the lower support 707 is disposed on the connecting column of the valve housing 703, and the longitudinal axis of the lower support 707 is perpendicular to the longitudinal axis of the connecting column; the lower support 707 is connected to the valve housing 703 by bolt structure, and the lower floating bearing 706 is pressed and fixed between the lower support 707 and the connecting column, and a sealing ring is placed at the sealing ring groove 714 to prevent air leakage.

[0057] Furthermore, the upper support 702 and the lower support 707 are symmetrically arranged on the plane of symmetry of the column body of the connecting column; the upper support 702 and the lower support 707 are coaxially arranged.

[0058] Furthermore, the valve shaft 701 is nested with the connecting column through the locking structure of the upper support 702 and the lower support 707.

[0059] Furthermore, the butterfly plate 704 is sleeved on the valve shaft 701 and located in the hollow area of ​​the valve body 703; the butterfly plate 704 is connected to the valve shaft 701 through bolt structures in the threaded holes 713 and 742.

[0060] Furthermore, the butterfly plate 704 is sleeved on the valve shaft 701 along the diameter direction of the valve housing 703.

[0061] Furthermore, the valve shaft 701 has sealing ring grooves 711, 712, 714, and 715, which are used to place sealing rings to prevent air leakage from the regulating valve. A square interface is reserved on the top of the valve shaft 701, which can be used to install high-precision adjustment mechanisms (such as servo controllers) or handles, expanding the application scenarios of the regulating valve.

[0062] Furthermore, the valve body 703 is manufactured using CNC machining to meet high-precision requirements. Multiple expansion threaded holes 732 are provided on the external side of the connecting column to facilitate different installation and usage needs of the control valve. Brackets or other expansion devices can be added depending on the application scenario. Furthermore, the butterfly plate 704 and the valve shaft 701 are connected through threaded holes 713 and 742. The stable bolt connection method can reduce the play during the adjustment process and improve the adjustment accuracy.

[0063] Furthermore, four vent holes 741 are provided on the butterfly plate 704. The size of the vent holes is determined based on the minimum flow rate of the gas turbine and the gas velocity within the device. The minimum flow area is determined by the ratio of the minimum flow rate of the gas turbine to the gas velocity. This flow area is the sum of the vent hole area and the area of ​​the annular airflow channel cross-section described below. This ensures that a controllable minimum vent channel exists in any position of the valve (including "fully closed"), effectively preventing the risk of a surge in back pressure and overheating caused by complete blockage of the gas turbine exhaust, and significantly improving the safety of the testing system. At the same time, the design of the vent holes can reduce the force-bearing area of ​​the airflow and also reduce the resistance when the control valve butterfly plate 704 rotates, improving the accuracy of the control valve. The outer diameter of the butterfly plate 704 is smaller than the inner diameter of the connecting column. An airflow channel is formed between the outer edge of the butterfly plate 704 and the inner side of the connecting column. When the airflow flows through the control valve, water vapor in the airflow can be condensed on the inner wall of the valve body 703 through this airflow channel, and then the condensate is blown out of the control valve by the subsequent airflow. If no external airflow channel is provided, the condensate will not be able to drain and will accumulate in the gas turbine's bleed air duct. This also reduces the risk of gas turbine overheating and decreases the rotational resistance of the regulating valve disc 704.

[0064] Furthermore, the floating bearings 705 and 706 are made of lead bronze, a material that inherently provides lubrication, eliminating the need for ball bearings or other similar structures and simplifying the control valve structure. A sealing ring is installed between the floating bearings 705 and 706 and the valve housing 703 to enhance the airtightness of the control valve.

[0065] Furthermore, it also includes a high-precision electric drive servo controller, which is used to connect to the upper square column of the valve shaft to achieve high-precision adjustment and control. The high-precision electric drive servo controller includes a displacement sensor. The servo controller drives the valve stem to rotate through a coupling or transmission mechanism, and the built-in high-resolution displacement sensor provides real-time and accurate feedback on the valve plate rotation angle.

[0066] Specifically, 1) Regarding defect one (insufficient precision) and defect three (dimensions / drive): High-precision servo drive and displacement feedback: An electric servo controller replaces the manual handle. A high-precision displacement sensor is installed on the servo controller, with an effective stroke of 10cm, precisely corresponding to the angular change of the valve plate within the critical adjustment range of 43° to 60°. Through closed-loop control of the servo system, high-resolution, precise setting and stable maintenance of the valve plate angle can be achieved, thus enabling precise setting within the small opening range (at which point...). high, (For flow rate) It can also achieve fine and stable flow rate adjustment and accurately control the expansion tank pressure to simulate the rotor inlet pressure.

[0067] Utilizing the inherent regulating characteristics of the butterfly valve: Operation is specifically selected and optimized within the small opening range of the butterfly valve. Within this range, the geometrical nonlinear characteristics of the butterfly valve (the crescent-shaped gap formed by the edge of the butterfly plate and the valve body 703) are fully utilized: minute angular changes ( This causes the effective size of the flow gap and the flow area to increase. A Significant relative changes () The extremely high flow rate (greater than that of ordinary valves) allows for highly sensitive flow regulation. The high-precision control capabilities of the servo system perfectly match this characteristic, achieving flow (equivalent) regulation with a precision far exceeding that of ordinary valves. The relationship between the flow area and rotation angle of the butterfly valve is as follows: (4) in, A The flow area refers to the cross-sectional area through which the fluid actually flows when it passes through a pipe or channel. Indicates the pipe diameter; Furthermore, the valve body vent design (anti-fully-closed structure): one or more vent holes of specific dimensions are machined on the valve body at the edge of the disc or near the valve seat. The core of this design is to ensure that the vent holes remain unobstructed even when the valve is in the "fully closed" command position (usually defined as the disc plane being perpendicular to the pipe axis, 0° opening), forming a minimum flow path that cannot be closed.

[0068] Furthermore, the area of ​​the vent hole simultaneously satisfies two contradictory requirements: (a) as small as possible while meeting other conditions: minimizing leakage to ensure that the main flow capacity is not affected at large openings and to provide the largest possible adjustment range at small openings; (b) large enough while meeting other conditions: ensuring that the minimum leakage flow through the hole is sufficient to maintain the gas turbine exhaust back pressure below the safe threshold when the valve is "fully closed", avoiding excessive turbine inlet temperature and ensuring that the gas turbine can operate stably and safely even when the valve is "fully closed" (even as a guarantee for extreme operating conditions).

[0069] Large-diameter valve body: The valve body diameter is customized according to the exhaust flow requirements of the test system, which is significantly larger than that of conventional commercially available butterfly valves, ensuring that it meets the requirements of large flow capacity and maintains low resistance characteristics at large opening.

[0070] Furthermore, such as Figure 2The regulating valve is located in the gas turbine bleed air duct of the gas turbine-jet rotor test system of the rotorcraft, and is installed at the outlet section of the gas turbine bleed air duct during operation. The high-temperature, high-pressure, high-speed gas flow from the gas turbine outlet is accelerated through the nozzle and enters the expansion tank, where it expands and accelerates again. At the expansion tank outlet, it splits into two streams. One stream enters the rotor through the jet rotor bleed air duct, expands and accelerates within the rotor's converging flow channel, and is then ejected through the nozzle at the rotor tip, providing thrust and lift to the rotor. The other stream enters the gas turbine bleed air duct, passes through the regulating valve, and is discharged into the atmosphere. By adjusting the opening of the regulating valve, the ratio of the two airflow streams can be adjusted, allowing the gas turbine to simulate the correspondence between different gas turbine exhaust pressures and rotor speeds at a constant speed. The control system calculates the required valve opening command based on the target expansion tank pressure or target rotor speed required by the test. The command is sent to the servo controller. The regulating valve is connected to the displacement sensor and the servo controller. The servo controller drives the servo motor to rotate, which in turn drives the valve stem and butterfly plate to rotate precisely to the target angle (fine adjustment within the 43°-60° range) via a coupling. The displacement sensor provides real-time, high-precision feedback on the actual valve plate angle, forming a closed-loop control to ensure angle stability. Small changes in the butterfly plate angle, due to its high sensitivity (large dA / dθ) within the 43°-60° range, precisely alter the exhaust flow area, thereby finely adjusting the flow rate and expansion tank pressure. Even under extreme commands or malfunctions, when the valve attempts to "close" beyond 43° (e.g., to the theoretical 0°), the vent hole always ensures minimal leakage, maintaining the gas turbine back pressure within a safe value and preventing overheating. Applying this embodiment on the test bench, the expansion tank pressure can be precisely controlled within a fixed range at a fixed gas turbine speed, successfully simulating inlet pressure conditions at different rotor speeds. The gas turbine operates smoothly, and no overheating alarms due to back pressure runaway occur. Compared to methods that frequently adjust the gas turbine speed, this improves experimental efficiency.

[0071] Figure 6 The control system logic diagram of the present invention is shown in the figure. The control system of the present invention specifically includes three main parts: a core control unit, a sensing system, and an actuator, which are described in detail below.

[0072] (1) Core control unit Engine Control Unit (ECU): As the core of system decision-making, it runs on real-time operating systems such as VxWorks. It is responsible for collecting global sensor data, identifying flight phases, calculating total power demand, and generating target power allocation commands and operating mode switching commands for the piston engine and gas turbine.

[0073] Gas turbine ECU: Receives instructions from the generator control ECU and is specifically responsible for the high-precision closed-loop control of the gas turbine. By adjusting the gas regulating valve and the fuel flow regulating valve, it precisely regulates the power and output of the gas turbine.

[0074] Piston engine ECU: Receives commands from the engine control ECU and is specifically responsible for the closed-loop control of the piston engine. It regulates the piston engine's speed and power by adjusting the stepper motor of the fuel supply system; and controls the engagement between the piston engine and the rotor system by adjusting the clutch stepper motor.

[0075] (2) Sensing system The gas turbine condition sensor cluster includes gas turbine pipeline pressure sensors, gas turbine speed sensors, gas turbine after-turbine temperature sensors, and gas turbine fuel consumption meters. These sensors are used to monitor the operating status of the gas turbine in real time, ensuring that it operates within a safe and efficient range.

[0076] The piston engine status sensor cluster includes a piston speed sensor, a throttle position sensor, a piston exhaust temperature sensor, a piston oil pressure sensor, and a piston oil consumption meter. This data is used to monitor the piston engine's operating condition in real time, ensuring precise control of the piston engine.

[0077] Rotor status sensor cluster: including rotor speed sensor and rotor tilt sensor, the engine control unit (ECU) controls the piston engine and gas turbine according to commands and rotor status.

[0078] (3) Implementing agency Gas turbine actuators: mainly include gas regulating valves and fuel flow regulating valves, driven by the gas turbine ECU, directly controlling the gas flow entering the rotor system and the fuel entering the gas turbine.

[0079] Piston engine actuators mainly include a stepper motor for regulating the fuel supply system and a stepper motor for the clutch. The former controls the fuel supply, while the latter manages the power on / off, together achieving piston engine power control and power coupling.

[0080] like Figure 7 As shown, the specific implementation steps of the integrated regulation and control method for the piston-gas turbine hybrid power system are as follows: Step S1: The sensors of the control system collect operating condition signals, including: rotor speed, gas turbine output power and piston engine output power; In this step, the control system of the present invention monitors the operating status of each part of the power system in real time through gas turbine status sensor cluster, piston engine status sensor cluster and rotor status sensor cluster. Specifically, it can detect the operating status such as rotor speed, gas turbine output power and piston engine output power, and generate operating condition signals, which will be used for subsequent power system adjustment in various working modes.

[0081] Step S2: After receiving the start command, the control system controls the gas turbine to start. The high-pressure gas output by the gas turbine drives the piston machine, which in turn drives the rotor system to accelerate rotation. When the rotor speed is greater than the idle speed threshold, the target power is obtained based on the total required power and the piston engine output power. The gas turbine provides power to the rotor system based on the target power, so that both the piston engine and the gas turbine drive the rotor system to rotate. The aircraft of this invention has four operating modes in different working phases: start-up mode, take-off mode, cruise mode, and maneuvering flight mode. Among them, the aircraft enters the cruise mode after starting up mode and take-off mode, and can switch between cruise mode and maneuvering flight mode.

[0082] In subsequent steps, the present invention achieves dual-mode cooperative drive by dynamically adjusting the working state, power output and cooperative logic of the piston engine and the gas turbine. The torque cooperative mode includes the starting condition, the takeoff condition and the maneuvering flight condition, and the functional decoupling mode includes the cruise condition.

[0083] In this step, the invention first describes the starting condition. Under the starting condition, the hybrid power system performs initial start-up and idle coordination.

[0084] (1) Initial startup The ECU commands the starter motor to drive the gas turbine to rotate and ignite until it reaches its self-sustaining speed.

[0085] After the gas turbine stabilizes, the ECU opens the solenoid valve of the compressor bleed gas pipeline, introducing high-pressure gas into the piston engine and driving the piston engine to start.

[0086] The piston engine ECU commands the clutch stepper motor to gradually tighten the clutch, and the piston engine begins to drive the rotor system to accelerate rotation independently.

[0087] In some embodiments, the piston engine independently calculates and outputs power based on a preset optimal fuel economy curve, and drives the rotor independently.

[0088] (2) Slow train coordination When the rotor speed sensor detects that the rotor speed exceeds the preset idle speed threshold, the engine control ECU controls the exhaust flow regulating valve to open, and the gas turbine begins to output power.

[0089] In this step, the present invention uses a dual-modal cooperative driving dynamics model to determine the target power.

[0090] The expression for the dual-modal cooperative driving dynamics model is: (5) in, This represents the moment of inertia of the rotor system. Indicates the rotor speed. and They represent Rotation speed at all times The corresponding output torque of piston engines and gas engines, , These represent transmission efficiency, respectively. , Indicates the clutch transmission coefficient. Indicates rotational speed The corresponding rotor aerodynamic load torque.

[0091] The piston machine output torque is calculated based on the dual-modal cooperative drive dynamics model, and the piston machine output power is determined from the piston machine output torque; the target power is obtained by subtracting the piston machine output power from the total required power.

[0092] The gas turbine intervenes to drive the rotor system based on the target power, so that both the piston engine and the gas turbine drive the rotor system to rotate.

[0093] In some embodiments, a load-predictive torque feedforward control algorithm can predict load changes based on rotor acceleration and feedforward shape the power engagement curve of the gas turbine to ensure that the dual power sources achieve shock-free torque coupling and smoothly transition to the operating speed.

[0094] Step S3: The piston engine maintains maximum output power, and the rotor aerodynamic load torque estimate is obtained in real time based on the extended Kalman filter. The output power of the gas turbine is adjusted based on the rotor aerodynamic load torque estimate. In this step, the present invention completes the system drive for takeoff, enabling the aircraft to take off vertically.

[0095] The piston engine maintains maximum output power as the power base. The engine control ECU comprehensively collects data such as torque coefficient and rotor speed, and obtains the rotor aerodynamic load torque estimate in real time based on extended Kalman filter. Based on the rotor aerodynamic load torque estimate, the output power of the gas turbine is adjusted to dynamically adjust the power in order to pursue maximum net lift.

[0096] The expression for real-time estimation of rotor aerodynamic torque using extended Kalman filtering is as follows: (6) in, This represents the estimated value of the rotor aerodynamic load torque. Indicates air density, Indicates the torque coefficient. R Indicates the rotor radius.

[0097] The rotor aerodynamic torque estimate is applied to the dual-mode cooperative drive dynamics model to adjust the gas turbine output power in real time.

[0098] Through the above steps, the torque feedforward control algorithm based on load prediction in this invention proactively compensates for power demand, greatly reducing the lag in lift control.

[0099] In some embodiments, this step further includes a temperature protection strategy. Specifically, the control system acquires the exhaust temperature, and when the exhaust temperature... At this time, the power reduction mode is triggered, reducing the power of the gas turbine.

[0100] Step S4: Determine the system energy change based on the gas turbine output power; determine whether the subsequent operating mode is cruise or maneuvering flight; If the operating mode is cruise, the piston engine is disengaged from the rotor system, including: Based on the energy change of the system, the clutch between the piston engine and the rotor system is completely disengaged; Multi-objective optimization is performed based on the output power of the gas turbine and the output power of the piston engine to obtain the optimized output power of the gas turbine. If the operating mode is maneuvering flight, then the piston engine is controlled to resume drive of the rotor system, including: The clutch between the piston engine and the rotor system is tightened based on the energy change of the system.

[0101] In this step, the aircraft completes vertical takeoff and enters either cruise or maneuvering flight mode, and can switch between cruise and maneuvering flight modes.

[0102] In this step, the present invention first establishes a transition state energy buffer model, the expression of which is: (7) in, Indicates the change in system energy. , They represent Time and Rotor speed at any given moment This indicates the output power of the gas turbine. , These represent the start and end times, respectively.

[0103] Based on the above model, this invention calculates the system energy change, which is then used for subsequent clutch control.

[0104] The system determines whether the subsequent operating mode is cruise or maneuvering flight, and performs different processing based on whether it is cruise or maneuvering flight, as detailed below.

[0105] (1) Cruise operating condition In this phase, the system switches to a functionally decoupled mode to achieve optimal global energy efficiency.

[0106] As the piston engine gradually reduces its power output, the clutch automatically disconnects the power connection between the piston engine and the rotor, directing the piston engine power to the power generation system, completing the mode transition. The piston engine enters a high-efficiency power generation mode, operating at the globally optimal fuel consumption point to supply power to the onboard systems.

[0107] In some embodiments, the globally optimal fuel consumption point can be obtained through experimentation.

[0108] Multi-objective optimization is performed based on the output power of the gas turbine and the output power of the piston engine to obtain the optimized output power of the gas turbine. This invention dynamically adjusts the torque output of each component based on different operating states. The multi-objective optimization expression is as follows: (8) Where min represents minimization optimization. For the rotor reference angular velocity, This indicates the change in generator torque of the piston engine; , and These are the weighting coefficients. , These refer to the output power of the gas turbine and the piston engine, respectively.

[0109] For cruise operation, this invention adjusts... , The weighting coefficient is reduced. The weighting coefficient is increased. The weighting coefficients are adjusted to adapt to cruise conditions. In some embodiments, this can be achieved by... The weighting coefficient was adjusted from 0.6 to 0.2, making The weighting coefficient was adjusted from 0.1 to 0.7.

[0110] After the above multi-objective optimization process, the optimized gas turbine output power is obtained.

[0111] The gas turbine is controlled by the optimized gas turbine output power, so that the gas turbine focuses on maintaining lift. Its power command is also corrected by the minimum energy consumption multi-objective optimization algorithm. Under the premise of meeting the lift requirements, it is made to operate in its own high-efficiency range, and the overall system achieves the optimal cruise energy efficiency.

[0112] (2) Maneuvering flight conditions In this stage, the clutch between the piston engine and the rotor system is tightened based on the energy changes of the system.

[0113] In maneuvering flight and agile evasion missions, the energy gap is calculated using an energy buffer algorithm when... When the torque exceeds 200J, torque compensation is triggered. The stepper motor rapidly increases the fuel injection volume of the piston engine, and the piston engine recouples with the rotor through the overrunning clutch, outputting supplementary torque. The additional torque from the gas turbine and piston engine works together to resist load fluctuations caused by unstable airflow or maneuvering avoidance, and to control clutch engagement.

[0114] Through the above steps, this invention, based on the formation of dynamic torque coordination, together with the rotor system, constitutes a stable control closed loop with high response speed, effectively resisting unstable airflow or maneuver load fluctuations and preventing aircraft instability. During this high-load coordination process, the exhaust temperature protection strategy is active throughout, ensuring that the power output during emergency maneuvers does not lead to thermodynamic over-limits.

[0115] The technical solution of this invention ultimately achieves improvements in various indicators, as shown in Table 1: Table 1

[0116] While the specific embodiments of the present invention depict actions or steps in a particular order, this should be understood as requiring such actions or steps to be performed in the specific order shown or in sequential order, or requiring all illustrated actions or steps to be performed to achieve the desired result. In certain environments, multitasking and parallel processing may be advantageous. Similarly, although several specific implementation details are included in the above discussion, these should not be construed as limiting the scope of this disclosure. Certain features described in the context of individual embodiments may also be implemented in combination in a single implementation. Conversely, various features described in the context of a single implementation may also be implemented individually or in any suitable sub-combination in multiple implementations.

[0117] 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 gas pipeline with pressure stabilization and intelligent temperature control functions, characterized in that, include: A diffuser (1) is a conical tube, the inlet end of which is used to connect to a gas turbine; The pressure stabilizing chamber (2) has its inlet end connected to the outlet end of the diffuser tube (1); The bleed air assembly (3) has its inlet end connected to the first outlet of the pressure stabilizing chamber (2) for guiding the gas to the jet rotor; The exhaust assembly (4) has its inlet end connected to the second outlet of the pressure stabilizing chamber (2), and its outlet end is provided with an adjustable vent valve (45). The air intake assembly (3) includes at least one bend, in which a flow guide structure for suppressing flow separation is provided.

2. The gas pipeline according to claim 1, characterized in that, The expansion angle of the diffuser (1) is 4°~8°, and it includes the front section (11), the middle section (12) and the end section (13) of the diffuser in sequence along the airflow direction.

3. The gas pipeline according to claim 2, characterized in that, It also includes a cooling system assembly (5), which includes a water tank (51), a water supply pipe (52), a flow control valve (53), and a centrifugal atomizing nozzle (54); the centrifugal atomizing nozzle (54) is connected to the middle section (12) of the diffuser pipe, and is connected to the water tank (51) through the water supply pipe (52) and the flow control valve (53).

4. The gas pipeline according to claim 1, characterized in that, The outlet of the pressure stabilizing chamber (2) adopts a multi-outlet diversion design, with one outlet connected to the bleed air assembly (3) and the other connected to the exhaust assembly (4).

5. The gas pipeline according to claim 1, characterized in that, The air intake assembly (3) has a guide plate (35) installed inside the bend. Since the air intake assembly (3) has two 45° bends, there is a large pressure loss. The guide plate (35) reduces the pressure loss at the bend by restricting the flow and avoids uneven airflow distribution.

6. The gas pipeline according to claim 1, characterized in that, The vent valve (45) is a steplessly adjustable disc valve mechanism, which adjusts the flow area of ​​the exhaust assembly (4) by changing the valve disc opening.

7. The gas pipeline according to any one of claims 1 to 6, characterized in that, The connections between the various pipeline sections are made using high-temperature resistant flanges. The high-temperature resistant flanges have circumferential grooves for adjusting the installation angle and are connected by high-temperature resistant bolts.

8. The gas pipeline according to claim 1, characterized in that, The outlet end of the bleed air assembly (3) is provided with an interface flange for connecting the jet rotor. An adjustment shim can be installed inside the interface flange to control the flow area of ​​the rotor inlet.

9. A support device for a gas pipeline according to any one of claims 1-8, characterized in that, It includes a pipeline support frame (61), a diffuser tube support (62), and a pressure stabilizing chamber support (63). The pipeline support frame (61) is used to fix the diffuser tube support (62) and the pressure stabilizing chamber support (63). The diffuser tube support (62) and the pressure stabilizing chamber support (63) are used to support the diffuser tube (1) and the pressure stabilizing chamber (2), respectively.

10. A method for integrated regulation and control of a piston-gas turbine hybrid power system, characterized in that, The composite power system includes a piston engine (801), a clutch (802), a steering gear (803), a rotor system (804), a clutch stepper motor (805), a fuel supply system (806), a fuel supply system stepper motor (807), a gas turbine (808), a compressor bleed air duct (809), a gas turbine bleed air duct (810), a starter (11), an exhaust flow regulating valve (12), a fuel flow regulating valve (13), an exhaust assembly 4, a compressor bleed air duct solenoid valve (14), and a control system; The piston engine (801) provides rotational power to the rotor shaft of the rotor system (804); the rotor system (804) has an air bleed pipe inside the rotor, and the gas generated by the gas turbine (808) enters the air bleed pipe of the rotor and is ejected from the blade tip to provide rotational power to the rotor; the gas turbine (808) provides gas to the piston engine (801) through the compressor air bleed pipe (809); The gas turbine (808) is connected to the compressor bleed air pipe (809), the gas turbine bleed air pipe (810) and the starter (811) respectively. The gas turbine (808) is equipped with a fuel flow regulating valve, the gas turbine bleed air pipe (810) is equipped with an exhaust flow regulating valve (812), and the bleed air pipe (809) is equipped with a compressor bleed air pipe solenoid valve (814). The gas turbine is communicatively connected to the exhaust flow regulating valve (812) and the fuel flow regulating valve (813); the gas turbine controls the opening of the gas turbine bleed air pipe (810) through the exhaust flow regulating valve (812), thereby controlling the output power of the gas turbine (808) to the rotor system (804); the gas turbine controls the power of the gas turbine through the fuel flow regulating valve (813); the compressor bleed air pipe (809) is controlled by the compressor bleed air pipe solenoid valve (814); The gas turbine bleed air duct (810) and exhaust assembly (4) are configured as the gas ducts according to any one of claims 1-8; The gas turbine bleed air duct (810) includes a diffuser (1), a pressure stabilizing chamber (2), and a bleed air assembly (3); the exhaust flow regulating valve (812) is located in the exhaust assembly (4).

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