Stamping turbine power generation system with heat dissipation adjusting function

Abstract

The invention discloses a stamping turbine power generation system with a heat dissipation adjusting function. The system comprises an air inlet channel, a flow regulator, a turbine working condition regulator, a power generator, an air compressor disc, a heat exchanger box, a converter and an exhaust pipe, the air inlet channel is connected with the stamping turbine through the flow regulator and the turbine working condition regulator in sequence, and the air compressor working condition regulator is arranged between the power generator and the air compressor disc. An air flow pipeline of the stamping turbine passes through the outer culvert opening and closing valve and then sequentially passes through the heat exchanger box, the air compressor working condition regulator and the air compressor disc to be connected with the exhaust pipe, and the air flow pipeline of the stamping turbine is further directly connected with the exhaust pipe through the outer culvert opening and closing valve. The invention has the advantages that the ram air requirements at two different cruise flight heights of 100km high altitude and 500m low altitude are met, and the influence of high temperature on the motor performance is effectively avoided, so that the technical problems of unstable rotating speed and difficult heat dissipation of the generator under the working conditions of different flight heights of the aircraft are effectively solved.

Description

Technical Field

[0001] The invention relates to a ramjet turbine power generation system, in particular to a ramjet turbine power generation system with a heat dissipation regulating function, and belongs to the field of thermal management of aircraft generators. Background Art

[0002] Driven by both technology and demand, permanent magnet synchronous motors have been vigorously developed and applied in the aviation field due to their advantages such as high efficiency and high power density. However, high loss density and heat dissipation difficulties are also problems faced by motors during operation, which bring huge safety hazards to motor operation. Therefore, the heat dissipation and cooling issues of ramjet turbine power generation systems for aviation have received more and more attention.

[0003] At present, the main solutions to the heat dissipation problem of permanent magnet synchronous motors include adding heat-conducting plugs at the end to enhance heat dissipation, external water-cooling structures to enhance heat exchange, and air-cooling structure design to enhance heat exchange. For aviation ramjet turbine power generation systems, there are high restrictions on the volume and weight of heat dissipation accessories, so it is more appropriate for aviation ramjet turbine power generation systems to use air cooling.

[0004] However, as the cruising flight altitude changes, the basic state parameters of the atmospheric environment, such as temperature and pressure, will change, which will bring about two aspects of influence. First, the power change brought to the ramjet turbine by the expansion of the medium, and the unstable rotor speed will cause the efficiency of the permanent magnet synchronous motor to decrease; second, the state of the medium involved in motor cooling changes, and the airflow passing through the cooling fins will increase the flow dissipation and flow resistance. Therefore, it is very necessary to design a ramjet turbine power generation system with adjustable heat dissipation function according to the change of cruising flight altitude. Summary of the invention

[0005] The technical problem to be solved by the present invention is to provide a ramjet turbine power generation system with adjustable heat dissipation function, which can maintain a stable rotation speed at different cruising altitudes, realize cooling and heat dissipation of a permanent magnet synchronous motor, and ensure motor efficiency.

[0006] In order to solve the above technical problems, the ramjet turbine power generation system with heat dissipation regulating function of the present invention comprises an air inlet for allowing ramjet air to enter, a flow regulator matched with a first-stage guide vane, a turbine operating condition regulator matched with a second-stage guide vane, a generator connected with a ramjet turbine, a compressor disk connected to the driving end of the generator, a heat exchange box and a converter matched with the generator, and an exhaust pipe for exhaust, the air inlet is connected to the ramjet turbine through the flow regulator and the turbine operating condition regulator in sequence, a compressor operating condition regulator is arranged between the generator and the compressor disk, the airflow pipeline of the ramjet turbine passes through an outer culvert opening and closing valve and then passes through a heat exchange box, a compressor operating condition regulator and a compressor disk in sequence to connect to the exhaust pipe, and the airflow pipeline of the ramjet turbine is also directly connected to the exhaust pipe through the outer culvert opening and closing valve.

[0007] The air inlet and the exhaust pipe are both pipe-shaped structures.

[0008] The flow regulator is an adjustable structure consisting of a linkage ring and a first-stage guide blade with a shaft neck.

[0009] The turbine operating condition regulator is an adjustable structure composed of a linkage ring and secondary guide blades with shaft necks.

[0010] The ram turbine is a single-stage axial flow turbine; the compressor disc is a matching set for a single-stage axial flow compressor.

[0011] The generator is a permanent magnet synchronous motor.

[0012] The heat exchange casing is a heat dissipation casing with fins.

[0013] The converter is a fully controlled rectifier.

[0014] The compressor operating condition regulator is an adjustable structure consisting of a linkage ring and compressor guide vanes with shaft necks.

[0015] A regulation and control method using the above-mentioned ramjet turbine power generation system with regulation and heat dissipation function comprises the following steps:

[0016] When the aircraft flies at low altitude, the controller controls the first-stage guide blade profile installation angle α of the flow regulator to increase, and the second-stage guide blade profile installation angle β of the turbine operating condition regulator P3 to decrease, thereby reducing the working capacity of the airflow and impacting the downstream ramjet turbine blades to the speed design value, doing work and cooling down; at this time, the culvert on-off valve is closed; all airflow flows through the fins of the heat exchange box for convective heat exchange; the airflow after decompression enters the compressor operating condition regulator, and the blade profile installation angle γ of its compressor guide blades is reduced under the control of the controller;

[0017] When the aircraft is flying at high altitude, at this time, the blade installation angle α of the first-stage guide vane of the flow regulator will be reduced under the control of the controller to reduce throttling; the blade installation angle β of the second-stage guide vane of the turbine operating condition regulator will be increased under the control of the controller to increase the working capacity of the airflow and impact the downstream ramjet turbine blades to the design speed value to do work and cool down; at this time, the outer culvert on-off valve is opened, and the outer culvert airflow, which accounts for 60% of the total flow, has a small resistance and is easy to discharge; the remaining 40% of the main channel airflow flows through the fins of the heat exchange box for convective heat exchange; the airflow after decompression enters the compressor operating condition regulator, and the blade installation angle γ of its compressor guide vane increases under the control of the controller.

[0018] The advantages of the present invention are:

[0019] When the aircraft is cruising at a low altitude, the flow regulator throttles, the turbine condition regulator pre-swirls the airflow, the outer culvert on-off valve is closed, and the working airflow all passes through the heat exchange box for heat dissipation and cooling of the generator, thereby improving the generator's power generation efficiency. The compressor condition regulator pre-swirls the airflow, increasing the working airflow pressure to facilitate exhaust pipe discharge; when the aircraft is cruising at a high altitude, the flow regulator increases the opening, the turbine condition regulator pre-swirls the airflow, and the outer culvert on-off valve is opened, 60% of the working airflow flows out of the outer culvert, thereby reducing the flow resistance of the working airflow, and 40% of the working airflow passes through the heat exchange box for heat dissipation and cooling of the generator, thereby improving the generator's power generation efficiency. The compressor condition regulator Pre-swirl is performed to ensure that the compressor disk does not surge, and the working air flow pressure is increased to facilitate exhaust pipe discharge. Therefore, during high-speed flight, the system can introduce high-speed aerodynamic turbine expansion to do work. Before the high-speed air enters the power vortex, the flow and operating conditions are adjusted by the air conditioning component to meet the ram air requirements at two different cruising flight altitudes of 100km and 500m. The ram air drives the permanent magnet motor to rotate and generate electricity. The temperature of the expanded air is at a very low level, which can carry out convection heat dissipation on the permanent magnet synchronous motor, effectively avoiding the impact of high temperature on motor performance, thereby effectively solving the technical problems of unstable speed and difficult heat dissipation of the generator under different flight altitude conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a principle block diagram of the ramjet turbine power generation system with heat dissipation regulating function of the present invention.

[0021] Figure 2 It is an airflow direction diagram under low-altitude flight conditions in an embodiment of the present invention.

[0022] Figure 3 It is an airflow direction diagram under high-altitude flight conditions in an embodiment of the present invention.

[0023] Figure 1Middle: P1-air duct, P2-flow regulator, P3-turbine operating condition regulator, P4-ramjet turbine, P5-generator, P6-heat exchange box, P7-converter, P8-compressor operating condition regulator, P9-compressor disc, P10-exhaust pipe, P11-external on-off valve, P12-controller. DETAILED DESCRIPTION

[0024] The ramjet turbine power generation system with heat dissipation regulating function of the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0025] Embodiment 1:

[0026] The ramjet turbine power generation system with heat dissipation regulating function of this embodiment comprises an air inlet P1 for allowing ramjet air to enter, a flow regulator P2 matched with the first-stage guide vanes, a turbine operating condition regulator P3 matched with the second-stage guide vanes, a generator P5 connected with a ramjet turbine P4, a compressor disk P9 connected to the driving end of the generator P5, a heat exchange box P6 and a converter P7 matched with the generator P5, and an exhaust pipe P10 for exhaust, wherein the ramjet turbine, the generator and the compressor disk are threadedly connected at both ends of the long shaft, and the air inlet P1 passes through the flow regulator P2 in sequence. The regulator P2 and the turbine operating condition regulator P3 are connected to the ram turbine P4. The compressor operating condition regulator P8 is arranged between the generator P5 and the compressor plate P9. The guide vanes of the flow regulator, the turbine operating condition regulator and the compressor operating condition regulator are matched with the clearance of the main casing of the system. The airflow pipeline of the ram turbine P4 passes through the outer culvert on-off valve P11 and then passes through the heat exchange casing P6, the compressor operating condition regulator P8 and the compressor plate P9 to connect to the exhaust pipe P10. The airflow pipeline of the ram turbine P4 is also directly connected to the exhaust pipe P10 through the outer culvert on-off valve P11. The flow regulator P2, turbine operating condition regulator P3, and culvert on-off valve P11 are all connected to a controller P12, and the controller P12 mainly includes data and command communication with the overall control system, a real-time test system, a command database and a data rapid processing system, and an actuator actuator. Therefore, when flying at high altitude, the controller P12 controls the flow regulator P2 to reduce the blade installation angle (the flow regulator blade installation angle α approaches zero), the turbine operating condition regulator P3 blade installation angle β increases, the culvert on-off valve P11 opens, and the compressor operating condition regulator P8 blade installation angle γ increases; When the aircraft flies at a low altitude, the ram air in the air inlet P1 enters the inlet of the flow regulator P2. The airflow is decompressed and cooled through the flow regulator P2, the turbine operating condition regulator P3 and the ram turbine P4, and the kinetic energy in the high-speed free flow is extracted to convert into shaft work. The generator P5 is driven by the transmission shaft to reach the designed speed to generate electricity and drive the downstream compressor disk P9. The airflow after decompression and cooling flows through the heat exchange box P6 for heat exchange and then heats up. The heat exchange box P6 realizes the cooling function. The heated airflow enters the exhaust pipe P10 through the compressor operating condition regulator P8 and the compressor disk P9, and is then discharged into the environment.

[0027] Furthermore, the air inlet duct P1 and the exhaust pipe P10 can be designed as a pipe-shaped structure according to the shape of the aircraft.

[0028] Furthermore, the flow regulator P2 is an adjustable structure composed of a linkage ring and a first-stage guide blade with a shaft neck, the turbine operating condition regulator P3 is an adjustable structure composed of a linkage ring and a second-stage guide blade with a shaft neck, the compressor operating condition regulator P8 is an adjustable structure composed of a linkage ring and a compressor guide blade with a shaft neck, the ram turbine P4 is a single-stage axial flow turbine; the compressor disc P9 is a matching single-stage axial flow compressor, the generator P5 is a permanent magnet synchronous motor, the heat exchanger box P6 is a heat dissipation box with fins, and the converter P7 is a fully controlled rectifier.

[0029] Embodiment 2:

[0030] This embodiment adopts the regulation and control method of the ramjet turbine power generation system with the regulation and heat dissipation function in the first embodiment, and includes the following steps:

[0031] like Figure 2 As shown, when the aircraft flies at low altitude, the airflow density is large, and the output power far exceeds the generator carrying capacity, so throttling is required. The controller P12 controls the first-stage guide blade profile installation angle α of the flow regulator P2 to increase (approach 60°) and the second-stage guide blade profile installation angle β of the turbine operating condition regulator P3 to decrease (approach zero), thereby reducing the working capacity of the airflow and impacting the downstream ramjet turbine blades to the speed design value to do work and cool down. Since the low air flow temperature is high, more air flow is required for the heat dissipation of the generator P5, and the outer culvert on-off valve P11 is closed at this time. All airflow flows through the fins of the heat exchange box P6 for convective heat exchange. The airflow after decompression enters the compressor operating condition regulator P8, and the blade profile installation angle γ of its compressor guide blades decreases (approaches zero) under the control of the controller P12 to prevent the airflow from being blocked in the compressor disk P9.

[0032] like Figure 3 As shown, when the aircraft is flying at high altitude, the airflow density is small and the airflow heat dissipation capacity is extremely strong, but the flow rate is small and the output shaft power capacity is weak. At this time, the blade installation angle α of the first-stage guide blade of the flow regulator P2 will be reduced under the control of the controller P12 to reduce throttling; the blade installation angle β of the second-stage guide blade of the turbine operating condition regulator P3 will be increased under the control of the controller P12 to increase the working capacity of the airflow and impact the downstream ramjet turbine blade to the speed design value to do work and cool down; because the airflow temperature at high altitude is low, less air flow is required for the heat dissipation of the generator P5. At this time, the outer culvert on-off valve P11 is opened, and the outer culvert airflow resistance accounting for 60% of the total flow is small and easy to discharge; the remaining 40% of the main channel airflow flows through the fins of the heat exchange box P6 for convective heat exchange; the airflow after decompression enters the compressor operating condition regulator P8, and the blade installation angle γ of its compressor guide blade is increased under the control of the controller P12 to prevent the airflow from surging in the compressor disk P9.

[0033] In this embodiment, the low altitude setting value is 500 m above sea level, the high altitude setting value is 10 km above sea level, and the ramjet turbine speed design value is 18000 rpm.

[0034] Of course, the above description is not a limitation of the present invention, and the present invention is not limited to the above examples. Changes, modifications, additions or substitutions made by technicians in this technical field within the essential scope of the present invention should also fall within the protection scope of the present invention.

Claims

1. A ramjet turbine power generation system with heat dissipation adjustment function, characterized in that: The invention comprises an air inlet (P1) for allowing ram air to enter, a flow regulator (P2) matched with a first-stage guide blade, a turbine operating condition regulator (P3) matched with a second-stage guide blade, a generator (P5) connected to a ram turbine (P4), a compressor disk (P9) connected to the driving end of the generator (P5), a heat exchange box (P6) and a converter (P7) matched with the generator (P5), and an exhaust pipe (P10) for exhausting air, wherein the air inlet (P1) passes through the flow regulator (P2), the turbine (P3) and the exhaust pipe (P10) in sequence. The operating condition regulator (P3) is connected to the ram turbine (P4), a compressor operating condition regulator (P8) is arranged between the generator (P5) and the compressor disk (P9), the air flow pipeline of the ram turbine (P4) passes through the outer culvert opening and closing valve (P11), and then passes through the heat exchange box (P6), the compressor operating condition regulator (P8) and the compressor disk (P9) in sequence to connect to the exhaust pipe (P10), and the air flow pipeline of the ram turbine (P4) is also directly connected to the exhaust pipe (P10) through the outer culvert opening and closing valve (P11).

2. The ramjet turbine power generation system with heat dissipation adjustment function according to claim 1, characterized in that: The air inlet (P1) and the exhaust pipe (P10) are both pipe-shaped structures.

3. The ramjet turbine power generation system with heat dissipation adjustment function according to claim 1 or 2, characterized in that: The flow regulator (P2) is an adjustable structure consisting of a linkage ring and a first-stage guide blade with a shaft neck.

4. The ramjet turbine power generation system with heat dissipation adjustment function according to claim 3, characterized in that: The turbine operating condition regulator (P3) is an adjustable structure consisting of a linkage ring and secondary guide blades with shaft necks.

5. The ramjet turbine power generation system with adjustable heat dissipation function according to claim 1, 2 or 4, characterized in that: The ram turbine (P4) is a single-stage axial flow turbine; the compressor disc (P9) is a matching device for a single-stage axial flow compressor.

6. The ramjet turbine power generation system with heat dissipation adjustment function according to claim 5, characterized in that: The generator (P5) is a permanent magnet synchronous motor.

7. The ramjet turbine power generation system with adjustable heat dissipation function according to claim 1, 2, 4 or 6, characterized in that: The heat exchange casing (P6) is a heat dissipation casing with fins.

8. The ramjet turbine power generation system with heat dissipation adjustment function according to claim 7, characterized in that: The converter (P7) is a fully controlled rectifier.

9. The ramjet turbine power generation system with adjustable heat dissipation function according to claim 8, characterized in that: The compressor operating condition regulator (P8) is an adjustable structure consisting of a linkage ring and a compressor guide vane with a journal.

10. A method for regulating and controlling a ramjet turbine power generation system with a heat dissipation regulating function according to any one of claims 1 to 9, characterized in that: The following steps are involved: When the aircraft flies at a low altitude, the controller (P12) controls the first-stage guide blade profile installation angle α of the flow regulator (P2) to increase, and the second-stage guide blade profile installation angle β of the turbine operating condition regulator P3 to decrease, thereby reducing the working capacity of the airflow and impacting the downstream ramjet turbine blades to the design speed value to perform work and cool down; at this time, the outer culvert on-off valve (P11) is closed; all airflow flows through the fins of the heat exchange box (P6) for convective heat exchange; the airflow after decompression enters the compressor operating condition regulator (P8), and the blade profile installation angle γ of its compressor guide blades is reduced under the control of the controller (P12); When the aircraft is flying at high altitude, at this time, the blade installation angle α of the first-stage guide blade of the flow regulator (P2) will be reduced under the control of the controller (P12), reducing the throttling; the blade installation angle β of the second-stage guide blade of the turbine operating condition regulator (P3) will be increased under the control of the controller (P12), increasing the working capacity of the airflow and impacting the downstream ramjet turbine blades to the speed design value, doing work and cooling; at this time, the outer culvert on-off valve (P11) is opened, and the outer culvert airflow, which accounts for 60% of the total flow, has a small resistance and is easy to discharge; The remaining 40% of the main channel airflow flows through the fins of the heat exchange box (P6) for convective heat exchange; the airflow after being reduced in pressure enters the compressor operating condition regulator (P8), and the blade installation angle γ of its compressor guide vane increases under the control of the controller (P12).

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