CN117738784A - Efficient axial flow supercharging system of inverted triangle rotor engine for aviation - Google Patents

Abstract

The invention provides an efficient axial-flow supercharging system of an inverted triangle rotor engine for aviation, which comprises an air inlet device arranged at an air inlet of the inverted triangle rotor engine, an exhaust device arranged at an air outlet of the inverted triangle rotor engine, an axial-flow supercharger and a supercharger control device arranged in the air inlet device, a turbine device arranged in the exhaust device, and the axial-flow supercharger, the turbine device and the inverted triangle rotor engine coaxially linked, wherein the supercharger control device is used for carrying out air inlet diversion according to cylinder pressure measurement feedback. The system realizes the real-time adjustment of the air inlet density and the air inlet pressure of the reverse triangular rotor engine at high altitude, and simultaneously utilizes the energy of waste gas to improve the power density and the energy conversion efficiency of the engine and improve the high-altitude performance and the economic performance of the engine.

Description

Efficient axial flow supercharging system of inverted triangle rotor engine for aviation

Technical Field

The invention belongs to the technical field of aviation power, and particularly relates to an efficient axial flow supercharging system of an inverted triangle rotor engine for aviation.

Background

Unmanned aerial vehicles are rapidly developed towards the aspects of increasingly miniaturized loads, longer endurance time, higher economy and the like. This requires that the unmanned aerial vehicle power system also have the characteristics of small volume, high power density. The rotor engine has a simple structure and strong power, and the complex crankshaft connecting rod mechanism of the traditional piston engine is compensated by the advantage of power output through rotation of the crankshaft, so that the arrangement space is reduced. Therefore, the device has wide application prospect in the aspect of power of a small unmanned aerial vehicle. At present, the rotor engines of the models of 80s-15BHP, AR-801, AR741 and the like are started to be produced and applied to various fields of unmanned aerial vehicle detection, relay communication, hybrid power and the like.

However, the combustion chamber of a conventional Wankel rotary engine is moving and long, which results in insufficient combustion and low combustion efficiency of the engine. In recent years, a novel rotor engine with an inverse triangle structure is developed, the rotor and cylinder profile of the rotor engine is opposite to that of a Wankel engine, a combustion chamber is fixed, the compression ratio is higher, and the problem of low combustion efficiency is solved to a certain extent.

In addition, considering the application in the unmanned power field, the low temperature, low pressure and lean air at high altitude become the main factors limiting the engine performance: (1) Because of low ambient pressure and low temperature, atomization, gas mixture organization and combustion are more difficult, and the combustion efficiency of the engine is reduced to a great extent. (2) The lean air reduces the air inflow of the engine, and the working efficiency is affected by less circulating working medium. (3) Low-temperature, low-pressure and low-density air enters the engine, so that the fuel equivalent ratio is improved, and the economic cost and the thermal efficiency of the engine are increased.

The development of the supercharging technology greatly improves the power density of the engine, is beneficial to stable combustion in a high-altitude environment, and promotes the development of the traditional fuel rotor engine technology. Besides increasing the density of the air intake, the turbocharging technology can also utilize the energy of the exhaust gas, improve the economy of the engine, has strong adaptability in high-altitude areas and can effectively reduce noise and exhaust pollution. However, the turbo-charging has poor acceleration performance and serious component heat load problems, and the special planetary gear structure of the rotor engine and low exhaust temperature under low equivalent ratio can effectively reduce the inertial load and the heat load of the engine and make up for the defects of turbo-charging. At present, the supercharging technology adopted on the reverse delta rotor engine is less in research and application in the aviation field, and the supercharging control technology under different altitudes and under the air intake parameters is still to be developed.

Disclosure of Invention

In order to solve the problems in the prior art, the invention provides an efficient axial-flow supercharging system of an anti-triangular rotor engine for aviation, which realizes real-time adjustment of the air intake density and the air intake pressure of the anti-triangular rotor engine at high altitude, and simultaneously improves the power density and the energy conversion efficiency of the engine and improves the high altitude performance and the economic performance of the engine by utilizing the energy of waste gas.

In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides an aviation is with high-efficient axial-flow supercharging system of anti-triangle rotor engine, including setting up the air inlet unit at anti-triangle rotor engine air inlet, set up the exhaust apparatus at anti-triangle rotor engine gas outlet, set up axial-flow type booster and booster controlling means in the air inlet unit, be provided with turbine unit in the exhaust apparatus, axial-flow type booster, turbine unit and anti-triangle rotor engine coaxial linkage, booster controlling means is used for carrying out the air intake water conservancy diversion according to jar pressure measurement feedback.

Further, the supercharger control device comprises a guide vane, an adjusting ring, a control casing, a cylinder pressure sensor, a connecting rod and a sliding rail, wherein the tail end of the guide vane is connected with the adjusting ring through the connecting rod, the adjusting ring is slidably connected to the sliding rail, the sliding rail is circumferentially fixed on the outer side of the air inlet device, the cylinder pressure sensor is arranged inside a combustion chamber of the inverted triangle rotor engine, the cylinder pressure sensor is used for acquiring pressure data in the combustion chamber and transmitting the pressure data to the control casing, and the control casing is connected with the adjusting ring and used for adjusting the angle of the guide vane according to the pressure data.

Further, the air inlet device comprises a filter grid and an air inlet pipeline, the air inlet pipeline is a cylindrical pipeline with an inner section gradually shrinking towards the direction, the filter grid is connected with one end of a large section of the air inlet pipeline, one end of a small section of the air inlet pipeline is connected with an inlet of the inverted triangle rotor engine, eight through holes are circumferentially formed in one end, close to the filter grid, of the air inlet pipeline, the tail ends of guide vanes extend out of the air inlet pipeline to be connected with an adjusting ring, and a plurality of mounting grooves are circumferentially formed in the inner wall of the air inlet pipeline to be used for mounting the axial-flow supercharger.

Further, the axial-flow supercharger comprises a supercharger rotating shaft, one end of the supercharger rotating shaft is sleeved in a hollow engine crankshaft of the reverse triangle rotor engine, the other end of the supercharger rotating shaft is connected with a multistage rotor blade disc, a plurality of mounting grooves are formed in the circumference of the rotor blade disc, groove structures are arranged at the roots of the rotor blades and the stator blades, the roots of the rotor blades are inserted into the mounting grooves in the rotor blade disc to be fixed, and the roots of the stator blades are inserted into the mounting grooves in the air inlet pipeline to be fixed; the number of the mounting grooves on the air inlet pipeline is the same as that of the mounting grooves on the rotor blade disc, and the mounting grooves are arranged at intervals in a hollow manner; one side of the axial-flow type supercharger is provided with a fairing, a through hole is formed in the fairing, and the rotor blades extend out of the fairing from the through hole.

Further, the clearance between the tail of the fairing and the anti-delta rotary engine is not more than 3mm.

Further, the rotor blade and the stator blade are provided with three stages, and each stage of the stator blade is closely arranged behind the rotor blade of the corresponding stage, and the section of the rotor blade is of a curved wing type structure.

Furthermore, one end of the rotating shaft of the supercharger extends out of the hollow engine crankshaft of the inverted triangle rotor engine and enters the exhaust device, two-stage turbine blades are arranged on the rotating shaft of the supercharger in the exhaust device to form the turbine device, and the structure and the connection mode of the turbine blades are the same as those of the rotor blades.

Further, the supercharger rotating shaft is sleeved in a hollow engine crankshaft of the inverted triangle rotor engine through a bearing, and the bearing is in interference fit with the supercharger rotating shaft; the part of the supercharger rotating shaft entering the exhaust device is supported and fixed in the exhaust device through a bearing.

Further, the exhaust device comprises an exhaust pipeline, the exhaust pipeline is in a convergent shape with a reduced section, three inlets are arranged at the large section end of the exhaust pipeline, and the three inlets of the exhaust pipeline are in airtight connection with three exhaust ports of the anti-delta rotor engine.

Further, the exhaust device and the turbine device are made of high-temperature resistant materials.

Compared with the prior art, the invention has at least the following beneficial effects:

the invention provides an efficient axial-flow supercharging system of an inverted triangle rotor engine for aviation, which is characterized in that an axial-flow supercharger is arranged for a special structure of the inverted triangle rotor engine to flow and axially enter the supercharger, the air enters the inverted triangle rotor engine after being subjected to speed reduction and supercharging, the flow loss of air flow is greatly reduced in the whole process, waste gas after being combusted of the inverted triangle rotor engine enters a turbine device and is discharged after being expanded, residual energy of the exhaust is fully utilized, the energy conversion rate is high, and the high-altitude working performance of the engine can be effectively improved; the supercharger control device carries out air inlet diversion through cylinder pressure measurement feedback to realize real-time adjustment of air inlet density and air inlet pressure of the reverse triangular rotor engine at high altitude, improves engine power density and energy conversion efficiency, and improves high altitude performance and economic performance of the engine.

The shaft of the axial-flow supercharger and the turbine device and the crankshaft of the inverted triangle rotor engine are coaxially connected by adopting a sleeve type structure, so that the occupied volume of the device can be effectively reduced, the power-weight ratio of the engine can be improved, and the performance of the unmanned aerial vehicle can be improved.

According to the invention, the angle of the guide vane is adjustable, the guide vane is connected with the peripheral adjusting ring, the adjusting ring is controlled by the control casing, the rotating speed of the axial-flow supercharger is increased when the air-lift engine works, the cylinder pressure sensor on the engine detects a feedback cylinder pressure signal to the control casing, the control casing controls the adjusting ring to rotate according to the performance improvement rule of the engine, the angle of the guide vane is changed to match the rotating speed of the supercharger, the wall surface separation of a flow field is avoided, and the working efficiency of the supercharger is improved. The engine power control device is simple in structure, small in occupied space and capable of effectively meeting stable power output of the engine at different altitudes.

Drawings

In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of an efficient axial-flow supercharging system for an inverted delta rotary engine for aviation in an embodiment of the present invention.

FIG. 2 is a schematic diagram of a three-dimensional structure of an engine high efficiency axial flow supercharger in an embodiment of the present invention.

Fig. 3 is a schematic structural view of a guide vane adjusting device in an embodiment of the present invention.

FIG. 4 is a schematic view of a mounting structure of a supercharger blade in an embodiment of the invention

Fig. 5 is a schematic diagram showing the change of the amount of naturally aspirated air at different altitudes of the engine in the embodiment of the invention.

FIG. 6 is a schematic diagram of a power attenuation change law of an engine at different altitudes according to an embodiment of the present invention.

FIG. 7 is a schematic diagram of the regulation of the pressure ratio of the supercharger at different altitudes in an embodiment of the present invention.

FIG. 8 shows the angle adjustment of the guide vane of the supercharger at different supercharging ratios in an embodiment of the present invention.

FIG. 9 shows the peak in-cylinder pressure variation at different altitudes in accordance with an embodiment of the present invention.

In the accompanying drawings:

1 is an air inlet device, 1-1 is a filter grid, and 1-2 is an air inlet pipeline;

2 is a supercharger control device, 2-1 is a guide vane, 2-2 is an adjusting ring, 2-3 is a control casing, 2-4 is a cylinder pressure sensor, 2-5 is a connecting rod, and 2-6 is a sliding rail;

3 is an axial-flow supercharger, 3-1 is a rotor blade disc, 3-2 is a rotor blade, 3-3 is a stator blade, 3-4 is a fairing, and 3-5 is a supercharger rotating shaft;

4 is an inverted triangle rotor engine, 4-1 is a rotor, 4-2 is a combustion chamber, and 4-3 is a crankshaft;

5 is an exhaust device, and 5-1 is an exhaust pipeline;

6 is a turbine device, 6-1 is a turbine blade disc, and 6-2 is a turbine blade.

Detailed Description

The invention is further described below with reference to the drawings and the detailed description.

As shown in figures 1 and 2, the efficient axial-flow supercharging system of the anti-delta rotor engine for aviation provided by the invention comprises an air inlet device 1, an anti-delta rotor engine 4 and an exhaust device 5, wherein an outlet of the air inlet device 1 is communicated with an inlet of the anti-delta rotor engine 4, an outlet of the anti-delta rotor engine 4 is communicated with an inlet of the exhaust device 5, a supercharger control device 2 and an axial-flow supercharger 3 are arranged in the air inlet device 1, a supercharger rotating shaft 3-5 of the axial-flow supercharger 3 is sleeved in an engine crankshaft 4-3, the engine crankshaft 4-3 is of a hollow structure, the supercharger rotating shaft 3-5 is positioned at the inner side of the crankshaft 4-3, and the supercharger rotating shaft 3-5 is in interference fit with a bearing to support the engine crankshaft 4-3 so as to realize rotation of different coaxial rotating speeds of the two.

The exhaust device 5 is provided with a turbine device 6, which is coaxially linked with the axial-flow supercharger 3.

The air inlet device 1 in this embodiment includes a filter grid 1-1 and an air inlet pipe 1-2, wherein a connecting flange is arranged between the filter grid 1-1 and the air inlet pipe 1-2, and the filter grid is connected with the air inlet pipe 1-2 through a connecting bolt, and a gasket is assembled to ensure connection stability and sealing. The air inlet pipeline 1-2 is a cylindrical pipeline with the inner section gradually shrinking towards the direction of the anti-triangular rotor engine 4, so that air inlet speed reduction and pressurization are facilitated, eight through holes (used for connecting the guide vane 2-1) are formed in the front end, the distance from the port of the air inlet pipeline 1-2 is about 5mm, and a mounting groove (used for mounting the stator vane 3-3 and see the mounting structure shown in figure 3) is formed in the rear section. The air inlet pipeline 1-2 is connected with the anti-delta rotor engine 4 through a connecting flange, and is connected through a connecting bolt, and the assembling gasket ensures stable connection and sealing.

As shown in fig. 1, 2 and 3, in the present embodiment, the supercharger control device 2 includes a guide vane 2-1, an adjusting ring 2-2, a control casing 2-3, a cylinder pressure sensor 2-4, a connecting rod 2-5 and a slide rail 2-6. The guide vane 2-1 comprises a rod-shaped tail end and is connected with the adjusting ring 2-2 through a connecting rod 2-5. The adjusting ring 2-2 is arranged on the sliding rail 2-6, the sliding rail 2-6 is arranged on the outer side of the air inlet channel 1-2 through bolts and is about 10mm away from a port of the air inlet channel 1-2, and the adjusting ring 2-2 is connected with the control casing 2-3 and used for controlling the adjusting ring 2-2 to move on the sliding rail 2-6, so that the angle of the guide vane 2-1 is adjusted. The cylinder pressure sensor 2-4 is arranged in the combustion chamber 4-2 of the engine through threads, the tip end of the cylinder pressure sensor extends into a pit of the combustion chamber 4-2 by about 15mm, the cylinder pressure sensor 2-4 is connected with the control casing 2-3 and used for transmitting the cylinder pressure to the control casing 2-3, and the control casing 2-3 controls the adjusting ring 2-2 to move on the sliding rail 2-6, so that the angle of the guide vane 2-1 is adjusted.

As shown in fig. 1, 2 and 4, the axial flow supercharger 3 in this embodiment includes a rotor disk 3-1, rotor blades 3-2, stator blades 3-3, a cowling 3-4, and a supercharger shaft 3-5. The rotor disc 3-1 is connected with the supercharger rotating shaft 3-5 through a connecting key, and the fairing 3-4 is sleeved outside to reduce pneumatic resistance and realize cross section convergence in the air inlet channel. In addition, the rotor disk 3-1 is divided into three stages, and 8 mounting grooves are machined per stage. The section of the rotor blade 3-2 is of a bent wing structure, the root of the rotor blade is inserted into the rotor blade disc 3-1 through a groove structure, and the rotor blade is fixedly connected through a fixing pin 3-4.

The number of the mounting grooves on the air inlet pipeline 1-2 is the same as that of the mounting grooves on the rotor blade disc 3-1, the stator blades 3-3 are equally divided into three stages, the stator blades are mounted on the air inlet pipeline 1-2 in the same structure, and each stage is closely arranged behind the rotor blades 3-2 of the corresponding stage. The supercharger rotating shaft 3-5 and the engine crankshaft 4-3 are of sleeve type structures, the engine crankshaft 4-3 is of a hollow structure, the supercharger rotating shaft 3-5 is positioned on the inner side of the crankshaft 4-3, the supercharger rotating shaft 3-5 is in interference fit with a bearing, and the engine crankshaft 4-3 is supported to realize the rotation of the supercharger rotating shaft 3-5 and the engine crankshaft 4-3 at different coaxial rotating speeds.

As shown in fig. 1 and 2, in this embodiment, the exhaust device 5 includes an exhaust pipe 5-1, and three inlets are machined at the front end of the exhaust pipe 5-1, and are respectively connected with three exhaust ports of the anti-delta rotor engine 4 through a connecting flange and bolts, and a gasket is installed in the middle to ensure sealing, so as to realize axial exhaust of combustion tail gas and reduce flow loss. The rear end of the exhaust pipe 5-1 has a convergent shape with a reduced section, which is convenient for the airflow to converge and accelerate and provides larger thrust.

As shown in fig. 1, 2 and 4, the turbine device 6 in this embodiment includes a turbine blade disk 6-1 and turbine blades 6-2. The turbine blade disc 6-1 is coaxial with the rotor blade disc 3-1 and is fixed on the supercharger rotating shaft 3-5 through a connecting key. The turbine blade disc 6-1 is divided into two stages, 8 mounting grooves are processed in each stage, the section of the turbine blade 6-2 is of a bent wing type structure, the root of the turbine blade is of a groove type structure, and the root of the turbine blade is inserted into the turbine blade disc 6-1 and is fixedly connected through a fixing pin. The supercharger rotating shaft 3-5 is provided with a bearing for supporting the exhaust pipeline 5-1, and a certain sealing effect is realized. After the high-temperature air flow enters the turbine device 6, the high-temperature air flow flows through the turbine blades 6-2 with reduced sections, expansion acceleration is realized, thrust is provided through the reaction force, and meanwhile, the rotor disc 3-1 and the rotor blades 3-2 are driven to coaxially link through the supercharger rotating shaft 3-5.

In use, the anti-delta rotary engine 4 is fixed, and the air inlet device 1 and the air outlet device 5 are connected with the anti-delta rotary engine 4 through a connecting flange and bolts. The supercharger rotating shaft 3-5 and the engine crankshaft 4-3 are respectively in interference fit with bearings, the rotor disc 3-1 and the turbine disc 6-1 are installed on the supercharger rotating shaft 3-5 through connecting keys, and the rotor blades 3-2 and the turbine blades 6-2 are respectively inserted into the rotor disc 3-1 and the turbine disc 6-1 through grooves. The stator blades 3-3 are arranged on the air inlet pipeline 1-2, are sequentially corresponding to the rotor blades 3-2 and are closely distributed, and the fairing 3-4 is sleeved on the outer side of the rotor blade disc 3-1. The adjusting ring 2-2 is arranged outside the air inlet pipeline 1-2 through the sliding rail 2-6, and the connecting end of the guide vane 2-1 passes through a through hole at the front end of the air inlet pipeline 1-2 and is connected with the adjusting ring 2-2. The control casing 2-3 is connected with the cylinder pressure sensor 2-4 and the adjusting ring 2-2.

When the axial-flow supercharger 3 works, the primary rotor blade 3-2 and the primary stator blade 3-3 form a compression stage, the rotor blade 3-2 rotates to drive air to rotate, and air inlet supercharging is achieved through speed reduction and supercharging of the stator blade 3-3.

When the supercharger control device 2 works, the cylinder pressure sensor 2-4 measures the periodical change condition of the pressure in the combustion chamber 4-2, and feeds back the periodical change condition to the control casing 2-3, the control casing 2-3 makes a regulation and control instruction according to a measurement signal, and the internal stepping motor drives the regulating ring 2-2 to rotate to control the angle of the guide vane 2-1, so that the adjustment of the airflow direction is realized.

The incoming flow enters the inlet of the anti-delta rotor engine 4 through the air inlet channel 1-2, and the clearance between the fairing 3-4 and the anti-delta rotor engine 4 is not more than 3mm to prevent radial air from being leaped up. Attention should also be paid to sealing between the supercharger shaft 3-5 and the inverted delta rotary engine 4 and the exhaust duct 5-1.

Because the supercharger is used facing high altitude, the main components such as the filter grid 1-1, the air inlet pipeline 1-2, the exhaust pipeline 5-1 and other static components are preferably made of light materials, so that the weight of the components is reduced, and the power-weight ratio of the engine is further improved.

Since the exhaust device 5 and the turbine device 6 are both in a high temperature environment during operation, a high temperature resistant material is required.

Referring to fig. 5, as altitude increases, the engine intake air amount decreases. As the altitude increases from 0km to 6km, the engine intake air amount decreases from 0.285g to 0.136g, decreasing by 52.2%.

Referring to fig. 6, the intake air amount of the engine is reduced, which results in a reduction in working medium on the one hand and a deterioration in combustion performance on the other hand. At an altitude of 6km, the power is 20.3kW, which is reduced by 8.8kW, about 43.3%, from the ground.

Referring to fig. 7, as altitude increases, the supercharger should adjust the rotational speed to maintain stable combustion of the engine, and as altitude increases to 6km, the supercharger operating pressure ratio should be adjusted to 2.09. Referring to fig. 8, the angle adjustment rule of the guide vane of the supercharger is shown under different supercharging ratios.

Referring to fig. 9, the peak in-cylinder pressure varies at different altitudes.

As shown in fig. 5, 6, 7, 8, 9, when the altitude increases above 2000m, the engine intake air amount decreases (see fig. 5), the cylinder pressure sensor 2-4 located inside the combustion chamber 4-2 detects the decrease in cylinder pressure (see fig. 9), the engine power decays (see fig. 6), and this signal is fed back to the control casing 2-3. The control casing 2-3 obtains the regulation target of the supercharging ratio according to the regulation shown in fig. 7 (refer to fig. 7), calculates the regulation rule of the guide vane 2-1 (refer to fig. 8), and controls the guide vane to rotate.

The invention discloses an efficient axial-flow supercharging system of an inverted triangle rotor engine for aviation. The system comprises an air inlet device, a supercharger control device, an axial-flow supercharger, an inverted triangle rotor engine, an exhaust device and a turbine device. After passing through the filter grid, the incoming flow is changed by the guide vane, enters the compressor section to be decelerated and pressurized, and is further decelerated and compressed by the convergent air inlet channel to become high-pressure air. When the aviation reverse triangle rotor engine works, the low air inflow leads the engine to burn worse and the power attenuation is serious, and after the compressed air enters the engine, the heat release of the center can be effectively advanced, the combustion performance is improved, and the work efficiency of the engine is improved. Meanwhile, the tail gas is discharged and then enters the turbine device, expansion is accelerated and discharged, secondary utilization is realized, and the power output of the engine is improved.

The above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the above embodiments, one skilled in the art may make modifications and equivalents to the specific embodiments of the present invention, and any modifications and equivalents thereof without departing from the spirit and scope of the present invention are within the scope of the claims of the present invention.

Claims (10)

1. The utility model provides an aviation is with high-efficient axial-flow supercharging system of anti-triangle rotor engine, a serial communication port, including setting up air inlet unit (1) at anti-triangle rotor engine (4) air inlet, set up exhaust apparatus (5) at anti-triangle rotor engine (4) air outlet, set up axial-flow type booster (3) and booster controlling means (2) in air inlet unit (1), be provided with turbine unit (6) in exhaust apparatus (5), axial-flow type booster (3), turbine unit (6) and anti-triangle rotor engine (4) coaxial linkage, booster controlling means (2) are used for carrying out the air intake water conservancy diversion according to jar pressure measurement feedback.

2. The efficient axial-flow supercharging system of an inverted triangle rotor engine for aviation according to claim 1, wherein the supercharger control device (2) comprises guide vanes (2-1), an adjusting ring (2-2), a control casing (2-3), a cylinder pressure sensor (2-4), a connecting rod (2-5), a sliding rail (2-6), the tail end of the guide vanes (2-1) is connected with the adjusting ring (2-2) through the connecting rod (2-5), the adjusting ring (2-2) is slidingly connected on the sliding rail (2-6), the sliding rail (2-6) is circumferentially fixed on the outer side of the air inlet device (1), the cylinder pressure sensor (2-4) is arranged in a combustion chamber (4-2) of the inverted triangle rotor engine (4), the cylinder pressure sensor (2-4) is used for acquiring pressure data in the combustion chamber (4-2) and transmitting the pressure data to the control casing (2-3), and the control casing (2-3) is connected with the adjusting ring (2-2) for adjusting the angle of the guide vanes (2-1) according to the pressure data.

3. The efficient axial-flow supercharging system of the inverted triangle rotor engine for aviation according to claim 2, wherein the air inlet device (1) comprises a filter grid (1-1), an air inlet pipeline (1-2), the air inlet pipeline (1-2) is a cylindrical pipeline with an inner section gradually shrinking towards the direction, the filter grid (1-1) is connected with one end of a large section of the air inlet pipeline (2), one end of a small section of the air inlet pipeline (2) is connected with an inlet of the inverted triangle rotor engine (4), eight through holes are circumferentially formed in one end, close to the filter grid (1-1), of the air inlet pipeline (1-2) for enabling tail ends of guide vanes (2-1) to extend out of the air inlet pipeline (1-2) to be connected with an adjusting ring (2-2), and a plurality of mounting grooves are circumferentially formed in the inner wall of the air inlet pipeline (1-2) for mounting the axial-flow supercharger (3).

4. The efficient axial-flow supercharging system of the inverted triangle rotor engine for aviation according to claim 3, wherein the axial-flow supercharger (3) comprises a supercharger rotating shaft (3-5), one end of the supercharger rotating shaft (3-5) is sleeved in a hollow engine crankshaft (4-3) of the inverted triangle rotor engine (4), the other end of the supercharger rotating shaft is connected with a multi-stage rotor blade disc (3-1), a plurality of mounting grooves are formed in the rotor blade disc (3-1) in the circumferential direction, groove structures are formed in the rotor blade (3-2) and the root of a stator blade (3-3), the root of the rotor blade (3-2) is inserted into the mounting groove in the rotor blade disc (3-1) for fixing, and the root of the stator blade (3-3) is inserted into the mounting groove in the air inlet pipeline (1-2) for fixing; the number of the mounting grooves on the air inlet pipeline (1-2) is the same as that of the mounting grooves on the rotor blade disc (3-1), and the mounting grooves are arranged at intervals in a hollow manner; one side of the axial-flow type supercharger (3) is provided with a fairing (3-4), the fairing (3-4) is provided with a through hole, and the rotor blades (3-2) extend out of the fairing (3-4) from the through hole.

5. An aeronautical anti-delta rotary engine high efficiency axial flow supercharging system according to claim 4, characterized in that the clearance between the tail of the fairing (3-4) and the anti-delta rotary engine (4) is not more than 3mm.

6. The efficient axial flow supercharging system of an inverted triangle rotor engine for aviation according to claim 4, wherein the rotor blades (3-2) and the stator blades (3-3) are arranged in three stages, each stage of the stator blades (3-3) is closely arranged behind the rotor blades (3-2) of the corresponding stage, and the section of each rotor blade (3-2) is of a bent wing type structure.

7. The efficient axial-flow supercharging system of an inverted triangle rotor engine for aviation according to claim 4, wherein one end of a supercharger rotating shaft (3-5) extends out of a hollow engine crankshaft (4-3) of the inverted triangle rotor engine (4) into an exhaust device (5), two-stage turbine blades (6-2) are arranged on the supercharger rotating shaft (3-5) in the exhaust device (5) to form the turbine device (6), and the structure and the connection mode of the turbine blades (6-2) are the same as those of the rotor blades (3-2).

8. The efficient axial-flow supercharging system of the inverted triangle rotor engine for aviation according to claim 7 is characterized in that the supercharger rotating shaft (3-5) is sleeved in a hollow engine crankshaft (4-3) of the inverted triangle rotor engine (4) through a bearing, and the bearing is in interference fit with the supercharger rotating shaft (3-5); the part of the supercharger rotating shaft (3-5) entering the exhaust device (5) is supported and fixed in the exhaust device (5) through a bearing.

9. The efficient axial-flow supercharging system of an inverted triangle rotor engine for aviation according to claim 1, wherein the exhaust device (5) comprises an exhaust pipe (5-1), the exhaust pipe (5-1) is in a convergent shape with a reduced cross section, three inlets are arranged at the large cross section end of the exhaust pipe, and the three inlets of the exhaust pipe (5-1) are in airtight connection with three exhaust ports of the inverted triangle rotor engine (4).

10. The efficient axial flow supercharging system of an inverted triangle rotor engine for aviation according to claim 1, wherein the exhaust device (5) and the turbine device (6) are made of high temperature resistant materials.