CN117780502A - wake circulating wave aeroengine - Google Patents

Abstract

A wake cycle wave aircraft engine comprising: the engine casing (100), a gas compressor (200), a combustion chamber (300) and a turbine (400) which are sequentially arranged in the engine casing along the axial direction, and a rotor shaft (500) which penetrates through the gas compressor (200) and the turbine (400) along the central axis of the combustion chamber (300) are fixed in the engine casing, and the engine casing is characterized in that the combustion chamber (300) comprises a circulating wave combustion chamber (320) and an internal and external flow mixing chamber (360), and compared with a propulsion system of a traditional aeroengine, the engine provided by the invention has higher combustion efficiency.

Description

wake circulating wave aeroengine

Technical field

The invention relates to the technical fields of aviation gas turbine engines and gas turbines, and in particular to a wake circulating wave engine.

Background technique

For conventional axial flow aero engines, when the inlet air flow rate is fixed, the main ways to improve its performance, that is, to increase its ideal cycle work and improve its thermal efficiency, are to increase the compressor pressure ratio and the component efficiency of the compressor and turbine, and to improve the turbine Front gas temperature, etc. For compressors and turbines, which are impeller machines, the research on their aerodynamics and structure has been relatively in-depth, and the space for performance improvement is limited; for the gas temperature in front of the turbine, due to the limitations of turbine manufacturing materials and cooling, the improvement potential is very limited.

Patent document CN113864050 discloses a detonation supercharged aircraft engine. Refer to Figure 1, which shows the thermodynamic cycle diagram of detonation supercharged combustion (1-2-A-B-3-4), constant volume combustion (1-2-3-4) and constant pressure combustion (1-2-3b-4b). As shown in the figure, the constant volume combustion cycle using detonation supercharged mode mainly includes 5 steps: injection of fresh air and combustible gas, pre-compression, constant volume combustion and pre-expansion after completion of combustion, and discharge of high-pressure gas to the turbine. The detonation supercharged combustion cycle is compared with the constant volume combustion cycle and the constant pressure combustion cycle without shock wave supercharging. The entropy increase is minimal and the cycle work is maximized.

Contents of the invention

In order to overcome the above-mentioned shortcomings of the existing technology, a wake circulating wave engine using a new combustion method and a new combustion chamber structural design is provided, which improves the engine efficiency by changing the thermodynamic cycle method, and provides an optimized engine structural design to solve the problem of combustion chamber combustion. Problems of organization and protection.

In order to achieve the above objects, the present invention adopts the following technical solutions:

A trailing circulating wave aeroengine includes: a casing, a compressor, a combustion chamber and a turbine that are fixed in the casing and arranged in sequence along the axial direction; and the compressor and turbine are penetrated along the central axis of the combustion chamber. The rotor shaft of the turbine is characterized by,

The combustion chamber includes a circulating wave combustion chamber and an internal and external flow mixing chamber, wherein the circulating wave combustion chamber is composed of a plurality of axially extending circulating wave channels distributed in a circumferential array, and each circulating wave channel is There is a fuel nozzle and an igniter, both of which are fixed on the casing. The two ends of the circulating wave combustion chamber are sealed by the air intake guide rotor and the air outlet guide rotor respectively; there is a fuel nozzle and an igniter outside the circulating wave combustion chamber. There is a wake channel outside the combustion chamber. The upstream side of the wake channel outside the combustion chamber is provided with a wake channel regulating valve, which can control the gas flow entering the wake channel outside the combustion chamber according to the wake channel regulating device;

After the air is pressurized by the compressor, it enters the combustion chamber through the inlet end channel, and part of it enters the circulating wave combustion chamber through the air inlet on the air intake guide rotor, and is sprayed out with the fuel nozzle The fuel spray is mixed and burned in the circulating wave channel to form high-temperature gas, which is discharged into the inner and outer flow mixing chamber through the air outlet on the air outlet guide rotor, and the other part enters the combustion chamber through the accompanying flow channel adjustment valve. The outdoor following flow channel is directly discharged into the internal and external flow mixing chamber; after the high-temperature gas discharged through the gas outlet and the gas discharged through the combustion outdoor following flow channel are mixed in the internal and external flow mixing chamber, they pass through the outlet The end channel is discharged into the turbine. The gas converts part of the energy into kinetic energy in the turbine, drives the compressor through the rotor shaft, and the high-temperature gas is ejected through the turbine to generate thrust.

The air inlets and air outlets are staggeredly distributed to ensure that both ends of the inlet and outlet are closed during the combustion process of gas in the circulating wave combustion chamber.

The outlet end channel is installed downstream of the internal and external flow mixing chamber.

The transition section channel includes an inlet end channel and an outlet end channel. The inlet end channel is connected between the combustion chamber and the compressor outlet, and the outlet end channel is connected between the internal and external flow mixing chamber and the turbine.

The associated wake channel includes a circulating wave combustion chamber outer wake channel, a wake channel regulating valve and a wake channel regulating device. The outer combustion chamber outer wake channel is arranged between the circulating wave combustion chamber and the casing.

A wake channel regulating valve is arranged upstream of the combustion chamber's wake channel, which can control the gas flow entering the wake channel according to the wake channel control device; another part of the pressurized air entering the combustion chamber passes through the wake channel regulating valve, passes through the combustion chamber's wake channel, enters the internal and external flow mixing chamber, and is mixed with the high-temperature combustion gas discharged through the exhaust guide rotor before entering the turbine through the outlet end channel.

The following flow channel control device includes an incoming flow state sensor, a following flow channel gas state sensor, a control chip and a valve servo adjustment mechanism. The inflow status sensor includes an electronic gas velocity measuring device and an electronic gas pressure measuring device, which is located upstream of the air intake guide rotor and can measure the air flow pressure and flow rate at the air intake guide rotor under current working conditions. And converted into electrical signals and input into the control chip; the following flow channel gas state sensor includes an electronic gas velocity measuring device and an electronic gas pressure measuring device, which is located at the entrance of the following flow channel and can measure the following flow channel under current working conditions. The air flow pressure and flow rate are converted into electrical signals and input into the control chip; the control chip is based on the preset inflow state-travel channel state curve and calculates the current working conditions according to the input electrical signal of the inflow state sensor. The optimal flow rate of the following flow channel, thereby generating a control signal for the adjustment valve of the following flow channel; the valve servo adjustment mechanism is a mechanical transmission mechanism with a servo actuator, and adjusts the following flow according to the control signal of the control chip The target position of the control valve.

The air inlet guide rotor and the outlet air guide rotor are both equipped with air guide rotor speed regulating devices, which control the rotation speeds of the air inlet guide rotor and the outlet air guide rotor according to the incoming flow conditions from the front.

The diversion rotor speed regulating device includes an incoming flow state sensor, a rotor shaft speed sensor, a control chip and an adjustable reducer. The inflow status sensor includes an electronic gas speed measuring device and an electronic gas pressure measuring device, which is located upstream of the air intake guide rotor and can measure the air flow pressure and flow rate at the air intake guide rotor under current working conditions. And convert it into an electrical signal and input it into the control chip; the rotor shaft speed sensor can measure the rotor shaft speed under the current working condition and convert it into an electrical signal and input it into the control chip; the control chip guides based on the preset inflow status. The flow rotor speed curve calculates the optimal speed of the diversion rotor under the current working condition based on the input electrical signal from the incoming flow state sensor, and calculates the optimal reduction ratio of the adjustable reducer based on the rotor shaft speed, thereby generating The control signal of the adjustable reducer; the adjustable reducer is a mechanical transmission with a servo actuator, the input shaft is connected to the rotor shaft, and the output shaft is connected to the rotating shaft of the air intake guide rotor. According to the The control signal of the control chip adjusts the reduction ratio.

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

First, compared with the propulsion system of traditional aero engines, the combustion efficiency of this invention is higher. The calculation results show that compared with the traditional constant-pressure combustion chamber, the cycle thermal efficiency of the trailing circulating wave engine can be increased by more than 20%, and the fuel consumption rate can be reduced by more than 15% under the same thrust conditions.

Second, the rotor mass of the present invention is close to that of conventional aircraft engines, and there is no structural stability problem.

Third, the present invention adopts a fixed combustion chamber design, and conventional ignition methods are not restricted, thus avoiding the problem of difficult ignition organization.

Fourth, the present invention adopts a fixed combustion chamber design, and there are no other factors such as centrifugal force that affect combustion.

Fifth, the present invention adopts the design scheme of the wake passage outside the combustion chamber, and uses the wake to directly absorb the possible leakage airflow from the combustion chamber, which optimizes the design of the combustion chamber and improves the reliability of the overall structure.

Sixth, the present invention adopts the combustion chamber outer flow channel, which helps the cooling of the combustion chamber.

Seventh, in the present invention, the design scheme of mixing the internal and external flows of the combustion chamber makes the turbine inlet temperature more uniform, further reducing the turbine heat protection pressure.

Description of the drawings

Figure 1 is a schematic diagram of the principle of detonation supercharged combustion, where a is the pressure-volume relationship diagram of the thermodynamic cycle process, and b is the temperature-entropy relationship diagram.

Figure 2 is a schematic structural diagram and a schematic diagram of the air flow direction of the wake circulating wave aeroengine of the present invention.

Figure 3 is a schematic structural diagram of the combustion chamber and following flow channel.

Figure 4 is a schematic diagram of a single channel of the circulating wave combustion chamber.

Figure 5 is a front view of the inlet guide rotor and the outlet guide rotor, wherein a is a schematic diagram of the interface between the combustion chamber inlet and the inlet guide rotor, and b is a schematic diagram of the interface between the combustion chamber outlet and the outlet guide rotor.

Figure 6 is a front view of an embodiment of a circulating wave combustion chamber with a total of 16 circulating wave channels.

In the picture: 100 casing; 200 compressor; 300 combustion chamber; 400 turbine; 500 rotor shaft; 600 air inlet; 900 following flow channel; 310. intake guide rotor; 320. circulating wave combustion chamber; 330. exhaust Diversion rotor; 360 internal and external flow mixing chamber; 370 diversion rotor speed regulating device; 390 transition section channel; 910 wake channel adjustment valve; 920 circulating wave combustion outdoor wake channel; 930 wake channel control device; 311 air inlet port ; 321 circulating wave channel; 322 fuel nozzle; 323 igniter; 331 air outlet port; 391 inlet channel; 392 outlet channel.

Detailed ways

Typical embodiments embodying the features and advantages of the present invention will be described in detail in the following description. It should be understood that the present invention can have various changes in different embodiments without departing from the scope of the present invention, and the description and drawings are for illustrative purposes in nature and are not used to limit the scope of the present invention. invention.

In the following description of different exemplary embodiments of the present invention, reference is made to the accompanying drawings, which form a part of the present invention and in which different exemplary structures, systems and steps that can implement multiple aspects of the present invention are shown by way of example. It should be understood that other specific schemes of components, structures, exemplary devices, systems and steps can be used, and structural and functional modifications can be made without departing from the scope of the present invention. Moreover, although the terms "upstream", "downstream", "between", etc. may be used in this specification to describe different exemplary features and elements of the present invention, these terms are used herein only for convenience, such as according to the direction of the examples described in the accompanying drawings. Nothing in this specification should be construed as requiring a specific three-dimensional orientation of the structure to fall within the scope of the present invention.

Please refer to Figure 2. Figure 2 represents a schematic structural diagram and a schematic diagram of the air flow direction of a wake circulating wave aeroengine that can embody the principles of the present invention. In this exemplary embodiment, the wake circulating wave aircraft engine proposed by the present invention is explained by taking a turbojet engine in the field of aircraft engines as an example. Those skilled in the art can easily understand that in order to apply the wake circulating wave engine proposed by the present invention to other fields, various modifications, additions, substitutions, deletions or other changes can be made to the following specific embodiments. The changes are still within the scope of the principle of the wake circulating wave aeroengine proposed by the present invention.

As shown in Figure 2, the wake circulating wave aeroengine proposed by the present invention includes a casing 100, and an intake passage 600, a compressor 200, a combustion chamber 300, a wake passage 900, Turbine 400, rotor shaft 500, other accessory transmission devices 700 and tail nozzle 800. Referring to Figures 2 to 6, Figure 2 representatively shows the airflow direction in the above-mentioned wake circulating wave aeroengine; Figure 3 representatively shows the combustion chamber 300 and accompanying flow of the above-mentioned wake circulating wave aeroengine. A schematic structural diagram of the flow channel 900; Figure 4 representatively shows a schematic layout of the single circulating wave channel 321; Figure 5 representatively shows a front view of the air inlet guide rotor 310 and the outlet air guide rotor 330, where, a is a schematic diagram of the interface between the combustion chamber inlet and the air inlet guide rotor 310, and b is a schematic diagram of the interface between the combustion chamber outlet and the outlet air guide rotor 330. Figure 6 represents a front view of an embodiment of a circulating wave combustion chamber 320. The main structures and working principles of the wake circulating wave aeroengine proposed by the present invention will be described in detail below with reference to the accompanying drawings.

As shown in FIGS. 2 to 6 , in this embodiment, the combustion chamber 300 is arranged between the compressor 200 and the gas turbine 400. As shown in FIG. 3 , the combustion chamber 300 mainly includes an inlet guide rotor 310, an outlet guide rotor 330, a circulating wave combustion chamber 320, an inner and outer flow mixing chamber 360, a guide rotor speed regulating device 370, and a transition section channel 390. Specifically, in this embodiment, the inlet guide rotor 310 and the outlet guide rotor 330 are rotatably arranged on the rotor shaft 500, and their rotation center axes coincide with the rotor shaft 500. The inlet guide rotor 310 and the outlet guide rotor 330 are sealed at the inlet and outlet of the circulating wave combustion chamber 320, respectively. The inlet guide rotor 310 near the inlet of the circulating wave combustion chamber is provided with an inlet port 311, and the outlet guide rotor 330 near the outlet of the circulating wave combustion chamber 320 is provided with an outlet port 331, and the inlet port 311 and the outlet port 332 are staggered in the circumferential direction around the central axis to ensure that the inlet and outlet ends of the gas are closed during the combustion process in the circulating wave combustion chamber 320. The rotation speeds of the inlet guide rotor 310 and the outlet guide rotor 330 are adjusted by the guide rotor speed regulating device 370 of each guide rotor.

The circulating wave combustion chamber 320 is composed of a plurality of circulating wave channels 321 that are stationary relative to the casing 100 and are arranged around a central axis. They are distributed in a radial circumferential array and form multiple channels extending along the axial direction of the combustion chamber 300 . Each circulating wave channel 321 is provided with a fuel nozzle 322 and an igniter 323 to ignite the gas entering the circulating wave channel 321 for constant volume combustion.

The transition section channel 390 includes an inlet end channel 391 and an outlet end channel 392. The inlet channel 391 is connected between the combustion chamber 300 and the outlet of the compressor 200, so that the gas compressed by the compressor 200 can enter the combustion chamber 300 through the inlet channel 391. The outlet channel 392 is connected between the inner and outer flow mixing chamber 360 and the air inlet of the turbine 400, so that the gas mixed in the inner and outer flow mixing chamber 360 is discharged from the air outlet port 331 and the combustion chamber companion flow channel 910 through the outlet channel 392. Enter the Turbo 400.

The wake passage 900 mainly includes a wake passage adjustment valve 910, a wake passage outside the circulating wave combustion chamber 920, and a wake passage control device 930. The wake passage 920 outside the combustion chamber is provided between the circulating wave combustion chamber 320 and the casing 100. The wake passage adjustment valve 910 is provided upstream of the wake passage. The geometric position of the valve 910 is controlled according to the instructions of the wake passage control device 930 to adjust Gas flow through flow channel 920.

As shown in Figures 3 and 4, in this embodiment, the air inlet 600 is arranged upstream of the compressor 200 around the rotor shaft 500, and the air outlet of the air inlet 600 is connected to the air inlet of the compressor 200. The air outlet of the compressor 200 is connected to the combustion chamber 300 through the inlet end channel 391. The compressor 200 is selected as a 10-stage axial flow compressor 200. In this embodiment, 16 circulation wave channels 321 are fixed on the engine casing 100, distributed in a radial circumferential array, forming 16 channels extending axially along the combustion chamber 300. The air inlet guide rotor 310 and the air outlet guide rotor 330 both adopt a sealing method combining a comb tooth sealing structure and an oil seal applied to aircraft engines. The air inlet of the turbine 400 is connected to the internal and external flow mixing chamber 360 through the outlet end channel 392, and the turbine 400 is selected as a three-stage turbine. It should be noted that in other exemplary embodiments of the present invention, the above-mentioned structures such as the air inlet duct 600, the compressor 200 and the turbine 400, as well as the sealing methods of the air inlet guide rotor 310 and the air outlet guide rotor 330 may all adopt existing structures and other methods, and the number of circulating wave channels 321 in the circulating wave combustion chamber 320 is not limited to this.

Based on the above description of the exemplary embodiments of the present invention, the working process of the wake circulation wave aircraft engine proposed by the present invention is roughly as follows:

As shown in Figure 2, air enters the engine through the intake passage 600. After being pressurized by the compressor 200, it enters the combustion chamber 300 through the inlet passage 391. After the gas enters the combustion chamber 300, a part of the gas enters the circulating wave channel 321 of the circulating wave combustion chamber 320 through the air inlet 311 on the intake guide rotor 310, and fully mixes with the fuel spray ejected from the fuel nozzle 322. Mixing, the gas in the circulating wave channel 321 undergoes the action of the complex wave system, repressurization, constant volume combustion of the mixed gas, and pre-expansion of the gas to form high-temperature gas. During the combustion process, the air inlets 311 at both ends of the circulating wave channel 321 Closed with the gas outlet 331, the high-temperature gas is discharged into the internal and external flow mixing chamber 360 through the gas outlet 331 on the gas outlet guide rotor 330; the other part of the gas enters the following flow channel 920 outside the combustion chamber through the following flow channel adjustment valve 910, and then is directly discharged into the internal and external flow. Flow mixing chamber 360. The high-temperature gas discharged from the gas outlet 311 and the gas discharged from the following flow channel 920 outside the combustion chamber are mixed in the inner and outer flow mixing chamber 360 , and are further mixed therein through the outlet end channel 392 and discharged into the turbine 400 . The gas converts part of the energy into the kinetic energy of the turbine 400 in the turbine, and drives the compressor 200 and other accessory transmission devices 700 through the rotor shaft 500. The gas is discharged from the turbine 400 and enters the tail nozzle 800, further fully expands, and is ejected at high speed to generate thrust. .

It should be pointed out that, refer to Figure 1, which shows the detonation supercharged combustion (1-2-A-B-3-4), constant volume combustion (1-2-3-4) and constant pressure combustion (1- 2-3b-4b) thermodynamic cycle diagram, as shown in the figure, the constant volume combustion cycle using detonation supercharging method mainly includes 5 steps: injection of fresh air and combustible gas, pre-compression, constant volume combustion and completion of combustion. Pre-expand and discharge high-pressure gas to the turbine. The detonation pressurized combustion cycle is compared with the constant volume combustion cycle and the constant pressure combustion cycle without shock wave pressurization. The entropy increase is minimum and the cycle work is maximum. Compared with traditional aero engines, the combustion efficiency of this invention is higher. The calculation results show that compared with the traditional constant-pressure combustion chamber, the cycle thermal efficiency of the trailing circulating wave engine can be increased by more than 20%, and the fuel consumption rate can be reduced by more than 15% under the same thrust conditions.

It should be pointed out that the mass of the rotor in the present invention is close to that of a traditional aeroengine, and there is no big gap in terms of structural stability compared with traditional aeroengines. In addition, the present invention adopts a design solution of fixed combustion chamber 321, which does not impose any restrictions on conventional ignition methods and eliminates ignition organization problems. The present invention is provided with a wake passage 900, which uses the wake outside the combustion chamber to help cool the combustion chamber and directly absorbs possible leakage airflow from the combustion chamber, thereby solving the problem of gas leakage from the combustion chamber. In the present invention, the wake discharged from the wake channel 920 outside the combustion chamber and the high-temperature gas discharged from the outlet 331 on the outlet guide rotor 330 are mixed in the inner and outer flow mixing chamber 360, so that the inlet temperature of the turbine 400 is more uniform, and further Reduced turbine thermal protection pressure. In summary, the wake circulating wave aeroengine proposed by the present invention proposes a new combustion chamber configuration design. Compared with the existing methods of improving aeroengine performance, the above design does not require the turbine to be upgraded. The front inlet temperature may improve the efficiency of the impeller machinery, and the structure is simpler and more reliable.

The exemplary embodiments of the wake circulating wave aeroengine proposed by the present invention have been described and/or illustrated in detail above. However, embodiments of the invention are not limited to the specific embodiments described herein; rather, components and/or steps of each embodiment may be used independently and separately from other components and/or steps described herein. Each component and/or step of one embodiment may also be used in combination with other components and/or steps of other embodiments. When introducing elements/components/etc. described and/or illustrated herein, the terms "a," "an," "the above," etc. are used to indicate that there are one or more elements/components/etc. The terms "comprises", "including" and "having" are used to indicate an open inclusion and mean that there may be additional elements/components/etc. in addition to the listed elements/components/etc.

Although the wake circulating wave aeroengine proposed by the present invention has been described according to different specific embodiments, those skilled in the art will recognize that the implementation of the present invention can be modified within the spirit and scope of the claims.

Claims (5)

1. A wake circulating wave aeroengine, including: a casing (100), a compressor (200), a combustion chamber (300) and a turbine (400) fixed in the casing and arranged in sequence along the axial direction, and The rotor shaft (500) penetrating the compressor (200) and the turbine (400) along the central axis of the combustion chamber (300) is characterized by: The combustion chamber (300) includes a circulating wave combustion chamber (320) and an internal and external flow mixing chamber (360), wherein the circulating wave combustion chamber (320) is composed of a plurality of axially extending cylindrical chambers distributed in a circumferential array. It consists of circulating wave channels (321). Each circulating wave channel (321) is provided with a fuel nozzle (322) and an igniter (323), and both are fixed on the casing (100). The circulating wave combustion Both ends of the chamber (320) are sealed by the air inlet guide rotor (310) and the outlet air guide rotor (330) respectively; an external combustion chamber following flow channel (920) is provided outside the circulating wave combustion chamber (320), which There is a wake channel regulating valve (910) provided upstream of the combustion chamber's out-of-combustor flow channel (920), which can control the gas flow entering the combustion chamber's out-of-combustion flow channel (920) according to the trace flow channel regulating device (930); After being pressurized by the compressor (200), the air enters the combustion chamber (300) through the inlet end channel (391), a portion of the air enters the circulating wave combustion chamber (320) through the air inlet port (311) on the air inlet guide rotor (310), and is mixed with the fuel spray sprayed by the fuel nozzle (322) in the circulating wave channel (321) to form high-temperature combustion gas after combustion reaction, and is discharged into the internal and external flow mixing chamber (360) through the air outlet port (331) on the air outlet guide rotor (330), and the other portion of the air is discharged through the accompanying flow channel regulating valve (910) ) enters the combustion chamber outer accompanying flow channel (920) and is directly discharged into the inner and outer flow mixing chamber (360); the high-temperature combustion gas discharged through the gas outlet (331) and the gas discharged through the combustion chamber outer accompanying flow channel (920) are mixed in the inner and outer flow mixing chamber (360) and then discharged into the turbine (400) through the outlet end channel (392), and a part of the energy of the gas is converted into kinetic energy in the turbine (400), and the compressor (200) is driven by the rotor shaft (500), and the high-temperature combustion gas is ejected through the turbine (400) to generate thrust. 2. The wake circulation wave aircraft engine according to claim 1 is characterized in that the inlet guide rotor (310) and the outlet guide rotor (330) are both provided with a guide rotor speed regulating device (370) to control the rotation speed of the inlet guide rotor (310) and the outlet guide rotor (330) according to the state of the front incoming flow. 3. The following circulating wave aeroengine according to claim 2, characterized in that the diversion rotor speed regulating device (370) includes an incoming flow state sensor (371), a rotor shaft speed sensor (372), and a control chip. (373) and adjustable reducer (374); The inflow status sensor (371) includes an electronic gas speed measuring device and an electronic gas pressure measuring device, which is used to measure the air flow pressure and flow rate at the inlet and outlet under the current working conditions, and converts it into an electrical signal and inputs it into the diversion rotor control chip. (373); The rotor shaft speed sensor (372) is used to measure the speed of the rotor shaft (500) under current working conditions, and convert it into an electrical signal for input to the diversion rotor control chip (373); The diversion rotor control chip (373) calculates the optimal speed of the diversion rotor under the current working conditions based on the preset incoming flow state-diversion rotor speed curve and the input inflow status sensor electrical signal, and calculates the optimal speed of the diversion rotor according to the rotor shaft Rotation speed, calculate the optimal reduction ratio of the adjustable reducer (374), thereby generating a control signal for the adjustable reducer (374); The adjustable reducer (374) is a mechanical transmission with a servo actuator, the input shaft of which is connected to the rotor shaft (500), and the output shaft of which is connected to the rotating shaft of the intake guide rotor (310), and the reduction ratio is adjusted according to the control signal of the guide rotor control chip (373). 4. The following circulating wave aeroengine according to claim 1 or 2, characterized in that the air inlet (311) and the air outlet (331) are staggered to ensure that the gas circulates in the circulating wave combustion chamber (320). ) during the combustion process, both ends of the inlet and outlet are closed. 5. The wake circulating wave aeroengine according to claim 1, characterized in that the wake channel control device (930) includes an incoming flow state sensor (931), a wake channel gas state sensor (932), and a wake channel gas state sensor (932). Flow channel control chip (933) and valve servo adjustment mechanism (934); The incoming flow sensor (931) comprises an electronic gas velocity measuring device and an electronic gas pressure measuring device, and is located upstream of the intake guide rotor (310), and is used to measure the airflow pressure and flow velocity at the intake guide rotor under the current working condition, and convert them into electrical signals to be input into the accompanying flow channel control chip (933); The wake channel gas state sensor (932) includes an electronic gas speed measuring device and an electronic gas pressure measuring device, which is located at the entrance of the wake channel (920) outside the combustion chamber and is used to measure the wake channel outside the combustion chamber under the current working conditions. (920) air flow pressure and flow rate, and convert them into electrical signals and input them into the accompanying flow channel control chip (933); The wake channel control chip (933) calculates the maximum value of the wake channel (920) outside the combustion chamber under the current working conditions based on the preset incoming flow state - wake channel state curve and the input incoming flow state sensor electrical signal. Optimal flow, thereby generating a control signal for the accompanying flow channel regulating valve (910); The valve servo adjustment mechanism (934) is a mechanical transmission mechanism with a servo actuator, and adjusts the target position of the accompanying channel control valve (910) according to the control signal of the accompanying channel control chip.