CN117780502A - Accompanying flow 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

Accompanying flow circulating wave aeroengine

Technical Field

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

Background

For a conventional axial-flow aeroengine, under the condition of fixed inlet air flow, ways of improving the performance, namely ideal circulating work and heat efficiency of the conventional axial-flow aeroengine are mainly to improve the pressure ratio of a compressor, the component efficiency of the compressor and a turbine, the temperature of gas before the turbine and the like. For the compressor and the turbine, which belong to impeller machinery, the pneumatic and structural researches of the compressor and the turbine are deeper, and the performance improvement space is limited; for the turbine front gas temperature, the lifting potential is very limited due to the limitations of turbine manufacturing materials and cooling.

Patent document CN113864050 discloses a detonation supercharged aeroengine, referring to fig. 1, fig. 1 shows thermodynamic cycle diagrams 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), and as shown, the constant volume combustion cycle adopting the detonation supercharged mode mainly comprises 5 steps: fresh air and combustible gas are injected, precompressed, burned at constant volume and pre-expanded after combustion is completed, and high pressure gas is exhausted to the turbine. The cycle of knock boost combustion is compared to a constant volume combustion cycle without shock boost and a constant pressure combustion cycle. The entropy increase is minimum and the cyclic work is maximum.

Disclosure of Invention

In order to overcome the defects in the prior art, the wake circulation wave engine adopting the novel combustion mode and the novel combustion chamber structural design is provided, the engine efficiency is improved by changing the thermodynamic circulation mode, and the optimized engine structural design is provided, so that the problems of combustion organization and protection of the combustion chamber are solved.

In order to achieve the above purpose, the present invention adopts the following technical scheme:

a wake cycle wave aircraft engine comprising: the engine case, the compressor, the combustion chamber and the turbine which are fixed in the engine case and are sequentially arranged along the axial direction, and the rotor shaft which penetrates through the compressor and the turbine along the central axis of the combustion chamber are characterized in that,

the combustion chamber comprises a circulating wave combustion chamber and an internal and external flow mixing chamber, wherein the circulating wave combustion chamber consists of a plurality of circulating wave channels which are distributed in a circumferential array and extend along the axial direction, each circulating wave channel is provided with a fuel nozzle and an igniter and is fixed on the casing, and two ends of the circulating wave combustion chamber are respectively sealed by an air inlet diversion rotor and an air outlet diversion rotor; the circulating wave combustion chamber is provided with a combustion chamber outside wake channel, the upstream of the combustion chamber outside wake channel is provided with a wake channel adjusting valve, and the gas flow entering the combustion chamber outside wake channel can be controlled according to the wake channel adjusting device;

after being pressurized by the air compressor, air enters the combustion chamber through an inlet end channel, one part of the air enters the circulating wave combustion chamber through an air inlet on the air inlet guide rotor and is mixed with fuel spray sprayed by the fuel nozzle in the circulating wave channel for combustion reaction to form high-temperature fuel gas, the high-temperature fuel gas is discharged into the inner and outer flow mixing chamber through an air outlet on the air outlet guide rotor, and the other part of the high-temperature fuel gas enters the combustion chamber through an accompanying channel adjusting valve and enters an accompanying channel outside the combustion chamber and is directly discharged into the inner and outer flow mixing chamber; after being mixed in the internal and external flow mixing chamber, the high-temperature gas discharged through the gas outlet and the gas discharged through the combustion chamber outside the accompanying flow channel are discharged into the turbine through the outlet end channel, part of energy of the gas is converted into kinetic energy in the turbine, the gas drives the gas compressor through the rotor shaft, and the high-temperature gas is sprayed out through the turbine to generate thrust.

The air inlets and the air outlets are distributed in a staggered manner, so that gas is ensured to be sealed at two ends of an inlet and an outlet in the combustion process in the circulating wave combustion chamber.

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

The transition section channel comprises an inlet end channel and an outlet end channel, wherein the inlet end channel is communicated between the combustion chamber and the outlet of the compressor, and the outlet end channel is communicated between the internal and external flow mixing chamber and the turbine.

The associated flow channel comprises a circulating wave combustion chamber outdoor flow channel, a flow channel regulating valve and a flow channel regulating device. The combustion chamber outdoor accompanying flow channel is arranged between the circulating wave combustion chamber and the casing.

The upstream of the combustion chamber outdoor wake channel is provided with a wake channel regulating valve which can control the flow of gas entering the wake channel according to the wake channel regulating device; and the other part of pressurized air entering the combustion chamber passes through the accompanying flow channel regulating valve, passes through the outside accompanying flow channel of the combustion chamber, enters the inside and outside flow mixing chamber, is mixed with high-temperature fuel gas discharged by the air outlet flow guiding rotor, and enters the turbine through the outlet end channel.

The accompanying flow channel regulating and controlling device comprises an incoming flow state sensor, an accompanying flow channel gas state sensor, a control chip and a valve servo regulating mechanism. The incoming flow state sensor comprises an electronic gas speed measuring device and an electronic gas pressure measuring device, is positioned at the upstream of the air inlet diversion rotor, can measure the air flow pressure and the air flow velocity at the air inlet diversion rotor under the current working condition, and is converted into an electric signal to be input into the control chip; the gas state sensor of the accompanying flow channel comprises an electronic gas speed measuring device and an electronic gas pressure measuring device, is positioned at the inlet of the accompanying flow channel, can measure the gas flow pressure and the gas flow rate of the accompanying flow channel under the current working condition, and is converted into an electric signal to be input into the control chip; the control chip calculates the optimal flow of the accompanying flow channel under the current working condition based on a preset incoming flow state-accompanying flow channel state curve according to the input incoming flow state sensor electric signal, so as to generate a control signal for the regulating valve of the accompanying flow channel; the valve servo regulating mechanism is a mechanical transmission mechanism with a servo actuator, and the target position of the valve is controlled by the accompanying flow channel according to the control signal of the control chip.

The air inlet diversion rotor and the air outlet diversion rotor are respectively provided with a diversion rotor speed regulating device, and the rotating speeds of the air inlet diversion rotor and the air outlet diversion rotor are controlled according to the forward incoming flow state.

The diversion rotor speed regulating device comprises an incoming flow state sensor, a rotor shaft rotating speed sensor, a control chip and an adjustable speed reducer. The incoming flow state sensor comprises an electronic gas speed measuring device and an electronic gas pressure measuring device, is positioned at the upstream of the air inlet diversion rotor, can measure the air flow pressure and the air flow velocity at the air inlet diversion rotor under the current working condition, and is converted into an electric signal to be input into the control chip; the rotor shaft rotating speed sensor can measure the rotating speed of the rotor shaft under the current working condition and convert the rotating speed into an electric signal to be input into the control chip; the control chip calculates the optimal rotation speed of the diversion rotor under the current working condition based on a preset incoming flow state-diversion rotor rotation speed curve according to an input incoming flow state sensor electric signal, and calculates the optimal reduction ratio of the adjustable speed reducer according to the rotation speed of the rotor shaft, so as to generate a control signal for the adjustable speed reducer; the adjustable speed reducer is a mechanical speed changer with a servo actuator, an input shaft is connected to a rotor shaft, an output shaft is connected to a rotating shaft of the air inlet diversion rotor, and the speed reduction ratio is adjusted according to a control signal of the control chip.

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

First, the present invention provides for higher combustion efficiency than conventional aircraft engine propulsion systems. The calculation result shows that: compared with the traditional constant pressure combustion chamber, the cycle thermal efficiency of the wake cycle wave engine can be improved by more than 20%, and the fuel consumption rate is reduced by more than 15% under the same thrust condition.

Second, the rotor quality of the invention is similar to the traditional aeronautical engine, and the invention has no structural stability problem

Third, the invention adopts the design scheme of the fixed combustion chamber, the conventional ignition mode is not limited, and the problem of difficult ignition organization is avoided

Fourth, the invention adopts the design scheme of the fixed combustion chamber, and does not have other factors such as centrifugal force and the like to influence the combustion

Fifth, the invention adopts the design scheme of the flow channel outside the combustion chamber, adopts the flow to directly absorb the possible leakage air flow of the combustion chamber, optimizes the design of the combustion chamber and improves the reliability of the whole structure

Sixth, the present invention employs a combustion chamber outside the wake passage while facilitating cooling of the combustion chamber.

Seventh, in the invention, the design scheme of mixing the internal and external flows of the combustion chamber ensures that the inlet temperature of the turbine is more uniform, and the heat-proof pressure of the turbine is further reduced

Drawings

Fig. 1 is a schematic diagram of the principle of detonation supercharged combustion, wherein a is a pressure-volume relation diagram of a thermodynamic cycle process, and b is a temperature-entropy relation diagram.

Fig. 2 is a schematic structural view and a schematic airflow direction view of the wake circulating wave aero-engine of the present invention.

FIG. 3 is a schematic view of the structure of the combustion chamber and the accompanying flow channel

Figure 4 is a single-pass schematic diagram of a circulating wave combustor,

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

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

In the figure: 100 cases; a 200 compressor; a 300 combustion chamber; a 400 turbine; 500 rotor shaft; 600 inlet channels; 900 accompaniment flow channel; 310. an air inlet diversion rotor; 320. a circulating wave combustion chamber; 330. an air outlet diversion rotor; 360 internal and external flow mixing chambers; 370 diversion rotor speed regulating device; 390 transition section passage; 910 the companion flow channel mediates the valve; 920 circulating wave combustion chamber outdoor wake channel; 930 an associated flow channel regulation device; 311 air inlet port; 321 a circulating wave channel; 322 fuel nozzles; 323 igniter; 331 outlet ports; 391 inlet end channels; 392 outlet end passage.

Detailed Description

Exemplary embodiments that embody features and advantages of the present invention are described in detail in the following description. It will be understood that the invention is capable of various modifications in various embodiments, all without departing from the scope of the invention, and that the description and drawings are intended to be illustrative in nature and not to be limiting.

In the following description of various exemplary embodiments of the invention, reference is made to the accompanying drawings, which form a part hereof, and in which are shown by way of illustration various exemplary structures, systems, and steps in which aspects of the invention may be practiced. It is to be understood that other specific arrangements of parts, structures, example devices, systems, and steps may be utilized and structural and functional modifications may be made without departing from the scope of the present invention. Moreover, although the terms "upstream," "downstream," "between," and the like may be used in this description to describe various example features and elements of the invention, these terms are used herein for convenience only, e.g., in accordance with the orientation of the examples depicted in the drawings. Nothing in this specification should be construed as requiring a particular three-dimensional orientation of the structure in order to fall within the scope of the invention.

Referring to fig. 2, a schematic structural diagram and a schematic airflow direction diagram of an associated flow circulating wave aero-engine capable of embodying the principles of the present invention are representatively provided in fig. 2. In this exemplary embodiment, the wake circulation wave aero-engine proposed by the present invention is described by taking a turbojet engine in the aero-engine field as an example. Those skilled in the art will readily appreciate that various modifications, additions, substitutions, deletions, or other changes may be made to the specific embodiments described below for use in other applications of the present invention, while remaining within the principles of the present invention.

As shown in fig. 2, the wake circulation wave aero-engine provided by the invention comprises a casing 100, and an air inlet channel 600, a gas compressor 200, a combustion chamber 300, a wake channel 900, a turbine 400, a rotor shaft 500, other accessory transmission devices 700 and a tail nozzle 800 which are fixed in the casing 100 in sequence. Referring to fig. 2-6 in combination, the airflow direction in the above-described wake cycle wave aircraft engine is representatively illustrated in fig. 2; FIG. 3 representatively illustrates a schematic view of the combustion chamber 300 and wake passage 900 of the wake cycle wave aircraft engine described above; fig. 4 representatively illustrates a schematic view of the arrangement within the single-cycle wave channel 321; fig. 5 representatively illustrates a front view of an inlet inducer rotor 310 and an outlet inducer rotor 330, where a is a schematic view of the interface of the combustion chamber inlet and inlet inducer rotor 310 and b is a schematic view of the interface of the combustion chamber outlet and outlet inducer rotor 330. Fig. 6 representatively illustrates a front view of an embodiment of a circulating wave combustion chamber 320. The main structure and the working principle of the wake circulating wave aero-engine provided by the invention are described in detail below with reference to the accompanying drawings.

As shown in fig. 2 to 6, in the present embodiment, the combustor 300 is disposed 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 regulator 370, and a transition section channel 390. Specifically, in the present embodiment, the inlet guide rotor 310 and the outlet guide rotor 330 are rotatably disposed on the rotor shaft 500, and the rotation center axes thereof coincide with the rotor shaft 500. The air inlet guide rotor 310 and the air outlet guide rotor 330 are respectively sealed at the inlet and the outlet of the circulating wave combustion chamber 320, the air inlet guide rotor 310 close to the inlet of the circulating wave combustion chamber is provided with an air inlet port 311, the air outlet guide rotor 330 close to the outlet of the circulating wave combustion chamber 320 is provided with an air outlet port 331, the air inlet port 311 and the air outlet port 332 are staggered in the circumferential direction around the central shaft, and the two ends of the inlet and the outlet of the gas are sealed in the combustion process in the circulating wave combustion chamber 320. The rotational speeds of the inlet inducer 310 and the outlet inducer 330 are regulated by inducer speed regulation means 370 of the respective inducer.

The circulating wave combustion chamber 320 is composed of a plurality of circulating wave channels 321 which are arranged around the central shaft and are stationary relative to the casing 100, and are distributed in radial circumferential arrays to form a plurality of channels extending along the axial direction of the combustion chamber 300. Each circulating wave channel 321 is internally 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 port 391 communicates between the combustion chamber 300 and the outlet of the compressor 200, so that the gas compressed by the compressor 200 enters the combustion chamber 300 through the inlet port 391. The outlet port channel 392 communicates between the inner and outer flow mixing chamber 360 and the air inlet of the turbine 400 for the mixed gas discharged into the inner and outer flow mixing chamber 360 from the outlet port 331 and the combustion chamber outer flow channel 910 to enter the turbine 400 from the outlet port channel 392.

The wake channel 900 mainly comprises a wake channel adjusting valve 910, a circulating wave combustion chamber outdoor wake channel 920 and a wake channel adjusting device 930. The combustion chamber outside the wake channel 920 is disposed between the circulating wave combustion chamber 320 and the casing 100, the wake channel adjusting valve 910 is disposed at the upstream of the wake channel, and the geometric position of the valve 910 is controlled according to the instruction of the wake channel adjusting device 930, so as to adjust the gas flow through the wake channel 920.

As shown in fig. 3 and 4, in the present embodiment, an intake passage 600 is provided upstream of the compressor 200 around the rotor shaft 500, and an outlet of the intake passage 600 communicates with an inlet of the compressor 200. The gas outlet of the compressor 200 communicates with the combustion chamber 300 through an inlet port channel 391. Wherein the compressor 200 is selected from 10-stage axial flow compressors 200. In this embodiment, 16 circulating wave channels 321 are fixed on the engine casing 100 and distributed in radial circumferential arrays to form 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 mode of combining a comb seal structure and an oil seal, which are applied to an aeroengine. The inlet of the turbine 400 is connected to the internal and external flow mixing chamber 360 through the outlet port 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 structures of the air inlet 600, the air compressor 200, the turbine 400, and the sealing manner of the air inlet guide rotor 310 and the air outlet guide rotor 330 may be any conventional structures or other manners, and the number of the circulating wave channels 321 in the circulating wave combustion chamber 320 is not limited thereto.

Based on the above description of the exemplary embodiments of the present invention, the workflow of the wake cycle wave aircraft engine proposed by the present invention is approximately as follows:

as shown in fig. 2, air enters the engine through the intake port 600, is pressurized by the compressor 200, and then enters the combustion chamber 300 through the inlet port 391. After the gas enters the combustion chamber 300, a part of the gas enters a circulating wave channel 321 of the circulating wave combustion chamber 320 through an air inlet 311 on an air inlet guide rotor 310 and is fully mixed with fuel oil spray sprayed by a fuel oil nozzle 322, and the gas is subjected to the action of a complex wave system in the circulating wave channel 321 to generate re-pressurization, constant volume combustion of mixed gas and pre-expansion of fuel gas to form high-temperature fuel gas, wherein the air inlets 311 and the air outlets 331 at two ends of the circulating wave channel 321 are closed in the combustion process, and the high-temperature fuel gas is discharged into an inner-outer flow mixing chamber 360 through the air outlets 331 on an air outlet guide rotor 330; another portion of the gas passes through the flow channel adjustment flap 910 into the combustion chamber outer flow channel 920 and then directly into the inner and outer flow mixing chamber 360. The high temperature gas discharged from the gas outlet 311 is mixed with the gas discharged from the combustion chamber outside-accompanying flow passage 920 in the inside-outside flow mixing chamber 360, and is further mixed therein through the outlet end passage 392 and discharged to the turbine 400. The gas converts a part of energy into kinetic energy of the turbine 400 in the turbine, drives the compressor 200 and other accessory transmission devices 700 through the rotor shaft 500, and is discharged from the turbine 400 and enters the tail nozzle 800 to be further fully expanded, and is ejected at a high speed to generate thrust.

It should be noted that, referring to fig. 1, fig. 1 shows a 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), and as shown in the figure, the constant volume combustion cycle adopting the detonation supercharging mode mainly comprises 5 steps: fresh air and combustible gas are injected, precompressed, burned at constant volume and pre-expanded after combustion is completed, and high pressure gas is exhausted to the turbine. The cycle of knock boost combustion is compared to a constant volume combustion cycle without shock boost and a constant pressure combustion cycle. The entropy increase is minimum and the cyclic work is maximum. Compared with the traditional aeroengine, the combustion efficiency of the invention is higher. The calculation result shows that: compared with the traditional constant pressure combustion chamber, the cycle thermal efficiency of the wake cycle wave engine can be improved by more than 20%, and the fuel consumption rate is reduced by more than 15% under the same thrust condition.

It should be noted that the rotor quality in the present invention is close to that of a conventional aeroengine, and there is no large gap in terms of structural stability problems compared to the conventional aeroengine. In addition, the design scheme of the fixed combustion chamber 321 is adopted in the invention, so that the conventional ignition mode is not limited, and the ignition organization problem is avoided. The invention is provided with the accompanying flow channel 900, and the accompanying flow outside the combustion chamber is adopted to help cool the combustion chamber and directly absorb the possible external leakage flow of the combustion chamber, so that the problem of gas leakage of the combustion chamber is solved. The present invention provides the wake flow discharged from the combustion chamber outside wake flow channel 920 and the high temperature gas discharged from the gas outlet 331 on the gas outlet guiding rotor 330 are mixed in the inside and outside flow mixing chamber 360, so that the inlet temperature of the turbine 400 is more uniform, and the turbine heat-proof pressure is further reduced.

Exemplary embodiments of the present invention proposed wake cycle wave aircraft engine are described and/or illustrated in detail above. Embodiments of the invention are not limited to the specific embodiments described herein, but rather, components and/or steps of each embodiment may be utilized independently and separately from other components and/or steps described herein. Each component and/or each step of one embodiment may also be used in combination with other components and/or steps of other embodiments. When introducing elements/components/etc. that are described and/or illustrated herein, the terms "a," "an," and "the" are intended to mean that there are one or more of the elements/components/etc. The terms "comprising," "including," and "having" are intended to be inclusive and mean that there may be additional elements/components/etc., in addition to the listed elements/components/etc.

While the present invention has been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.

Claims (5)

1. A wake cycle wave aircraft engine comprising: the engine case (100), a compressor (200), a combustion chamber (300) and a turbine (400) which are fixed in the engine case and are sequentially arranged along the axial direction, and a rotor shaft (500) which penetrates through the compressor (200) and the turbine (400) along the central axis of the combustion chamber (300) are characterized in that,

the combustion chamber (300) comprises a circulating wave combustion chamber (320) and an internal and external flow mixing chamber (360), wherein the circulating wave combustion chamber (320) is formed by a plurality of circulating wave channels (321) which are distributed in a circumferential array and extend along the axial direction, each circulating wave channel (321) is provided with a fuel nozzle (322) and an igniter (323) and is fixed on the casing (100), and two ends of the circulating wave combustion chamber (320) are respectively sealed by an air inlet guide rotor (310) and an air outlet guide rotor (330); a combustion chamber outside the circulating wave combustion chamber (320) is provided with a combustion chamber outside the combustion chamber, a flow channel regulating valve (910) is arranged at the upstream of the flow channel outside the combustion chamber (920), and the gas flow entering the flow channel outside the combustion chamber (920) can be controlled according to a flow channel regulating device (930);

after being pressurized by the compressor (200), air enters the combustion chamber (300) through an inlet end channel (391), one part of the air enters the circulating wave combustion chamber (320) through an inlet (311) on the air inlet guide rotor (310), and is mixed with fuel spray sprayed by the fuel nozzle (322) in the circulating wave channel (321) for combustion reaction to form high-temperature fuel gas, the high-temperature fuel gas is discharged into the inner and outer flow mixing chamber (360) through an air outlet (331) on the air outlet guide rotor (330), and the other part of the high-temperature fuel gas enters the combustion chamber outside the accompanying flow channel (920) through the accompanying flow channel regulating valve (910) and is directly discharged into the inner and outer flow mixing chamber (360); after being mixed in the internal and external flow mixing chamber (360), the high-temperature fuel gas discharged through the gas outlet (331) and the gas discharged through the combustion chamber outside accompanying flow channel (920) are discharged into the turbine (400) through the outlet end channel (392), part of energy of the gas is converted into kinetic energy in the turbine (400), the gas drives the gas compressor (200) through the rotor shaft (500), and the high-temperature fuel gas is sprayed out through the turbine (400) to generate thrust.

2. The wake cycle wave aeroengine as claimed in claim 1, wherein the air inlet guide rotor (310) and the air outlet guide rotor (330) are respectively provided with a guide rotor speed regulating device (370), and the rotational speeds of the air inlet guide rotor (310) and the air outlet guide rotor (330) are controlled according to the forward incoming flow state.

3. The wake cycle wave aircraft engine of claim 2, wherein the inducer rotor timing device (370) comprises an incoming flow condition sensor (371), a rotor shaft speed sensor (372), a control chip (373) and an adjustable speed reducer (374);

the incoming flow state sensor (371) comprises an electronic gas speed measuring device and an electronic gas pressure measuring device, and is used for measuring the pressure and the flow rate of the air flow at the inlet and the outlet under the current working condition, converting the pressure and the flow rate into electric signals and inputting the electric signals into the diversion rotor control chip (373);

the rotor shaft rotating speed sensor (372) is used for measuring the rotating speed of the rotor shaft (500) under the current working condition, and converting the rotating speed into an electric signal to be input into the diversion rotor control chip (373);

the diversion rotor control chip (373) calculates the optimal rotation speed of the diversion rotor under the current working condition according to the input incoming flow state sensor electric signal based on the preset incoming flow state-diversion rotor rotation speed curve, and calculates the optimal reduction ratio of the adjustable speed reducer (374) according to the rotation speed of the rotor shaft, thereby generating a control signal for the adjustable speed reducer (374);

the adjustable speed reducer (374) is a mechanical speed changer with a servo actuator, an input shaft is connected to the rotor shaft (500), an output shaft is connected to a rotating shaft of the air inlet diversion rotor (310), and the speed reduction ratio is adjusted according to a control signal of the diversion rotor control chip (373).

4. The wake cycle wave aeroengine according to claim 1 or 2, wherein the air inlet (311) and the air outlet (331) are staggered, ensuring that both inlet and outlet ends of the gas are closed during combustion in the cycle wave combustion chamber (320).

5. The wake cycle wave aircraft engine of claim 1, wherein the wake channel conditioning device (930) comprises an incoming flow status sensor (931), a wake channel gas status sensor (932), a wake channel control chip (933) and a valve servo-adjustment mechanism (934);

the incoming flow sensor (931) comprises an electronic gas speed measuring device and an electronic gas pressure measuring device, is positioned at the upstream of the air inlet guide rotor (310), is used for measuring the air flow pressure and the air flow velocity at the air inlet guide rotor under the current working condition, and is converted into an electric signal to be input into the accompanying flow channel control chip (933);

the gas state sensor (932) of the accompanying flow channel comprises an electronic gas velocity measuring device and an electronic gas pressure measuring device, is positioned at the inlet of the accompanying flow channel (920) outside the combustion chamber, is used for measuring the airflow pressure and the airflow velocity of the accompanying flow channel (920) outside the combustion chamber under the current working condition, and is converted into an electric signal to be input into the accompanying flow channel control chip (933);

the accompanying flow channel control chip (933) calculates the optimal flow of the accompanying flow channel (920) outside the combustion chamber under the current working condition according to the input incoming flow state sensor electric signal based on the preset incoming flow state-accompanying flow channel state curve, so as to generate a control signal for the accompanying flow channel adjusting valve (910);

the valve servo adjusting mechanism (934) is a mechanical transmission mechanism with a servo actuator, and adjusts the target position of the wake channel control valve (910) according to the control signal of the wake channel control chip.