Axial flow rotary wave barrier engine

Abstract

The application belongs to the technical field of engines and relates to an axial flow rotary wave partition engine, which comprises a casing and, sequentially arranged in the casing, an air inlet, an adjustable guide vane, at least one compression rotor, a first outlet static vane, a combustion chamber, a guide vane grid, at least one expansion rotor, a second outlet static vane and an exhaust part. The compression rotor is provided with a plurality of compression flow channels distributed in the circumferential direction. The compression flow channel comprises a tapering section, a throat and a diverging section arranged in sequence. The compression rotor and the expansion rotor are coaxially arranged. The airflow from the compression rotor and adjusted by the first outlet static vane forms a standing vortex stable flame region in the combustion chamber, thereby constituting an axial continuous air path without flow channel switching. The application realizes the collaborative coupling of rotary ram compression, standing vortex combustion and flow channel type expansion work in a single continuous air path, significantly reduces the axial size of the engine, reduces the number of parts and improves the power density.

Description

Technical Field

[0001] This invention belongs to the field of engine technology and relates to an axial flow rotating wave baffle engine. Background Technology

[0002] Gas turbine engines are characterized by high power density, compact structure, and strong continuous output capability, and are widely used in fields such as aviation propulsion, ship propulsion, vehicle propulsion, and distributed power generation. As equipment systems increasingly demand miniaturization, high power density, and rapid response capabilities from power units, traditional axial compressor and turbine structures face certain limitations in terms of stage number, component size, and flow losses.

[0003] The core components of a traditional gas turbine engine include the compressor, combustion chamber, and turbine. The compressor typically employs a multi-stage axial flow structure, using a series arrangement of rotor and stator blades to progressively increase air pressure by applying work to the air stage by stage. However, limited by the airfoil's diffusion capacity and the flow stability boundary under the adverse pressure gradient, the single-stage pressure ratio of traditional axial compressors is relatively low, typically only 1.2 to 1.5. To achieve a higher overall pressure ratio, a multi-stage series structure is necessary, leading to an excessively long axial dimension of the engine, an increased number of components, greater difficulty in controlling blade tip clearance, and increased system integration complexity. These problems are particularly pronounced in the low-to-medium power range due to the multi-stage axial flow structure.

[0004] Corresponding to the compressor, traditional turbines also employ a multi-stage axial flow structure. Through the cooperation of multiple stages of guide vanes and moving blades, high-temperature combustion gases expand and perform work in stages. Limited by the single-stage enthalpy drop capacity and the high-temperature strength of the blade materials, traditional turbines also require multiple stages in series to achieve a high total expansion ratio, further increasing the axial dimensions and structural complexity of the engine.

[0005] Therefore, both the compressor and turbine of traditional gas turbine engines face the dilemma of having to adopt a multi-stage series structure due to the limited capacity of a single stage. This common problem results in a longer axial dimension, a larger number of parts, and higher structural complexity, which is particularly prominent in applications of small to medium power and compact power units. Summary of the Invention

[0006] The purpose of this invention is to provide an axial-flow rotating wave baffle engine to solve the technical problems of excessively long axial dimensions, excessive number of parts, and high structural complexity in the prior art.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: an axial flow rotating wave baffle engine, comprising a casing and an intake duct, adjustable guide vanes, at least one compression rotor, a first outlet stator vane, a combustion chamber, a guide vane grid, at least one expansion rotor, a second outlet stator vane, and an exhaust section, which are sequentially disposed within the casing. The compression rotor includes a compression rotor hub and a plurality of first baffles spaced circumferentially around the outer periphery of the compression rotor hub. Adjacent first baffles, the compression rotor hub, and the casing together form a plurality of compression channels arranged circumferentially. The compression channels sequentially include a converging section, a throat, and a expanding section along the relative airflow direction. A compression ramp is provided on the lower wall of the converging section, and the height of the compression channel between the upper and lower walls of the converging section gradually decreases along the airflow direction.

[0008] The expansion rotor includes an expansion rotor hub and a plurality of second baffles spaced circumferentially around the outer periphery of the expansion rotor hub. Adjacent second baffles, together with the expansion rotor hub and the casing, form a plurality of expansion channels arranged circumferentially. The expansion channels include a convergent section, a throat section and an expansion section in sequence along the airflow direction.

[0009] The combustion chamber includes a central body, an annular outer wall, and an annular main channel formed between the central body and the annular outer wall. A recessed cavity is provided in the annular main channel, and the recessed cavity is located between the trailing edge of the central body and the annular outer wall.

[0010] The compression rotor and the expansion rotor are arranged on the same rotor system. The first outlet vane is located between the compression rotor and the combustion chamber. The airflow from the first outlet vane enters the annular main channel with a tangential velocity component and forms a vortex stabilizing flame zone in the recessed cavity at the trailing edge of the central stationary body.

[0011] Preferably, the tapering section of the compression channel is used to accelerate the airflow and induce the formation of an oblique shock wave system within the compression channel, the throat is used to stabilize the compression wave system, and the expanding section is used to decelerate and diffuse the airflow.

[0012] Preferably, the converging section of the expansion channel is used to accelerate the high-temperature gas discharged from the combustion chamber, the throat section is used to stabilize the expansion wave system, and the expanding section is used to accelerate the expansion of the gas.

[0013] Preferably, the adjustable guide vane includes a plurality of guide vanes arranged circumferentially, and a variable guide channel is formed between adjacent guide vanes.

[0014] Preferably, the first outlet stator and the second outlet stator are fixedly disposed relative to the casing. The first outlet stator includes a first hub-side mounting ring and a plurality of first helical blades spaced apart circumferentially from the first hub-side mounting ring, and a gradually expanding channel is formed between adjacent first helical blades.

[0015] Preferably, the first outlet vane and the second outlet vane are fixedly disposed relative to the housing, and the second outlet vane adopts the same structure as the first outlet vane.

[0016] Preferably, the guide vane grid is fixedly disposed relative to the housing, and the guide vane grid includes a second hub-side mounting ring and a plurality of second helical blades spaced apart circumferentially on the second hub-side mounting ring, with a tapering channel formed between adjacent second helical blades.

[0017] Preferably, there are two compression rotors and two expansion rotors. The two compression rotors include a high-pressure compression rotor and a low-pressure compression rotor, and the two expansion rotors include a high-pressure expansion rotor and a low-pressure expansion rotor. The high-pressure compression rotor and the high-pressure expansion rotor are mounted on a high-pressure shaft, and the low-pressure compression rotor and the low-pressure expansion rotor are mounted on a low-pressure shaft. The high-pressure shaft and the low-pressure shaft rotate in opposite directions.

[0018] Preferably, the system further includes an axial compressor and an axial turbine arranged coaxially, with one compression rotor and one expansion rotor; the axial compressor is located between the inlet duct and the adjustable guide vane, and the axial turbine is located between the expansion rotor and the second outlet stator vane.

[0019] Beneficial effects Compared to existing technologies, this invention utilizes a three-stage compression flow channel (converging section-throat-expanding section) of the compression rotor to achieve a high pressure ratio within a single compression rotor using shock wave compression mechanism, replacing the step-by-step pressurization method of traditional multi-stage axial compressors. Similarly, a three-stage expansion flow channel (converging section-throat section-expanding section) of the expansion rotor enables a complete expansion process from subsonic to supersonic speeds within a single expansion rotor, replacing the step-by-step expansion method of traditional multi-stage axial turbines. The compression and expansion rotors are coaxially arranged, forming a continuous axial airflow path without flow channel switching. More importantly, the airflow from the first outlet stator vane enters the combustion chamber carrying a tangential velocity component, spontaneously forming a vortex-stabilized flame zone within the recessed cavity at the trailing edge of the central stoker. This transforms the inherent circumferential velocity component at the compression rotor outlet from a loss source in traditional designs into a driving force for maintaining flame stability, achieving a deep aerodynamic integration of the compression aerodynamic process and the combustion organization process. Thus, this invention completes the entire cycle of compression, combustion, and expansion within an extremely short axial length, significantly reducing the engine's axial dimensions, decreasing the number of parts, and increasing power density. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of a single-rotor axial-flow rotating wave deflector engine. Figure 2 This is a schematic diagram of the overall structure of a counter-rotating axial-flow rotating wave deflector engine. Figure 3 A schematic diagram of the overall structure of a hybrid series axial-flow rotating wave deflector engine; Figure 4 A schematic diagram of the shaft side of a single-rotor axial-flow rotating wave deflector engine; Figure 5 A schematic diagram of the axle side of a counter-rotating axial-flow rotating wave deflector engine; Figure 6 A schematic diagram of the shaft side of a hybrid series axial-flow rotating wave deflector engine; Figure 7 A schematic diagram of the rotating shafts of the rotating ram-compression rotor and the expansion rotor of a single-rotor axial-flow rotating wave baffle engine; Figure 8 This is a schematic diagram of the high and low pressure stages of a counter-rotating axial-flow rotating wave deflector engine. Figure 9 This is a schematic diagram of the hybrid connection of a hybrid series axial flow rotating wave baffle engine.

[0021] Figure label: 1. Intake duct; 2. Adjustable guide vane; 3. Compression rotor; 4. First outlet stator vane; 5. Combustion chamber; 6. Guide vane grid; 7. Expansion rotor; 8. Second outlet stator vane; 9. Exhaust section. Detailed Implementation

[0022] The technical solutions of this application will now be described clearly and in detail with reference to the accompanying drawings. In the description of the embodiments of this application, unless otherwise stated, "multiple" refers to two or more. The terms "first" and "second" are used for descriptive purposes only and should not be construed as implying or suggesting relative importance or implicitly indicating the number of indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature.

[0023] Example 1 Reference Figure 1 , Figure 4 and Figure 7 This embodiment provides an axial-flow rotating wave baffle engine, in which all core air passage components are arranged in series along a single axis, forming a continuous axial main air passage without any flow channel branches or switching. It includes a casing and, sequentially arranged within the casing along the working fluid flow direction, an intake duct 1, adjustable guide vanes 2, a compression rotor 3, a first outlet stator vane 4, a combustion chamber 5, a guide vane 6, an expansion rotor 7, a second outlet stator vane 8, and an exhaust section 9.

[0024] Reference Figure 1 and Figure 4The adjustable guide vane 2 is located between the inlet duct 1 and the compressor rotor 3. Its specific structure includes multiple guide vanes evenly distributed circumferentially. Each guide vane can rotate within a certain angle range around its own radial journal. The rotation drive mechanism can employ an actuator cylinder linkage ring mechanism or other conventional adjustable guide vane adjustment mechanisms. The cross-section of the guide vane is an aerodynamic airfoil, and adjacent guide vanes form a variable guide channel with a convergent or convergent-diffusion shape along the flow direction.

[0025] The adjustable guide vane 2's adjustment function is to control the absolute airflow angle and absolute Mach number at the guide vane outlet by changing the installation angle of the guide vane. Since the prerequisite for the compression rotor 3 to form a supersonic incoming flow in the relative coordinate system depends on the vector composition relationship between the circumferential velocity of the compression rotor and the direction and magnitude of the absolute velocity of the incoming flow, the adjustable guide vane 2 adjusts the pre-swirl angle of the incoming flow to match the relative airflow angle with the geometric installation angle of the compression rotor inlet, and ensures that the relative Mach number is maintained within the preset supersonic operating range that can stably establish a shock wave system.

[0026] Reference Figure 1 , Figure 4 and Figure 7 The compression rotor 3 is the core supercharging component of the engine, mounted on the same rotor shaft as the expansion rotor 7. Its main structure includes a compression rotor hub with multiple first baffles evenly distributed circumferentially around its outer periphery. The first baffles extend spirally axially, their outer radial edges close to the inner wall of the casing, and their inner radial edges integrally or fixedly connected to the wall of the compression rotor hub. The pressure and suction surfaces of two adjacent first baffles, the outer wall of the compression rotor hub, and the inner wall of the casing together form a compression flow channel extending from the compression rotor inlet to the compression rotor outlet. Multiple such compression flow channels are arranged in parallel circumferentially, collectively constituting the working volume of the compression rotor 3.

[0027] Along the relative airflow direction, the compression channel exhibits distinct segmentation characteristics in the meridional profile and the cross-section of the compression channel: (1) Converging Section: This section is located in the inlet region of the compression rotor 3. The inner wall of the compression channel is provided with a compression ramp at a certain wedge angle to the relative incoming flow direction. The height of the compression channel between the upper and lower walls of the converging section gradually decreases along the airflow direction. When the relatively supersonic incoming flow enters the converging section, the gradual decrease in the height of the compression channel further accelerates the airflow, inducing the formation of one or more oblique shock waves at the compression ramp. After the oblique shock wave passes through the airflow, the relative Mach number decreases, and the static pressure and static temperature increase in a stepwise manner.

[0028] (2) Throat: Located downstream of the contraction section, the cross-sectional area of ​​the compression channel reaches a local minimum or remains basically constant here. The core function of this section is to constrain the effective flow area of ​​the compression channel, provide back pressure for the upstream shock wave system, stabilize the overall position of the compression wave system, and confine the terminal shock wave to the vicinity of this section, preventing it from rushing upstream into the contraction section or downstream into the expansion section when the operating conditions fluctuate, thereby ensuring the stability and repeatability of the compression process.

[0029] (3) Diverging section: Located downstream of the throat, the cross-sectional area of ​​the compression channel gradually increases. The airflow, which is still supersonic or high subsonic after being compressed by the shock wave, decelerates further in this section, converting the remaining kinetic energy into an increase in static pressure. When the airflow leaves the diverging section, the relative velocity decreases to the set value, completing the entire compression process.

[0030] When the compressor rotor 3 rotates at high speed, air enters the compression channel at a predetermined angle under the guidance of the adjustable guide vanes 2. In the relative coordinate system, the relative velocity of the airflow has reached supersonic speed. The airflow passes through the oblique shock wave system in the contraction section, where the velocity drops sharply and the pressure rises sharply; in the throat, the shock wave system is locked; and in the diffusion section, it is further decelerated and diffused. The static pressure rise that would require several stages in a traditional multi-stage axial compressor is achieved within a single compressor rotor 3, greatly compressing the axial dimension.

[0031] Reference Figure 1 and Figure 4 The first outlet stator vane 4 is located between the outlet of the compression rotor 3 and the inlet of the combustion chamber 5. Its structure is a fixed stator vane cascade arranged circumferentially, including a first hub-side mounting ring and a plurality of first helical blades spaced apart circumferentially thereon, with a gradually expanding channel formed between adjacent first helical blades.

[0032] The first outlet stator vane 4 has a dual function: First, it diffuses the high-speed swirling gas discharged from the compression channel, further reducing the airflow velocity and increasing the static pressure to optimize the pressure conditions at the combustion chamber inlet; second, and this is a key function that distinguishes it from traditional designs—it does not completely rectify the swirling flow at the compressor rotor outlet. The outlet geometry and channel shape of the first outlet stator vane 4 are deliberately designed so that the airflow retains sufficient tangential velocity components when it leaves the first outlet stator vane 4 and enters the combustion chamber 5.

[0033] Reference Figure 1 and Figure 4 The combustion chamber 5 includes a central hull extending along the engine axis and an annular outer wall coaxially surrounding the central hull, forming an annular axial main flow channel between them. In the trailing edge region of the central hull, the annular outer wall contracts inward or the central hull expands outward, forming a localized recessed cavity. A fuel injection structure is disposed on the central hull or the annular outer wall to inject fuel into the annular main flow channel.

[0034] When the high-pressure airflow carrying a significant tangential velocity component from the first outlet stator vane 4 enters the annular main flow channel in a quasi-tangential manner, the airflow undergoes strong shearing and entrainment within the concave cavity due to the sudden truncation of the central stator's trailing edge and the abrupt expansion of the concave cavity's geometry. This forms a stable annular recirculation zone around the trailing edge of the central stator, i.e., the vortex-stabilized flame zone. Within this zone, the high-temperature burned gas continuously circulates, entraining and igniting the fresh fuel-air mixture injected by the fuel injection structure, forming a continuous and stable flame root.

[0035] Reference Figure 1 and Figure 4 The guide vane 6 is located between the outlet of the combustion chamber 5 and the inlet of the expansion rotor 7. Its structure includes a second hub-side mounting ring and a plurality of second helical blades spaced circumferentially thereon, with a tapering channel formed between adjacent second helical blades.

[0036] The function of the guide vane 6 is to aerodynamically "shape" the high-temperature, high-pressure combustion gas at the combustion chamber outlet: by accelerating the gas through a converging channel, its speed and direction become more uniform, and it is then propelled into the downstream expansion rotor 7 with a specific outlet airflow angle and Mach number. This outlet airflow angle, together with the geometric installation angle of the expansion rotor inlet and the circumferential speed of the expansion rotor, determines the relative velocity triangle at the expansion rotor inlet, ensuring that the expansion rotor 7 is in its optimal efficiency range under design conditions.

[0037] Reference Figure 1 , Figure 4 and Figure 7 The expansion rotor 7 is the power-generating component of the engine, and it is arranged coaxially with the compression rotor 3. Its structural logic is similar to that of the compression rotor 3, but its function is opposite. The expansion rotor hub of the expansion rotor 7 is also provided with multiple second baffles along the circumferential direction. The adjacent second baffles, together with the expansion rotor hub wall and the inner wall of the casing, form an expansion flow channel.

[0038] The expansion channel exhibits a clear sequential arrangement of convergent section, throat section, and expansion section along the airflow direction: (1) Converging section: Starting from the inlet of the expansion rotor 7, the cross-sectional area of ​​the expansion channel gradually decreases. The gas from the guide vane 6 is at a subsonic speed here. As the area shrinks, the airflow accelerates and the pressure decreases.

[0039] (2) Throat section: The cross-sectional area of ​​the expansion channel reaches its minimum, and the gas accelerates to the speed of sound or slightly below the speed of sound here, forming a critical or near-critical state and stabilizing the upstream flow field.

[0040] (3) Expansion section: After the throat, the cross-sectional area of ​​the expansion channel expands rapidly. The gas that has reached the speed of sound or high subsonic speed continues to expand and accelerate to the speed of sound in the expansion section. The pressure and temperature drop sharply. The huge momentum change of the airflow generates a strong reaction force on the wall of the expansion channel. Its circumferential component force drives the expansion rotor 7 to rotate and do work.

[0041] Reference Figure 1 and Figure 4 The second outlet stator vane 8 adopts the same structure as the first outlet stator vane 4 and is located downstream of the expansion rotor 7. It also includes a first hub-side mounting ring and multiple first helical blades spaced circumferentially around the first hub-side mounting ring, forming a gradually expanding channel between adjacent first helical blades. Its function is to guide the residual circumferential velocity component still carried at the outlet of the expansion rotor 7 into axial exhaust gas, reducing outlet residual velocity loss and recovering some of the swirling kinetic energy. The guided exhaust gas is discharged from the casing through the exhaust section 9, completing the entire cycle.

[0042] Example 2 Reference Figure 2 , Figure 5 and Figure 8 While keeping the core gas path principle and combustion chamber configuration of Embodiment 1 completely unchanged, this embodiment provides a counter-rotating derivative structure.

[0043] In this embodiment, there are two compression rotors 3 and two expansion rotors 7. The two compression rotors 3 include a low-pressure compression rotor and a high-pressure compression rotor, and the two expansion rotors 7 include a high-pressure expansion rotor and a low-pressure expansion rotor. The high-pressure compression rotor and the high-pressure expansion rotor are mounted on a high-pressure shaft, and the low-pressure compression rotor and the low-pressure expansion rotor are mounted on a low-pressure shaft. Figure 8 As shown, the low-pressure rotor shaft and the high-pressure rotor shaft are coaxially mounted and rotate in opposite directions by gas power.

[0044] The airflow from the low-pressure compressor rotor outlet is rectified and guided by the intermediate guide vanes before entering the high-pressure compressor rotor inlet at a suitable angle for further shock wave compression. The airflow from the high-pressure compressor rotor outlet directly enters the combustion chamber 5. The combusted gas first enters the high-pressure expansion rotor to perform work, and the exhaust gas then passes through the interstage guide structure into the low-pressure expansion rotor to continue recovering residual energy, finally exiting through the second outlet vane 8.

[0045] This embodiment uses a counter-rotating structure to distribute the total pressure ratio across two compression rotors 3, one high-pressure and one low-pressure rotor. This reduces the circumferential speed requirement of a single compression rotor 3 and alleviates the centrifugal load and bearing load on the rotor system. The high-pressure and low-pressure rotors rotate in opposite directions, which balances the gyroscopic torque. While maintaining the continuous and compact core gas path of the basic configuration, the total pressure ratio and power density are improved.

[0046] Example 3 Reference Figure 3 , Figure 6 and Figure 9 While keeping the core gas path principle and combustion chamber configuration of Embodiment 1 completely unchanged, this embodiment provides a hybrid series derivative structure.

[0047] This embodiment also includes an axial compressor and an axial turbine, with one compression rotor 3 and one expansion rotor 7. The axial compressor is located between the inlet duct 1 and the adjustable guide vane 2, and the axial turbine is located between the expansion rotor 7 and the second outlet stator vane 8. Figure 9 As shown, the axial compressor and the axial turbine are connected by the same rotating shaft.

[0048] Air is first pressurized and rectified by an axial compressor at a low pressure ratio, and then enters the adjustable guide vane 2 and the compression rotor 3 to complete the main pressurization. The high-temperature gas after combustion first completes the main work by the expansion rotor 7, and the exhaust gas then enters the axial turbine for residual energy recovery. The axial turbine drives the axial compressor to rotate through the shaft, forming a self-sustaining small energy recovery cycle.

[0049] The hybrid series structure of this embodiment introduces mature and reliable traditional turbine mechanical components as auxiliary boosting and residual energy recovery units without disrupting the continuous and compact air path of "shock compression-vortex combustion-flow channel expansion work", thereby improving the overall cycle efficiency of the whole machine and the matching flexibility with existing power turbines and other loads.

[0050] It is understood that the present invention has been described through some embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of the invention. Furthermore, under the teachings of the present invention, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of the invention. Therefore, the present invention is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of the present invention.

Claims

1. An axial-flow rotating wave baffle engine, characterized in that, The device includes a casing and, sequentially disposed within the casing, an intake duct, adjustable guide vanes, at least one compression rotor, a first outlet stator vane, a combustion chamber, a guide vane grid, at least one expansion rotor, a second outlet stator vane, and an exhaust section. The compression rotor includes a compression rotor hub and a plurality of first baffles spaced circumferentially around the outer periphery of the compression rotor hub. Adjacent first baffles, the compression rotor hub, and the casing together form a plurality of circumferentially arranged compression channels. The compression channels sequentially include a converging section, a throat, and a diverging section along the relative airflow direction. A compression ramp is provided on the lower wall of the converging section, and the height of the compression channel between the upper and lower walls of the converging section gradually decreases along the airflow direction. The expansion rotor includes an expansion rotor hub and a plurality of second baffles spaced circumferentially around the outer periphery of the expansion rotor hub. Adjacent second baffles, together with the expansion rotor hub and the casing, form a plurality of expansion channels arranged circumferentially. The expansion channels include a converging section, a throat section and an expanding section in sequence along the airflow direction. The combustion chamber includes a central body, an annular outer wall, and an annular main channel formed between the central body and the annular outer wall. A recessed cavity is provided in the annular main channel, and the recessed cavity is located between the trailing edge of the central body and the annular outer wall. The compression rotor and the expansion rotor are arranged on the same rotor system. The first outlet vane is located between the compression rotor and the combustion chamber. The airflow from the first outlet vane enters the annular main channel with a tangential velocity component and forms a vortex stabilizing flame zone in the recessed cavity at the trailing edge of the central stationary body.

2. The axial-flow rotating wave deflector engine according to claim 1, characterized in that, The tapering section of the compression channel is used to accelerate the airflow and induce the formation of an oblique shock wave system within the compression channel. The throat is used to stabilize the compression wave system, and the expanding section is used to decelerate and diffuse the airflow.

3. The axial-flow rotating wave deflector engine according to claim 1, characterized in that, The converging section of the expansion channel is used to accelerate the high-temperature gas discharged from the combustion chamber, the throat section is used to stabilize the expansion wave system, and the expansion section is used to accelerate the expansion of the gas.

4. The axial-flow rotating wave deflector engine according to claim 1, characterized in that, The adjustable guide vane includes multiple guide vanes arranged circumferentially, and a variable guide channel is formed between adjacent guide vanes.

5. The axial-flow rotating wave deflector engine according to claim 1, characterized in that, The first outlet stator and the second outlet stator are fixedly disposed relative to the casing. The first outlet stator includes a first hub-side mounting ring and a plurality of first helical blades spaced apart circumferentially from the first hub-side mounting ring. A gradually expanding channel is formed between adjacent first helical blades.

6. The axial-flow rotating wave deflector engine according to claim 5, characterized in that, The second outlet stator blade adopts the same structure as the first outlet stator blade.

7. The axial-flow rotating wave deflector engine according to claim 1, characterized in that, The guide vane grid is fixedly disposed relative to the casing. The guide vane grid includes a second hub-side mounting ring and a plurality of second helical blades spaced apart circumferentially on the second hub-side mounting ring. A tapering channel is formed between adjacent second helical blades.

8. The axial-flow rotating wave deflector engine according to claim 1, characterized in that, There are two compression rotors and two expansion rotors. The two compression rotors include a high-pressure compression rotor and a low-pressure compression rotor. The two expansion rotors include a high-pressure expansion rotor and a low-pressure expansion rotor. The high-pressure compression rotor and the high-pressure expansion rotor are mounted on a high-pressure shaft. The low-pressure compression rotor and the low-pressure expansion rotor are mounted on a low-pressure shaft. The high-pressure shaft and the low-pressure shaft rotate in opposite directions.

9. The axial-flow rotating wave deflector engine according to claim 1, characterized in that, It also includes an axial compressor and an axial turbine arranged coaxially, with one compression rotor and one expansion rotor; the axial compressor is located between the inlet and the adjustable guide vane, and the axial turbine is located between the expansion rotor and the second outlet stator vane.

Images