A turbine power generation device based on pulse detonation

Abstract

This invention discloses a turbine power generation device based on pulse detonation, comprising a compressor, a pulse detonation combustion chamber, a gas turbine, a coupling, a generator, and a controller. During operation, air enters from the compressor and is split into inner and outer bypass air. The inner bypass air passes through a cyclone separator and enters the mixing chamber. Fuel, controlled by a solenoid valve, enters the mixing chamber through a nozzle at the center of the cyclone separator, mixing with the air to form a premixed gas. After passing through a central conical blunt body, the premixed gas is ignited by a high-energy electric nozzle in a concave cavity and enters the detonation section. The flame accelerates in this section, ultimately forming a detonation wave. This detonation wave ejects the outer bypass air and enters the tailpipe together, further increasing the pressure. The ejected airflow enters the gas turbine and drives the generator to generate electricity. Compared to traditional slow-burning power generation devices, this invention has higher power generation efficiency, a wider range of power output variation, and can achieve rapid changes in power output.

Description

Technical Field

[0001] This invention relates to the field of turbine power generation technology, and in particular to a turbine power generation device based on pulse detonation. Background Technology

[0002] Combustion is a crucial way for fuels to release their inherent chemical energy. There are two types of combustion in nature: slow combustion and detonation combustion. Slow combustion relies on heat conduction to raise the temperature of the unburned mixture or the diffusion of intermediate activation products to propagate the combustion wave to the unburned mixture. The propagation speed of the combustion wave in slow combustion is affected by the rate of heat conduction or mass transfer, resulting in a relatively low propagation speed. Detonation combustion, on the other hand, relies on a shock wave to compress the unburned mixture, raising its pressure and temperature, leading to spontaneous combustion. The coupling between the slow combustion wave and the shock wave results in a higher flame propagation speed, thus the detonation wave propagation speed is extremely high. Pulse detonation is a type of detonation combustion that utilizes pulse detonation waves to generate periodic impulses. Power systems utilizing pulse detonation combustion have advantages such as high cycle thermal efficiency, low fuel consumption, relatively simple structure, and light weight. Therefore, extensive research has been conducted on the application of pulse detonation combustion technology in propulsion systems.

[0003] Germany first attempted to use pulse detonation in propulsion systems in the 1940s. It wasn't until the 1980s that the U.S. Naval Postgraduate School built an air-breathing pulse detonation engine, proving its practical value. In the 1990s, the U.S. developed single-tube and multi-tube rotary valve inlet pulse detonation engines, achieving thrust adjustment without reducing propulsion efficiency. In 2003, Pratt & Whitney's Seattle Aeronautical Research Center, with funding from the U.S. Naval Research Laboratory, developed a full-scale, flight-inlet-condition five-tube rotary valve pulse detonation engine demonstrator. In January 2008, the U.S. Air Force Research Laboratory and ISSI successfully conducted the first manned flight test powered by a pulse detonation engine in California. The University of Tsukuba in Japan also conducted flight test research on pulse detonation rocket engines and built a pulse detonation rocket.

[0004] When pulse detonation combustion technology is used in propulsion devices, the thrust generated also exhibits unsteady characteristics due to its non-steady-state nature. To generate more stable thrust, the operating frequency of the pulse detonation combustion device needs to be increased. However, if pulse detonation combustion is applied to power generation systems, the operating frequency requirement for the pulse detonation combustion device is lower, and the high cycle efficiency of the pulse detonation combustion mode can be utilized to improve power generation efficiency.

[0005] Therefore, the purpose of this invention is to provide a turbine power generation device based on pulse detonation to improve the power generation efficiency of existing power generation devices. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to address the deficiencies mentioned in the background art by providing a turbine power generation device based on pulse detonation.

[0007] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0008] A turbine power generation device based on pulse detonation includes a compressor, a pulse detonation combustion chamber, a gas turbine, a coupling, a generator, and a controller;

[0009] The compressor is located at the inlet of the pulse detonation combustion chamber and is used to supply air to the detonation combustion chamber;

[0010] The pulse detonation combustion chamber includes an outer shell, an inner shell, a cyclone separator, M fixed rods, a fuel pipe, a fuel nozzle, a solenoid valve, a central cone blunt body, N flame support plates, P high-energy electric nozzles, and Q baffles. M and N are natural numbers greater than or equal to 2, P is a natural number greater than or equal to 1, and Q is a natural number greater than or equal to 8.

[0011] The outer shell comprises an extension section, a stable section, and a contraction section. The extension section is a hollow frustum of a cone with openings at both ends and an upstream end face area smaller than the downstream end face area. The stable section is a hollow cylinder with openings at both ends. The contraction section is a hollow frustum of a cone with openings at both ends and a downstream end face area smaller than the upstream end face area. The inner diameters of the larger end face of the extension section, the stable section, and the contraction section are the same. The extension section, the stable section, and the contraction section are coaxially and sealed together from upstream to downstream.

[0012] The inner shell is disposed within the outer shell and includes a mixing section, an ignition section, a connecting section, and a detonation section. The mixing section is a hollow cylinder open at both ends. The ignition section is a hollow cylinder with through holes on both end faces having a diameter equal to the inner diameter of the mixing section. The connecting section is a hollow frustum open at both ends, with the downstream end face area smaller than the upstream end face area, and the inner diameter of its upstream end face equal to the inner diameter of the mixing section. The detonation section is a hollow cylinder open at both ends, with its inner diameter equal to the inner diameter of the larger end face of the connecting section. The mixing section, ignition section, connecting section, and detonation section are coaxially and sealed together sequentially from upstream to downstream.

[0013] The M fixing rods are evenly arranged circumferentially between the outer shell and the inner shell, with one end fixed to the inner wall of the outer shell and the other end fixed to the outer wall of the inner shell, so that the outer shell and the inner shell are coaxially arranged.

[0014] The hydrocyclone includes a fixed cylinder and several blades, wherein the fixed cylinder is a hollow cylinder with open ends, and the axes of the several blades are evenly arranged on the outer wall of the fixed cylinder.

[0015] The fuel nozzle is a hollow cylinder with a through hole at the center of its upstream end face for connecting with the fuel pipe, and a sealed end face at its downstream end.

[0016] One end of the fuel pipe is connected to external fuel, and the other end passes through the outer shell stable section and the inner shell mixing section in sequence, and is sealed and fixed to the through hole at the center of the upstream end face of the fuel nozzle, so that the fuel nozzle is coaxially arranged in the inner shell mixing section.

[0017] The fixed sleeve of the cyclone separator is fitted outside the fuel nozzle and is coaxially fixed to the fuel nozzle;

[0018] The fuel nozzles are evenly arranged circumferentially on the side wall downstream of the cyclone separator.

[0019] The solenoid valve is installed inside the fuel pipe and is used to control the opening and closing of the fuel pipe;

[0020] The central cone-shaped blunt body is a cone, the diameter of its bottom surface is equal to the inner diameter of the detonation section, and a cone-shaped first groove is provided at the center of the bottom surface.

[0021] The flame support plate is a hollow semi-cylinder with openings at both ends;

[0022] The N flame-connecting support plates are circumferentially and evenly arranged between the ignition section and the central cone blunt body. Each plate is fixed at one end to the ignition section at a through hole on its upstream end face, and at the other end to the central cone blunt body, such that the cone tip of the central cone blunt body faces upstream and the central cone blunt body and the ignition section are coaxial. The openings of the flame-connecting support plates all face downstream, and the planar sidewalls of the flame-connecting support plates are coplanar with the inner wall of the upstream end face of the ignition section and the bottom surface of the central cone blunt body, respectively.

[0023] The inner wall of the upstream end face of the ignition section and the bottom surface of the central cone blunt body are provided with grooves that correspond one-to-one with the flame-connecting support plate. The flame-connecting support plate, the corresponding groove on the inner wall of the upstream end face of the flame-connecting support plate, and the corresponding groove on the bottom surface of the central cone blunt body are collinear, forming a smooth, semi-cylindrical groove that is connected to the first groove.

[0024] The P high-energy electric nozzles are evenly arranged circumferentially and pass through the outer shell and ignition section in sequence for ignition.

[0025] The Q baffles are arranged in a ring shape and are evenly distributed at equal intervals within the detonation section. Their outer walls are all coaxially fixed to the inner wall of the detonation section, and the distance between adjacent baffles does not exceed twice the inner diameter of the detonation section.

[0026] The inlet of the extended section is the pulse detonation combustion chamber inlet, which is connected to the compressor outlet; the contraction section forms the tail nozzle, and its outlet is the pulse detonation combustion outlet, which is connected to the gas turbine inlet pipe; the gas turbine is connected to the generator via a coupling.

[0027] The controller is electrically connected to the solenoid valve and the P high-energy electrical nozzles respectively, and is used to control the operation of the solenoid valve and the P high-energy electrical nozzles.

[0028] As a further optimization of the turbine power generation device based on pulse detonation of the present invention, a guide fluid is provided on the downstream end face of the fuel nozzle;

[0029] The guide body is a cone with a bottom diameter equal to the diameter of the downstream end face of the fuel nozzle, and the bottom surface of the guide body and the downstream end face of the fuel nozzle are coaxially fixed together.

[0030] As a further optimization of the turbine power generation device based on pulse detonation of the present invention, the P high-energy electrical nozzles are all located on the mid-section of the ignition section.

[0031] As a further optimization of the turbine power generation device based on pulse detonation of the present invention, M is 3, N is 4, P is 2, and Q is 8.

[0032] Compared with the prior art, the present invention, employing the above technical solution, has the following technical effects:

[0033] 1. Compared with traditional slow-burning power generation devices, the present invention has higher power generation efficiency;

[0034] 2. The present invention has a wide range of power generation variation and can change the power generation in a short period of time;

[0035] 3. The combustion device of the present invention is simple and compact, which can reduce the overall weight. Attached Figure Description

[0036] Figure 1 This is a schematic diagram of an overall turbine power generation device based on pulse detonation according to the present invention.

[0037] Figure 2 This is a schematic diagram of the structure within the mixing section of the present invention;

[0038] Figure 3 This is a schematic diagram of the structure within the ignition section of the present invention;

[0039] Figure 4 This is a schematic diagram of the flow inside the pulse detonation combustion chamber in this invention.

[0040] In the diagram, 1-compressor, 2-extension section of the outer shell, 3-smoothing section of the outer shell, 4-contraction section of the outer shell, 5-mixing section of the inner shell, 6-ignition section of the inner shell, 7-connecting section of the inner shell, 8-knock section of the inner shell, 9-cyclone separator, 10-fuel nozzle, 11-fuel pipe, 12-solenoid valve, 13-central cone blunt body, 14-high-energy electric nozzle, 15-turbulence vane, 16-gas turbine, 17-coupling, 18-generator, 19-controller, 20-blade on the cyclone separator, 21-nozzle on the fuel nozzle, 22-flame support plate. Detailed Implementation

[0041] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings:

[0042] This invention can be implemented in many different forms and should not be considered limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully express the scope of the invention to those skilled in the art. In the drawings, components are enlarged for clarity.

[0043] It should be understood that although the terms first, second, third, etc., may be used herein to describe various elements, components, and / or parts, these elements, components, and / or parts are not limited by these terms. These terms are merely used to distinguish elements, components, and / or parts from one another. Therefore, the first element, component, and / or part discussed below may be a second element, component, or part without departing from the teachings of this invention.

[0044] like Figure 1 As shown, the present invention discloses a turbine power generation device based on pulse detonation, including a compressor, a pulse detonation combustion chamber, a gas turbine, a coupling, a generator, and a controller;

[0045] The compressor is located at the inlet of the pulse detonation combustion chamber and is used to supply air to the detonation combustion chamber;

[0046] The pulse detonation combustion chamber includes an outer shell, an inner shell, a cyclone separator, M fixed rods, a fuel pipe, a fuel nozzle, a solenoid valve, a central cone blunt body, N flame support plates, P high-energy electric nozzles, and Q baffles. M and N are natural numbers greater than or equal to 2, P is a natural number greater than or equal to 1, and Q is a natural number greater than or equal to 8.

[0047] The outer shell comprises an extension section, a stable section, and a contraction section. The extension section is a hollow frustum of a cone with openings at both ends and an upstream end face area smaller than the downstream end face area. The stable section is a hollow cylinder with openings at both ends. The contraction section is a hollow frustum of a cone with openings at both ends and a downstream end face area smaller than the upstream end face area. The inner diameters of the larger end face of the extension section, the stable section, and the contraction section are the same. The extension section, the stable section, and the contraction section are coaxially and sealed together from upstream to downstream.

[0048] The inner shell is disposed within the outer shell and includes a mixing section, an ignition section, a connecting section, and a detonation section. The mixing section is a hollow cylinder open at both ends. The ignition section is a hollow cylinder with through holes on both end faces having a diameter equal to the inner diameter of the mixing section. The connecting section is a hollow frustum open at both ends, with the downstream end face area smaller than the upstream end face area, and the inner diameter of its upstream end face equal to the inner diameter of the mixing section. The detonation section is a hollow cylinder open at both ends, with its inner diameter equal to the inner diameter of the larger end face of the connecting section. The mixing section, ignition section, connecting section, and detonation section are coaxially and sealed together sequentially from upstream to downstream.

[0049] The M fixing rods are evenly arranged circumferentially between the outer shell and the inner shell, with one end fixed to the inner wall of the outer shell and the other end fixed to the outer wall of the inner shell, so that the outer shell and the inner shell are coaxially arranged.

[0050] like Figure 2 As shown, the hydrocyclone includes a fixed cylinder and several blades, wherein the fixed cylinder is a hollow cylinder with open ends, and the axes of the several blades are evenly arranged on the outer wall of the fixed cylinder.

[0051] The fuel nozzle is a hollow cylinder with a through hole at the center of its upstream end face for connecting with the fuel pipe, and a sealed end face at its downstream end.

[0052] One end of the fuel pipe is connected to external fuel, and the other end passes through the outer shell stable section and the inner shell mixing section in sequence, and is sealed and fixed to the through hole at the center of the upstream end face of the fuel nozzle, so that the fuel nozzle is coaxially arranged in the inner shell mixing section.

[0053] The fixed sleeve of the cyclone separator is fitted outside the fuel nozzle and is coaxially fixed to the fuel nozzle;

[0054] The fuel nozzles are evenly arranged circumferentially on the side wall downstream of the cyclone separator.

[0055] The solenoid valve is installed inside the fuel pipe and is used to control the opening and closing of the fuel pipe;

[0056] like Figure 3 As shown, the central cone blunt body is a cone, the diameter of its bottom surface is equal to the inner diameter of the detonation section, and a cone-shaped first groove is provided at the center of the bottom surface.

[0057] The flame support plate is a hollow semi-cylinder with openings at both ends;

[0058] The N flame-connecting support plates are circumferentially and evenly arranged between the ignition section and the central cone blunt body. Each plate is fixed at one end to the ignition section at a through hole on its upstream end face, and at the other end to the central cone blunt body, such that the cone tip of the central cone blunt body faces upstream and the central cone blunt body and the ignition section are coaxial. The openings of the flame-connecting support plates all face downstream, and the planar sidewalls of the flame-connecting support plates are coplanar with the inner wall of the upstream end face of the ignition section and the bottom surface of the central cone blunt body, respectively.

[0059] The inner wall of the upstream end face of the ignition section and the bottom surface of the central cone blunt body are provided with grooves that correspond one-to-one with the flame-connecting support plate. The flame-connecting support plate, the corresponding groove on the inner wall of the upstream end face of the flame-connecting support plate, and the corresponding groove on the bottom surface of the central cone blunt body are collinear, forming a smooth, semi-cylindrical groove that is connected to the first groove.

[0060] The P high-energy electric nozzles are evenly arranged circumferentially and pass through the outer shell and ignition section in sequence for ignition.

[0061] The Q baffles are arranged in a ring shape and are evenly distributed at equal intervals within the detonation section. Their outer walls are all coaxially fixed to the inner wall of the detonation section, and the distance between adjacent baffles does not exceed twice the inner diameter of the detonation section.

[0062] The inlet of the extended section is the pulse detonation combustion chamber inlet, which is connected to the compressor outlet; the contraction section forms the tail nozzle, and its outlet is the pulse detonation combustion outlet, which is connected to the gas turbine inlet pipe; the gas turbine is connected to the generator via a coupling.

[0063] The controller is electrically connected to the solenoid valve and the P high-energy electrical nozzles respectively, and is used to control the operation of the solenoid valve and the P high-energy electrical nozzles.

[0064] A guide fluid is provided on the downstream end face of the fuel nozzle; the guide fluid is a cone with a bottom diameter equal to the diameter of the downstream end face of the fuel nozzle, and the bottom surface of the guide fluid and the downstream end face of the fuel nozzle are coaxially fixed together.

[0065] The P high-energy electric nozzles are all located on the mid-section of the ignition section, with M preferably being 3, N preferably being 4, P preferably being 2, and Q preferably being 8.

[0066] like Figure 4 As shown, after the air comes out of the compressor, it passes through the split section and enters the flow channel between the outer shell and the inner shell and the flow channel inside the inner shell, and is divided into outer bypass air and inner core air. The outer bypass air flows through the outer surface of the pulse detonation combustion chamber, reduces the temperature of the combustion chamber wall, and then flows directly to the gas turbine generator through the tail nozzle. The inner core airflow enters the mixing section.

[0067] The internal air enters the mixing chamber through the cyclone separator, forming a double vortex flow field. The fuel enters the fuel nozzle through the fuel pipe after the solenoid valve is opened, and then enters the mixing chamber radially through the injection hole on the fuel nozzle via the pulse detonation combustion chamber, where it is mixed with the air to form a premixed gas.

[0068] The swirl number of the hydrocyclone should preferably be no less than 0.7. The fuel nozzle is located at the center of the hydrocyclone. To better mix with air, the nozzle orifices should be arranged circumferentially and perpendicular to the airflow direction. The diameter and number of nozzle orifices are determined by the fuel penetration depth in the air and the fuel flow rate. The penetration depth should be 1 / 2 to 2 / 3, and the fuel flow rate should meet the requirement of a premixed air equivalence ratio of 1.

[0069] The ignition section is divided into a main flow zone and a concave cavity zone. The main flow zone is the central area with the same size as the inner diameter of the mixing end, and the concave cavity zone is the cavity area outside the central area. Air enters the concave cavity zone and forms a spiral vortex flow field. The premixed gas is ignited by the high-energy electric nozzle under the action of the spiral vortex. When P is 2, the ignition adopts a dual ignition method, that is, two symmetrically arranged high-energy electric nozzles are used for simultaneous ignition. After the premixed gas passes through the central cone blunt body, a small vortex is formed in the main flow zone, which causes the flame in the concave cavity to ignite the premixed gas at that location through the flame support plate, so that the flame spreads to the rear.

[0070] A first groove is provided at the rear end of the central cone bluff body. After the premixed gas is ignited at the rear of the central cone bluff body, a compression wave is formed in a short time. The compression wave is reflected and enhanced through the first groove, strengthening combustion and accelerating flame propagation. A baffle is provided in the detonation section. When the flame passes through the baffle, it propagates faster, and the intensity of the compression wave gradually increases, forming a shock wave. At this time, the flame propagation speed remains stable, and the shock wave couples with the flame to form a detonation wave. The detonation wave entrains the bypass air, and the pressure is further increased under the action of the tail nozzle. The number of baffles is not less than 8, and the spacing is not more than twice the inner diameter of the detonation section, so that the blockage ratio of the detonation section should not be less than 0.3. The inner diameter of the detonation section of the pulse detonation combustion chamber should be the same as the inner diameter of the rear end face of the central cone bluff body.

[0071] The detonation wave draws the bypass air into the tailpipe, increasing the pressure and reducing the airflow temperature; the inner diameter of the tailpipe outlet should not be too small, otherwise it will reduce the operating frequency of the detonation combustion chamber or even cause continuous combustion, resulting in the failure of the detonation cycle.

[0072] The detonation wave exiting the exhaust nozzle combines with the bypass air to form a high-speed, high-pressure airflow that flows towards the gas turbine. Through the coupling, this airflow drives the generator to perform work. This process constitutes a single cycle; the actual power generation process is a multi-cycle process, which is a continuous repetition of the single cycle described above. Because the pulse detonation cycle is significantly more efficient than the slow-burning cycle, it generates more electricity with less fuel.

[0073] The controller directs the high-energy electric nozzle and solenoid valve to operate at specified times, forming a control sequence. The controller is required to have a control delay time within 5% of the single-cycle time.

[0074] The entire process of turbine power generation in this invention is as follows:

[0075] The first stage of a single cycle is the fuel filling stage. The controller issues a command to open the solenoid valve, allowing fuel to enter the fuel line, pass through the fuel nozzle, and enter the mixing section. Air from the compressor passes through a cyclone separator to form a premixed gas mixture with the fuel. This premixed gas mixture continues until it reaches the tailpipe, at which point the solenoid valve closes, ending the filling stage. The second stage is ignition and flame propagation. A high-energy electric nozzle ignites the flame, which enters the detonation section. Under the action of the detonation vanes, a detonation wave is formed. This wave passes through the tailpipe and, together with the bypass air, enters the gas turbine, driving the generator to produce electricity. When a detonation wave is generated in the pulse detonation combustion chamber section, the pressure rises. Air from the compressor enters the bypass air, and after the detonation wave exits the tailpipe, the pressure returns to normal, and air begins to enter the combustion chamber. At this point, the second stage ends. The third stage is exhaust gas emission and isolation gas filling. In this stage, only air enters the pulse detonation combustion chamber section, forming a certain degree of air isolation to prevent fresh premixed gas from contacting the flame. This stage ends, and the next cycle's fuel filling stage begins.

[0076] The time for each process needs to be calculated based on the specific combustion chamber structure and operating frequency. The combustion filling stage time must ensure the fuel completely fills the entire pulse detonation combustion chamber section. The exhaust gas emission and isolation gas filling time must ensure complete exhaust gas emission and the formation of a sufficiently long isolation section to prevent continuous combustion. The fuel filling time is controlled by a solenoid valve, while the operating frequency or single-cycle time is controlled by the solenoid valve and the high-energy electric nozzle ignition frequency.

[0077] This invention generates electricity through pulse detonation combustion, which effectively improves power generation efficiency.

[0078] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0079] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A turbine power generation device based on pulse detonation, characterized in that, Includes compressor, pulse detonation combustor, gas turbine, coupling, generator and controller; The compressor is located at the inlet of the pulse detonation combustion chamber and is used to supply air to the detonation combustion chamber; The pulse detonation combustion chamber includes an outer shell, an inner shell, a cyclone separator, M fixed rods, a fuel pipe, a fuel nozzle, a solenoid valve, a central cone blunt body, N flame support plates, P high-energy electric nozzles, and Q baffles. M and N are natural numbers greater than or equal to 2, P is a natural number greater than or equal to 1, and Q is a natural number greater than or equal to 8. The outer shell comprises an extension section, a stable section, and a contraction section. The extension section is a hollow frustum of a cone with openings at both ends and an upstream end face area smaller than the downstream end face area. The stable section is a hollow cylinder with openings at both ends. The contraction section is a hollow frustum of a cone with openings at both ends and a downstream end face area smaller than the upstream end face area. The inner diameters of the larger end face of the extension section, the stable section, and the contraction section are the same. The extension section, the stable section, and the contraction section are coaxially and sealed together from upstream to downstream. The inner shell is disposed within the outer shell and includes a mixing section, an ignition section, a connecting section, and a detonation section. The mixing section is a hollow cylinder open at both ends. The ignition section is a hollow cylinder with through holes on both end faces having a diameter equal to the inner diameter of the mixing section. The connecting section is a hollow frustum open at both ends, with the downstream end face area smaller than the upstream end face area, and the inner diameter of its upstream end face equal to the inner diameter of the mixing section. The detonation section is a hollow cylinder open at both ends, with its inner diameter equal to the inner diameter of the larger end face of the connecting section. The mixing section, ignition section, connecting section, and detonation section are coaxially and sealed together sequentially from upstream to downstream. The M fixed rods are evenly arranged circumferentially between the outer shell and the inner shell, with one end fixed to the inner wall of the outer shell and the other end fixed to the outer wall of the inner shell, so that the outer shell and the inner shell are coaxially arranged. The hydrocyclone includes a fixed cylinder and several blades, wherein the fixed cylinder is a hollow cylinder with open ends, and the axes of the several blades are evenly arranged on the outer wall of the fixed cylinder. The fuel nozzle is a hollow cylinder with a through hole at the center of its upstream end face for connecting with the fuel pipe, and a sealed end face at its downstream end. One end of the fuel pipe is connected to external fuel, and the other end passes through the outer shell stable section and the inner shell mixing section in sequence, and is sealed and fixed to the through hole at the center of the upstream end face of the fuel nozzle, so that the fuel nozzle is coaxially arranged in the inner shell mixing section. The fixed sleeve of the cyclone separator is fitted outside the fuel nozzle and is coaxially fixed to the fuel nozzle; The fuel nozzles are evenly arranged circumferentially on the side wall downstream of the cyclone separator. The solenoid valve is installed inside the fuel pipe and is used to control the opening and closing of the fuel pipe; The central cone-shaped blunt body is a cone, the diameter of its bottom surface is equal to the inner diameter of the detonation section, and a cone-shaped first groove is provided at the center of the bottom surface. The flame support plate is a hollow semi-cylinder with openings at both ends; The N flame-connecting support plates are circumferentially and evenly arranged between the ignition section and the central cone blunt body. Each plate is fixed at one end to the ignition section at a through hole on its upstream end face, and at the other end to the central cone blunt body, such that the cone tip of the central cone blunt body faces upstream and the central cone blunt body and the ignition section are coaxial. The openings of the flame-connecting support plates all face downstream, and the planar sidewalls of the flame-connecting support plates are coplanar with the inner wall of the upstream end face of the ignition section and the bottom surface of the central cone blunt body, respectively. The inner wall of the upstream end face of the ignition section and the bottom surface of the central cone blunt body are provided with grooves that correspond one-to-one with the flame-connecting support plate. The flame-connecting support plate, the corresponding groove on the inner wall of the upstream end face of the flame-connecting support plate, and the corresponding groove on the bottom surface of the central cone blunt body are collinear, forming a smooth, semi-cylindrical groove that is connected to the first groove. The P high-energy electric nozzles are evenly arranged circumferentially and pass through the outer shell and ignition section in sequence for ignition. The Q baffles are arranged in a ring shape and are evenly distributed at equal intervals within the detonation section. Their outer walls are all coaxially fixed to the inner wall of the detonation section, and the distance between adjacent baffles does not exceed twice the inner diameter of the detonation section. The inlet of the extended section is the pulse detonation combustion chamber inlet, which is connected to the compressor outlet; the contraction section forms the tail nozzle, and its outlet is the pulse detonation combustion outlet, which is connected to the gas turbine inlet pipe; the gas turbine is connected to the generator via a coupling. The controller is electrically connected to the solenoid valve and the P high-energy electrical nozzles respectively, and is used to control the operation of the solenoid valve and the P high-energy electrical nozzles.

2. The turbine power generation device based on pulse detonation according to claim 1, characterized in that, A guide fluid is provided on the downstream end face of the fuel nozzle; The guide body is a cone with a bottom diameter equal to the diameter of the downstream end face of the fuel nozzle, and the bottom surface of the guide body and the downstream end face of the fuel nozzle are coaxially fixed together.

3. The turbine power generation device based on pulse detonation according to claim 1, characterized in that, The P high-energy electric nozzles are all located on the mid-section of the ignition section.

4. The turbine power generation device based on pulse detonation according to claim 1, characterized in that, M is 3, N is 4, P is 2, and Q is 8.

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