A gas turbine based on a supercharged heat exchanger and a control method thereof

Abstract

The present invention provides a gas turbine based on a supercharged heat exchanger and a control method thereof. The gas turbine comprises: a gas turbine body comprising a starter generator, a compressor, and a turbine coaxially connected in sequence via a main shaft; a detonation combustion chamber and a supercharged heat exchanger. The compressor's air inlet admits air, and its exhaust port is connected to the first inlet end of the supercharged heat exchanger for further pressurizing and heating the air. The first exhaust end of the supercharged heat exchanger is connected to the air inlet of the detonation combustion chamber for mixing air and fuel for detonation combustion. The exhaust port of the detonation combustion chamber is connected to the second inlet end of the supercharged heat exchanger for allowing detonation flue gas to enter the supercharged heat exchanger to pressurize and heat the air from the compressor. The second exhaust end of the supercharged heat exchanger is connected to the turbine, so that the detonation flue gas drives the turbine to perform work, thereby driving the starter generator to generate electricity. The present invention can significantly improve the overall cycle efficiency of the gas turbine, thereby improving the power generation efficiency of the system.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine based on a supercharged heat exchanger and a control method thereof. Background Art

[0002] A gas turbine is a mechanical device that uses the energy of natural gas to generate power. It typically consists of three parts: a gas engine, a generator, and auxiliary equipment. In a gas engine, compressed gas is mixed with air and burned at high temperatures. The resulting high-temperature gases flow through the piston, causing it to move up and down, thereby driving the rotor. A generator is mounted on the rotor, and when the rotor rotates, the generator also rotates, generating electricity. Auxiliary equipment includes cooling systems, oil systems, and exhaust systems, all of which help the gas engine operate properly. For example, the cooling system maintains the gas engine's temperature within a suitable range; the oil system provides lubricating oil for the gas engine; and the exhaust system removes exhaust gases generated by the gas engine.

[0003] Detonation combustion is a combustion technology that achieves combustion through the propagation of a detonation wave. A detonation wave is a shock wave that propagates in a detonation reaction, enabling a rapid reaction between reactants and oxygen upon contact. Detonation combustion technology can improve combustion efficiency, reduce pollution, and operate at higher pressures and temperatures. It is currently used in the automotive, aviation, and aerospace industries.

[0004] Traditional gas turbines primarily improve their overall cycle thermal efficiency by increasing the compressor pressure ratio and combustor outlet temperature. However, due to limitations in materials, processes, and aerodynamic design, significant increases in either the compressor pressure ratio or combustor outlet temperature are difficult, limiting overall power generation efficiency. Traditional gas turbines also face challenges in reducing pollutant emissions. Compared to traditional technologies, detonation combustion can significantly improve the overall cycle efficiency of gas turbines while reducing NOx emissions. However, detonation combustion also presents challenges such as difficulty starting and a narrow operating range. Summary of the Invention

[0005] In view of this, an embodiment of the present application provides a gas turbine based on a supercharged heat exchanger and a control method thereof, so as to significantly improve the overall cycle efficiency of the gas turbine and thereby improve the power generation efficiency of the system.

[0006] The embodiment of the present application provides the following technical solution: a gas turbine based on a supercharged heat exchanger, comprising:

[0007] A gas turbine main body, the gas turbine main body comprising a generator, a compressor and a turbine coaxially connected in sequence via a main shaft;

[0008] The system further comprises a detonation combustion chamber and a supercharged heat exchanger, wherein the air is introduced into the air inlet of the compressor for compressing and supercharging the air, the exhaust port of the compressor is connected to the first air inlet end of the supercharged heat exchanger for further supercharging and increasing the temperature of the air in the supercharged heat exchanger, and the first exhaust end of the supercharged heat exchanger is connected to the air inlet end of the detonation combustion chamber for allowing the supercharged and heated air to enter the detonation combustion chamber and mix with the fuel for detonation combustion;

[0009] The exhaust port of the detonation combustion chamber is connected to the second air inlet end of the supercharged heat exchanger, so as to allow the detonation flue gas generated after the detonation combustion to enter the supercharged heat exchanger, and to pressurize and heat the air from the compressor through shock wave energy conversion. The second exhaust end of the supercharged heat exchanger is connected to the turbine, so as to allow the detonation flue gas after shock wave energy conversion to enter the turbine, drive the turbine to do work, and drive the generator to generate electricity.

[0010] According to one embodiment of the present application, the boost heat exchanger is composed of a plurality of boost heat exchange tubes connected in parallel, and each of the boost heat exchange tubes forms an independent boost heat exchange channel.

[0011] According to one embodiment of the present application, the first air inlet end of each of the boost heat exchange tubes is connected to the exhaust port of the compressor, and the second air inlet end is connected to the exhaust port of the detonation combustion chamber; the first exhaust end of each of the boost heat exchange tubes is connected to the air inlet of the detonation combustion chamber, and the second exhaust end is connected to the turbine; and control valves are respectively provided on the first air inlet end, the second air inlet end, the first exhaust end and the second exhaust end.

[0012] According to one embodiment of the present application, the control valves on the first air inlet end, the second air inlet end, the first exhaust end, and the second exhaust end are all opened or closed in a pulsed intermittent manner.

[0013] According to one embodiment of the present application, a detonation combustion cooling system is provided outside the detonation combustion chamber for cooling the wall surface of the detonation combustion chamber.

[0014] According to one embodiment of the present application, the detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, the inlet of the cooling channel is connected to the fuel input pipeline, and the outlet of the cooling channel is connected to the fuel inlet of the detonation combustion chamber, so that the fuel enters the cooling channel to cool the wall of the detonation combustion chamber and then enters the detonation combustion chamber.

[0015] According to one embodiment of the present application, a regulating control valve is provided on the fuel input pipeline.

[0016] According to one embodiment of the present application, the detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, and a circulating coolant flows into the cooling channel.

[0017] According to one embodiment of the present application, the detonation combustion chamber adopts any one of the boosted combustion modes including continuous rotating detonation and pulse detonation.

[0018] An embodiment of the present invention further provides a control method for a gas turbine based on a supercharged heat exchanger as described above, the control method comprising the following steps:

[0019] Step (1) closing the control valves at the first exhaust end and the second exhaust end of the supercharged heat exchanger, first opening the control valve at the first air inlet end, closing it after a preset time, and simultaneously opening the control valve at the second air inlet end, so that the compressor outlet air and the detonation combustion chamber outlet flue gas enter the supercharged heat exchanger in sequence;

[0020] Step (2) After a preset time, close the control valve at the second air inlet end and simultaneously open the control valve at the first air outlet end;

[0021] Step (3) After a preset time, open the control valve of the first air inlet end;

[0022] Step (4) After a preset time, close the control valve of the first exhaust end;

[0023] Step (5) After a preset time, close the control valve at the first air inlet end and open the control valve at the second air outlet end;

[0024] Step (6) After a preset time, open the control valve of the second air inlet end;

[0025] Step (7) After a preset time, close the control valve of the second exhaust end;

[0026] Step (8) Repeat steps (2)-(7).

[0027] Compared to the prior art, the beneficial effects achieved by at least one of the above-mentioned technical solutions employed in the embodiments of this specification include at least the following: In this embodiment, the high-temperature flue gas at the combustion chamber outlet is used to further supercharge the air at the compressor outlet. The supercharged air at the outlet of the supercharged heat exchanger enters the detonation combustion chamber, where it is further supercharged using detonation combustion technology (supercharged combustion technology) to generate high-temperature, high-pressure flue gas that enters the turbine to produce work. Compared to traditional combustion engines, the gas turbine of the present invention improves overall cycle efficiency through double supercharging after the compressor, thereby improving the system's power generation efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0029] Figure 1 1 is a schematic structural diagram of a gas turbine according to an embodiment of the present invention;

[0030] Figure 2 1 is a schematic structural diagram of a booster heat exchanger according to an embodiment of the present invention;

[0031] Figure 3 Schematic diagram of the control process of the boost heat exchanger according to an embodiment of the present invention. DETAILED DESCRIPTION

[0032] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0033] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of this application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments, and the technical solutions of the present invention will be clearly and completely described. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0034] like Figure 1 As shown, an embodiment of the present invention provides a gas turbine based on a boost heat exchanger, comprising:

[0035] A gas turbine main body, the gas turbine main body comprising a generator, a compressor and a turbine coaxially connected in sequence via a main shaft;

[0036] It also includes a detonation combustion chamber and a supercharged heat exchanger, wherein the air is introduced into the air inlet of the compressor for compressing and supercharging the air, and the exhaust port of the compressor is connected to the first air inlet end of the supercharged heat exchanger for further pressurizing and heating the air in the supercharged heat exchanger, and the first exhaust end of the supercharged heat exchanger is connected to the air inlet of the detonation combustion chamber for allowing the air after pressurization and temperature increase to enter the detonation combustion chamber and mix with fuel for detonation combustion; the exhaust port of the detonation combustion chamber is connected to the second air inlet end of the supercharged heat exchanger for allowing the detonation flue gas generated after detonation combustion to enter the supercharged heat exchanger, and supercharge and heat the air from the compressor through shock wave energy conversion, and the second exhaust end of the supercharged heat exchanger is connected to the turbine for allowing the detonation flue gas after shock wave energy conversion to enter the turbine, drive the turbine to do work, and drive the generator to generate electricity.

[0037] The structural arrangement and operating principle of the embodiment of the present invention are as follows: In the mechanical connection, the starter-generator, compressor, and turbine are connected via a main shaft and operate at the same speed. During the gas turbine startup process, the starter-generator operates in motor mode, driving the compressor and turbine via the main shaft. Under low operating conditions, the starter-generator operates in generator mode, with the turbine driving the compressor and starter-generator, and the starter-generator outputs power. Under normal operating conditions, the starter-generator operates in generator mode, with the turbine driving the compressor and starter-generator, and the starter-generator outputs power.

[0038] Among them, atmospheric air enters the compressor, is pressurized by the compressor, enters the supercharged heat exchanger to further increase the temperature and pressure, and then enters the detonation combustion chamber, where it is mixed with fuel and detonated and combusted. The temperature and pressure are further increased by detonation combustion to form high-temperature and high-pressure combustion gas. The high-temperature and high-pressure combustion gas at the outlet of the detonation combustion chamber enters the supercharged heat exchanger, and the air from the compressor is pressurized and heated by shock wave energy conversion. After the temperature and pressure of the combustion gas itself are reduced, it enters the turbine to drive the turbine to do work. The gas turbine structure of the present invention has two-stage supercharging, which improves the overall cycle efficiency compared to traditional gas turbines, thereby improving the system's power generation efficiency and reducing pollutant emissions. In addition, the air enters the detonation combustion chamber after passing through the supercharged heat exchanger, which also solves the problems of difficult detonation combustion startup and narrow working range.

[0039] On this basis, the high-temperature and high-pressure flue gas at the outlet of the detonation combustion chamber passes through the boost heat exchanger and then enters the turbine, which reduces the temperature of the flue gas at the turbine inlet, solves the problem of the detonation flue gas temperature being too high and the turbine being unable to work, improves the life and reliability of the turbine, and reduces costs.

[0040] At the same time, the booster heat exchanger intermittently inhales and discharges the compressor outlet air and the combustion chamber outlet gas, and cools the booster heat exchanger through the compressor outlet air, thereby reducing the temperature of the booster heat exchanger itself, which is beneficial to improving life and reliability and reducing costs.

[0041] In one embodiment of the present invention, Figure 2 As shown, the boost heat exchanger is composed of a plurality of boost heat exchange tubes connected in parallel, and each of the boost heat exchange tubes forms an independent boost heat exchange channel.

[0042] Specifically, the first air inlet end of each of the boost heat exchange tubes is connected to the exhaust port of the compressor, and the second air inlet end is connected to the exhaust port of the detonation combustion chamber; the first air outlet end of each of the boost heat exchange tubes is connected to the air inlet of the detonation combustion chamber, and the second air outlet end is connected to the turbine; and control valves are respectively provided on the first air inlet end, the second air inlet end, the first air outlet end, and the second air outlet end. The control valves on the first air inlet end, the second air inlet end, the first air outlet end, and the second air outlet end are all opened or closed in a pulsed intermittent manner.

[0043] In this embodiment, when a single boost heat exchange tube is working, both the intake and exhaust are pulsed intermittent. After multiple boost heat exchange tubes are connected in parallel, the opening and closing time of different boost heat exchange tube channels are adjusted to achieve continuous intake of compressor outlet air and detonation combustion chamber outlet gas. After boosting and heat exchange, the air continuously enters the detonation combustion chamber and turbine, ensuring continuous and stable operation of the gas turbine.

[0044] In one embodiment, the control method of a gas turbine based on a boost heat exchanger of the present invention comprises the following steps:

[0045] Step (1) closing the control valves at the first exhaust end and the second exhaust end of the supercharged heat exchanger, first opening the control valve at the first air inlet end, closing it after a preset time, and simultaneously opening the control valve at the second air inlet end, so that the compressor outlet air and the detonation combustion chamber outlet flue gas enter the supercharged heat exchanger in sequence;

[0046] Step (2) After a preset time, close the control valve at the second air inlet end and simultaneously open the control valve at the first air outlet end;

[0047] Step (3) After a preset time, open the control valve of the first air inlet end;

[0048] Step (4) After a preset time, close the control valve of the first exhaust end;

[0049] Step (5) After a preset time, close the control valve at the first air inlet end and open the control valve at the second air outlet end;

[0050] Step (6) After a preset time, open the control valve of the second air inlet end;

[0051] Step (7) After a preset time, close the control valve of the second exhaust end;

[0052] Step (8) Repeat steps (2)-(7).

[0053] The above control method of this embodiment is as follows: Figure 3 As shown, port 1 of the boost heat exchange tube is the air inlet end, and port 2 is the exhaust end. Under normal operating conditions:

[0054] 1. In a single booster heat exchanger tube, the left side is the combustion chamber outlet flue gas, and the right side is the compressor outlet air.

[0055] 2. Open the first exhaust end valve of port 2, connect the boost heat exchange tube to the detonation combustion chamber inlet pipe, and the compressor outlet air on the right side of the boost heat exchange tube enters the combustion chamber inlet pipe.

[0056] 3. As the air at the compressor outlet enters the combustion chamber inlet, the pressure in the pipeline decreases, the first inlet valve of port 1 is opened, the left side of the boost heat exchange tube is connected to the compressor outlet pipeline, and the air at the compressor outlet continues to enter the boost heat exchange tube.

[0057] At this time, the left side of the pipe is the "compressor outlet air" that continuously enters, the middle is the "combustion chamber outlet flue gas", and the right side is the "compressor outlet air" that continuously enters the combustion chamber inlet pipe;

[0058] At this time, the "combustion chamber outlet flue gas" in the middle not only continues to move to the right, but also expands at the same time to increase the temperature and pressure of the compressor outlet air on both sides because its total temperature is always higher than that of the compressor outlet.

[0059] 4. When the "compressor outlet air" on the right side is completely exhausted in the previous step, close the first exhaust end valve of port 2. At this time, the air in the pipeline is "compressor outlet air" on the left side and "combustion chamber outlet flue gas" on the right side.

[0060] 5. When the "compressor outlet air" completely enters the "boost heat exchange pipe", open the second exhaust end valve of port 2, and connect the right side of the boost heat exchange pipe to the "turbine inlet pipe". The flue gas from the right combustion chamber outlet continues to enter the "turbine inlet pipe" to the right.

[0061] 6. As the "combustion chamber outlet flue gas" enters the "turbine inlet pipe", the pressure in the boost heat exchange pipe drops, the second air inlet valve of port 1 is opened, and the left side of the boost heat pipe is connected to the "combustion chamber outlet pipe". At this time, the combustion chamber outlet flue gas continues to enter the "boost heat exchange pipe";

[0062] The "combustion chamber outlet flue gas" is formed on the left, the "compressor outlet air" is formed in the middle, and the "combustion chamber outlet flue gas" is formed on the right. In addition to continuing to move to the right, the "combustion chamber outlet flue gas" in the middle also expands at the same time to increase the temperature and pressure of the compressor outlet air because its total temperature is always higher than that of the compressor outlet.

[0063] 7. When the "combustion chamber outlet flue gas" is completely discharged into the "turbine inlet duct", close the second exhaust end valve of port 2, forming the "combustion chamber outlet flue gas" on the left and the "compressor outlet air" on the right. When the "compressor outlet air" completely enters the duct, close the second intake end valve of port 1, restore to the initial state, and repeat 2.

[0064] Among them, the N "boost heat exchange tubes" in the boost heat exchanger are respectively in different working conditions in the above-mentioned working processes 2 to 7.

[0065] For example, when the total number of tubes is 48, the first tube is in state 2, the second tube is in state 3... the sixth tube is in state 7, the seventh tube is in state 2, and the cycle continues in sequence... the 48th tube is in state 7, ensuring the continuity of air intake and exhaust in the "detonation combustion chamber outlet pipe", "compressor outlet pipe", "detonation combustion chamber inlet pipe" and "turbine inlet pipe".

[0066] During specific implementation, the above-mentioned preset time needs to be set according to the specific situation. For example, from opening to closing of the exhaust end, the opening time needs to ensure that the air at the compressor outlet is completely discharged into the detonation combustion chamber inlet, but it should not be too long to prevent the flue gas at the combustion chamber outlet from entering the combustion chamber inlet. The preset time in each of the above steps is inconsistent and needs to be calculated and determined in advance through simulation calculations based on the intake speed and expansion speed. In addition, the valve opening and closing time can also be actively controlled in real time by monitoring the airflow temperature on the left and right sides of the boost heat exchange tube to determine whether the air and flue gas are exhausted.

[0067] According to the above control method, when the supercharging heat exchange pipe is connected to the compressor outlet, the compressor will draw air into the supercharging heat exchange pipe. After a preset period of time, it is then connected to the outlet of the detonation combustion chamber. As the high-temperature, high-pressure gas at the outlet of the supercharging heat exchange pipe enters the supercharging heat exchange pipe, the exhaust end on the other side of the supercharging heat exchange pipe is closed. Within the pipe, the detonation gas further compresses the compressor outlet air just inhaled, further increasing the air's temperature and pressure. After being pressurized, the air enters the detonation combustion chamber. The inlet end of the supercharging heat exchange pipe is then connected to the compressor outlet, drawing in the compressor outlet air. The exhaust end of the supercharging heat exchange pipe is closed. After a preset period of time, the inlet end of the supercharging heat exchange pipe is closed, and the exhaust end is connected to the turbine. After heat exchange and pressurization, the detonation flue gas enters the turbine. After another preset period of time, the inlet end of the supercharging heat exchange pipe is reconnected to the outlet of the detonation combustion chamber. The exhaust end valve is then closed. Repeating this operation achieves continuous and stable control of the gas turbine.

[0068] Since the detonation combustion chamber is a high pressure and temperature working environment, a cooling system is required to keep the temperature of the gas engine within an appropriate range. Therefore, in an embodiment of the present invention, a detonation combustion cooling system is provided outside the detonation combustion chamber to cool the wall surface of the detonation combustion chamber.

[0069] In another specific embodiment, fuel cooling is used to cool the detonation combustion chamber. Specifically, the detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber. The cooling channel's air inlet is connected to a fuel input pipeline, and the cooling channel's exhaust is connected to the detonation combustion chamber's fuel inlet. Fuel enters the cooling channel to cool the detonation combustion chamber's walls before entering the detonation combustion chamber. Furthermore, a regulating control valve is provided on the fuel input pipeline connected to the detonation combustion chamber to facilitate operational control.

[0070] In another specific embodiment, an external liquid cooling cycle can be used to cool the detonation combustion chamber. Specifically, the detonation combustion cooling system includes a cooling channel disposed around the outer wall of the detonation combustion chamber, into which circulating coolant flows, specifically by a circulating pump.

[0071] In other embodiments, a structure combining multiple cooling methods such as the above-mentioned fuel cooling and external liquid cooling circulation can also be adopted, which can be independently controlled by control valves on the pipeline and can be selected for use according to the high temperature resistance performance of the detonation combustion chamber.

[0072] In an embodiment of the present invention, the detonation combustion chamber may be a continuous rotating detonation, a pulse detonation, or other forms of pressurized combustion technology.

[0073] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A gas turbine based on a supercharged heat exchanger, characterized in that: include: A gas turbine main body, the gas turbine main body comprising a generator, a compressor and a turbine coaxially connected in sequence via a main shaft; The system further comprises a detonation combustion chamber and a supercharged heat exchanger, wherein the air is introduced into the air inlet of the compressor for compressing and supercharging the air, the exhaust port of the compressor is connected to the first air inlet end of the supercharged heat exchanger for further supercharging and increasing the temperature of the air in the supercharged heat exchanger, and the first exhaust end of the supercharged heat exchanger is connected to the air inlet end of the detonation combustion chamber for allowing the supercharged and heated air to enter the detonation combustion chamber and mix with the fuel for detonation combustion; The exhaust port of the detonation combustion chamber is connected to the second air inlet end of the supercharged heat exchanger, so as to allow the detonation flue gas generated after the detonation combustion to enter the supercharged heat exchanger, and to pressurize and heat the air from the compressor through shock wave energy conversion. The second exhaust end of the supercharged heat exchanger is connected to the turbine, so as to allow the detonation flue gas after shock wave energy conversion to enter the turbine, drive the turbine to do work, and drive the generator to generate electricity.

2. The gas turbine based on a boost heat exchanger according to claim 1, characterized in that: The boost heat exchanger is composed of a plurality of boost heat exchange tubes connected in parallel, and each of the boost heat exchange tubes forms an independent boost heat exchange channel.

3. The gas turbine based on a supercharged heat exchanger according to claim 2, characterized in that: The first air inlet end of each of the boost heat exchange tubes is connected to the exhaust port of the compressor, and the second air inlet end is connected to the exhaust port of the detonation combustion chamber; the first exhaust end of each of the boost heat exchange tubes is connected to the air inlet of the detonation combustion chamber, and the second exhaust end is connected to the turbine; and control valves are respectively provided on the first air inlet end, the second air inlet end, the first exhaust end, and the second exhaust end.

4. The gas turbine based on a boost heat exchanger according to claim 3, characterized in that: The control valves on the first air inlet end, the second air inlet end, the first exhaust end and the second exhaust end are all opened or closed in a pulsed intermittent manner.

5. The gas turbine based on a boost heat exchanger according to claim 1, characterized in that: A detonation combustion cooling system is provided outside the detonation combustion chamber for cooling the wall surface of the detonation combustion chamber.

6. The gas turbine based on a boost heat exchanger according to claim 5, characterized in that: The detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, the inlet of the cooling channel is connected to the fuel input pipeline, and the outlet of the cooling channel is connected to the fuel inlet of the detonation combustion chamber, so that the fuel enters the cooling channel to cool the wall of the detonation combustion chamber and then enters the detonation combustion chamber.

7. The gas turbine based on a boost heat exchanger according to claim 6, characterized in that: A regulating control valve is provided on the fuel input pipeline.

8. The gas turbine based on a boost heat exchanger according to claim 5, characterized in that: The detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, and a circulating coolant flows into the cooling channel.

9. The gas turbine based on a boost heat exchanger according to claim 1, characterized in that: The detonation combustion chamber adopts any one of the pressurized combustion modes including continuous rotating detonation and pulse detonation.

10. A control method for a gas turbine based on a boost heat exchanger according to any one of claims 1 to 9, characterized in that: The control method comprises the following steps: Step (1) closing the control valves at the first exhaust end and the second exhaust end of the supercharged heat exchanger, first opening the control valve at the first air inlet end, closing it after a preset time, and simultaneously opening the control valve at the second air inlet end, so that the compressor outlet air and the detonation combustion chamber outlet flue gas enter the supercharged heat exchanger in sequence; Step (2) After a preset time, close the control valve at the second air inlet end and simultaneously open the control valve at the first air outlet end; Step (3) After a preset time, open the control valve of the first air inlet end; Step (4) After a preset time, close the control valve of the first exhaust end; Step (5) After a preset time, close the control valve at the first air inlet end and open the control valve at the second air outlet end; Step (6) After a preset time, open the control valve of the second air inlet end; Step (7) After a preset time, close the control valve of the second exhaust end; Step (8) Repeat steps (2)-(7).

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