A gas turbine with a parallel detonation combustion chamber

Abstract

This invention provides a gas turbine with a parallel detonation combustion chamber, comprising: a slow-burning combustion unit, including a generator, a low-pressure compressor, a high-pressure compressor, and a turbine connected sequentially via a first main shaft, and a slow-burning combustion chamber; the low-pressure compressor's inlet is open to the atmosphere, its exhaust port is connected to the high-pressure compressor, and the high-pressure compressor's exhaust port is connected to the slow-burning combustion chamber, allowing the compressed atmosphere to mix and burn with fuel, driving the turbine to perform work and power generation; and a detonation combustion unit, including a detonation turbine and a detonation turbine generator connected via a second main shaft, and a detonation combustion chamber; the low-pressure compressor's exhaust port is also connected to the detonation combustion chamber, allowing the compressed atmosphere to mix and burn with fuel via detonation, and the resulting detonation flue gas, after treatment, enters the detonation turbine, driving the detonation turbine to perform work and power generation, thereby powering the detonation turbine generator to generate electricity. This invention can effectively improve the overall cycle efficiency of the gas turbine and reduce pollutant emissions.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and more specifically to a gas turbine with a parallel detonation combustion chamber. Background Technology

[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 the gas engine, the gas is compressed, mixed with air, and burned at high temperatures. The high-temperature gases produced by combustion flow through a piston, causing it to move up and down, thus rotating the rotor. A generator is mounted on the rotor; as the rotor rotates, the generator also rotates, generating electricity. Auxiliary equipment includes cooling systems, oil systems, and exhaust systems, which help the gas engine operate normally. For example, the cooling system keeps the gas engine's temperature within a suitable range; the oil system provides lubricating oil to the gas engine; and the exhaust system removes the exhaust gases produced 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 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, aerospace, and aviation industries.

[0004] Traditional gas turbines primarily improve overall cycle thermal efficiency by increasing compressor pressure ratio and combustion chamber outlet temperature. However, due to limitations in materials, manufacturing processes, and aerodynamic design, significant increases in either compressor pressure ratio or combustion chamber outlet temperature are difficult, thus limiting overall power generation efficiency. Furthermore, traditional gas turbines face challenges in reducing pollutant emissions. In contrast, detonation combustion can significantly improve the overall cycle efficiency of gas turbines while reducing NOx emissions. However, detonation combustion also suffers from difficulties in starting up and a narrow operating range. Summary of the Invention

[0005] In view of this, this application provides a gas turbine with a parallel detonation combustion chamber to improve the overall cycle efficiency of the gas turbine while reducing pollutant emissions.

[0006] This application provides the following technical solution: a gas turbine with a parallel detonation combustion chamber, comprising:

[0007] The slow-burning combustion unit includes a generator, a low-pressure compressor, a high-pressure compressor, and a turbine, which are coaxially connected in sequence via a first main shaft. It also includes a slow-burning combustion chamber. The low-pressure compressor's inlet is open to the atmosphere for compressing and pressurizing it. The low-pressure compressor's outlet is connected to the high-pressure compressor for further compressing and pressurizing the atmosphere. The high-pressure compressor's outlet is connected to the slow-burning combustion chamber, allowing the compressed atmosphere to enter and mix with fuel for combustion. The resulting flue gas enters the turbine, driving it to perform work and power the generator to produce electricity.

[0008] The detonation combustion unit includes a detonation turbine and a detonation turbine generator connected in sequence via a second main shaft, and also includes a detonation combustion chamber; the exhaust port of the low-pressure compressor is also connected to the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and mixes with the fuel for detonation combustion;

[0009] The exhaust port of the high-pressure compressor is also connected to the exhaust port of the detonation combustion chamber, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber. After processing, the mixture enters the detonation turbine, which drives the detonation turbine to do work, thereby driving the detonation turbine generator to generate electricity.

[0010] According to one embodiment of this application, the detonation combustion unit further includes a deceleration diffuser, which is connected to the exhaust port of the high-pressure compressor and the exhaust port of the detonation combustion chamber respectively, so as to decelerate and diffuse the mixture before discharging it into the detonation turbine.

[0011] According to one embodiment of this application, a detonation combustion cooling system is provided outside the detonation combustion chamber for cooling the walls of the detonation combustion chamber.

[0012] According to one embodiment of this application, the detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber. The air inlet of the cooling channel is connected to the exhaust port of the low-pressure compressor, and the exhaust port of the cooling channel is connected to the exhaust port of the detonation combustion chamber. This allows the air compressed by the low-pressure compressor to cool the wall of the detonation combustion chamber within the cooling channel, and then mixes with the high-speed, high-pressure flue gas generated by detonation in the exhaust section of the detonation combustion chamber before being discharged.

[0013] According to one embodiment of this application, the detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber. The air inlet of the cooling channel is connected to a fuel input pipeline, and the exhaust outlet of the cooling channel is connected to the slow-burning combustion chamber and the detonation combustion chamber, respectively, so that fuel enters the cooling channel to cool the wall of the detonation combustion chamber, and then enters the slow-burning combustion chamber and the detonation combustion chamber, respectively.

[0014] According to one embodiment of this application, the detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber, and a circulating coolant flows through the cooling channel.

[0015] According to one embodiment of this application, it further includes a first heat exchanger and a second heat exchanger;

[0016] The second heat exchanger is connected between the exhaust port of the low-pressure compressor and the inlet of the detonation combustion chamber. The exhaust port of the detonation turbine is connected to the second heat exchanger, so that the compressed air at the outlet of the low-pressure compressor exchanges heat with the flue gas at the outlet of the detonation turbine before entering the detonation combustion chamber.

[0017] The first heat exchanger is connected between the exhaust port of the high-pressure compressor and the inlet of the slow-burning combustion chamber. The exhaust port of the turbine is connected to the first heat exchanger, so that the compressed air at the outlet of the high-pressure compressor exchanges heat with the flue gas at the outlet of the turbine before entering the slow-burning combustion chamber.

[0018] According to one embodiment of this application, the first spindle and the second spindle operate at different speeds.

[0019] According to one embodiment of this application, the detonation combustion chamber employs any one of the pressurized combustion methods, including continuous rotary detonation and pulse detonation.

[0020] According to one embodiment of this application, during the start-up process of the gas turbine, the starter generator operates in motor mode; when the gas turbine is in low operating condition and normal operating condition, the starter generator operates in generator mode.

[0021] This invention employs a parallel structure of a conventional combustion chamber and a detonation combustion chamber. The conventional combustion chamber primarily ensures stable operation of the gas turbine, providing stable inlet air conditions for the detonation combustion chamber, and simultaneously generating partial power according to operating conditions. The detonation combustion chamber is mainly used for high-efficiency, low-pollution power generation, improving the overall power generation efficiency of the gas turbine and reducing overall pollutant emissions.

[0022] Compared with the prior art, the beneficial effects that can be achieved by the above-mentioned at least one technical solution adopted in the embodiments of this specification include at least the following: compared with the traditional detonation gas turbine, it effectively improves the overall cycle efficiency of the gas turbine and reduces the overall pollutant emissions; at the same time, it solves the problems of difficult start-up and unstable continuous operation of pure detonation gas turbines; and by mixing the high-pressure compressor outlet air with the detonation gas, it solves the problem that the detonation gas temperature is too high and the turbine cannot work. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of a traditional gas turbine structure;

[0025] Figure 2 This is a schematic diagram of the gas turbine structure according to the first embodiment of the present invention;

[0026] Figure 3 This is a schematic diagram of the gas turbine structure according to the second embodiment of the present invention. Detailed Implementation

[0027] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0028] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments, providing a clear and complete description of the technical solutions of the present invention. Obviously, the described embodiments are merely some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0029] like Figure 1 As shown, Figure 1 This is a schematic diagram of a traditional gas turbine. Its mechanical connection structure consists of a starter generator, a low-pressure compressor, a high-pressure compressor, and a turbine connected via a main shaft. During gas turbine startup, the starter generator operates as an electric motor, driving the low-pressure compressor, high-pressure compressor, and turbine. In power generation mode, the turbine drives the low-pressure compressor, high-pressure compressor, and electric motor, with the electric motor outputting power. Specifically, the low-pressure compressor draws in air, pressurizes it, and then it enters the high-pressure compressor. The high-pressure compressor further pressurizes the air before it enters the combustion chamber to mix and burn with fuel. The resulting high-temperature flue gas drives the turbine, which in turn drives the low-pressure compressor, high-pressure compressor, and electric motor.

[0030] However, it is difficult to improve the overall power generation efficiency of traditional gas turbines, and it is also difficult to reduce pollutant emissions. Based on this, the present invention adopts a structure in parallel with a traditional slow-burning combustion chamber and a detonation combustion chamber to solve the above problems, and at the same time solves the problems of difficult start-up and unstable continuous operation of pure detonation gas turbines.

[0031] like Figure 2 As shown, an embodiment of the present invention provides a gas turbine with a parallel detonation combustor, comprising:

[0032] The slow-burning combustion unit includes a generator, a low-pressure compressor, a high-pressure compressor, and a turbine, which are coaxially connected in sequence via a first main shaft. It also includes a slow-burning combustion chamber. The low-pressure compressor's inlet is open to the atmosphere for compressing and pressurizing it. The low-pressure compressor's outlet is connected to the high-pressure compressor for further compressing and pressurizing the atmosphere. The high-pressure compressor's outlet is connected to the slow-burning combustion chamber, allowing the compressed atmosphere to enter and mix with fuel for combustion. The resulting flue gas enters the turbine, driving it to perform work and power the generator to produce electricity.

[0033] The detonation combustion unit includes a detonation turbine and a detonation turbine generator connected in sequence via a second main shaft, and also includes a detonation combustion chamber; the exhaust port of the low-pressure compressor is also connected to the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and mixes with the fuel for detonation combustion;

[0034] The exhaust port of the high-pressure compressor is also connected to the exhaust port of the detonation combustion chamber, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber. After processing, the mixture enters the detonation turbine, which drives the detonation turbine to do work, thereby driving the detonation turbine generator to generate electricity.

[0035] The structural configuration and working principle of this invention are as follows: In the mechanical connection section, the starter generator, low-pressure compressor, high-pressure compressor, and turbine are connected via a first main shaft and operate at the same speed. The detonation turbine and detonation turbine generator are connected via a second main shaft and operate at a second speed. During the start-up process of the gas turbine, the starter generator operates in motor mode, driving the low-pressure compressor, high-pressure compressor, and turbine to rotate via the first main shaft. Under low operating conditions, the starter generator operates in generator mode, with the turbine driving the low-pressure compressor, high-pressure compressor, and starter generator to rotate, and the starter generator outputs power. During the start-up process and under low operating conditions, the detonation turbine and detonation turbine generator do not operate. Under normal operating conditions, the starter generator operates in generator mode, with the turbine driving the low-pressure compressor, high-pressure compressor, and starter generator to rotate, and the starter generator outputs power; simultaneously, under normal operating conditions, the detonation turbine drives the detonation turbine generator to rotate, outputting power.

[0036] In this process, ambient air is pressurized by a low-pressure compressor and then passes through a high-pressure compressor and a detonation combustion chamber. The air entering the high-pressure compressor is further compressed and then enters the slow-burning combustion chamber to mix and burn with fuel. While the total pressure remains relatively constant, the total temperature rises, generating high-temperature flue gas that drives the turbine to perform work before being discharged into the atmosphere. In the detonation combustion chamber, the air and fuel mix and undergo detonation combustion, further increasing the total pressure and temperature. This produces high-temperature, high-pressure, high-speed gas, which mixes with the high-pressure air from the high-pressure compressor and, after processing, forms high-temperature flue gas with temperature, pressure, and velocity suitable for the detonation turbine. This solves the problem of excessively high detonation gas temperatures preventing the turbine from operating, improving turbine lifespan and reliability, and reducing costs.

[0037] The first and second spindles mentioned above operate at different speeds.

[0038] Specifically, since the low-pressure compressor, high-pressure compressor, and turbine in the first main shaft have large flow rates, the rotational speed of the first main shaft is relatively low while meeting the aerodynamic design requirements. The second main shaft is a detonation combustion chamber, and the flow rate is drawn from the compressor outlet. Therefore, the flow rate is less than the outlet flow rate of a conventional slow-burning combustion chamber, so the rotational speed of the second main shaft is relatively high.

[0039] In one specific embodiment, the detonation combustion unit further includes a decelerating diffuser, which is connected to both the exhaust port of the high-pressure compressor and the exhaust port of the detonation combustion chamber. This diffuser decelerates and diffuses the gas mixture before it is discharged into the detonation turbine. The decelerating diffuser processes the high-temperature, high-pressure, and high-speed gas, while simultaneously mixing it with high-pressure air from the high-pressure compressor. The high-temperature, high-pressure, and high-speed gas is further decelerated and diffused in the decelerating diffuser, resulting in a further increase in static pressure and a decrease in temperature. The gas is then discharged into the detonation turbine, where it drives the turbine to perform work before being released into the atmosphere.

[0040] Because the detonation combustion chamber operates under high pressure and temperature, a cooling system is required to maintain the gas engine temperature within a suitable range. Therefore, in this embodiment of the invention, a detonation combustion cooling system is installed outside the detonation combustion chamber to cool its walls.

[0041] In one specific embodiment, air discharged from a low-pressure compressor 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 inlet of the cooling channel is connected to the exhaust port of the low-pressure compressor, and the exhaust port of the cooling channel is connected to the exhaust port of the detonation combustion chamber. This allows the air compressed by the low-pressure compressor to cool the wall of the detonation combustion chamber within the cooling channel. The air then mixes with the high-speed, high-pressure flue gas generated by detonation in the exhaust section of the detonation combustion chamber before being discharged and entering the deceleration diffuser.

[0042] In another specific embodiment, fuel cooling is used to cool the detonation combustion chamber. The specific structure is as follows: the detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber. The air inlet of the cooling channel is connected to a fuel input pipeline, and the exhaust outlet of the cooling channel is connected to both the slow-burning combustion chamber and the detonation combustion chamber. This allows fuel to enter the cooling channel to cool the wall of the detonation combustion chamber before entering both the slow-burning and detonation combustion chambers. Furthermore, regulating control valves are installed on the fuel input pipelines connecting to the slow-burning and detonation combustion chambers for easy operation and control.

[0043] In another specific embodiment, an external liquid cooling circulation method can be 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, through which circulating coolant flows, specifically through a circulating pump.

[0044] In other embodiments, a structure combining multiple cooling methods such as air cooling from the low-pressure compressor exhaust, fuel cooling, and external liquid cooling circulation can be adopted. These methods are independently controlled by control valves on the pipelines and can be selected based on the high-temperature resistance of the detonation combustion chamber.

[0045] In another embodiment of the invention, such as Figure 3 As shown, it also includes a first heat exchanger and a second heat exchanger;

[0046] The second heat exchanger is connected between the exhaust port of the low-pressure compressor and the inlet of the detonation combustion chamber. The exhaust port of the detonation turbine is connected to the second heat exchanger, so that the compressed air at the outlet of the low-pressure compressor exchanges heat with the flue gas at the outlet of the detonation turbine. After the temperature rises, the flue gas enters the detonation combustion chamber. The exhaust gas at the outlet of the deceleration diffuser enters the detonation turbine and drives the detonation turbine to do work. After the exhaust gas enters the second heat exchanger and exchanges heat with the air at the outlet of the low-pressure compressor, it is discharged into the atmosphere.

[0047] The first heat exchanger is connected between the exhaust port of the high-pressure compressor and the inlet of the slow-burning combustion chamber. The exhaust port of the turbine is connected to the first heat exchanger, so that the compressed air at the outlet of the high-pressure compressor exchanges heat with the flue gas at the outlet of the turbine. After the temperature rises, the flue gas enters the slow-burning combustion chamber. The exhaust gas at the outlet of the slow-burning combustion chamber enters the turbine to do work, and then enters the first heat exchanger to exchange heat with the air at the outlet of the high-pressure compressor before being discharged into the atmosphere.

[0048] A flue gas heat exchanger is an industrial device used to heat and cool flue gas in industrial processes. It typically consists of a series of plates or pipes through which heat is exchanged via flowing cooling water or other fluids. Flue gas heat exchangers are used in many different applications, including boilers, gas turbines, and steam turbines, to improve the efficiency of these devices and reduce their emissions. Furthermore, flue gas heat exchangers can be used to recover waste heat, thereby reducing energy consumption and costs.

[0049] The gas turbine in this embodiment is a regenerative cycle gas turbine equipped with a flue gas heat exchanger. By exchanging heat between the flue gas discharged from the gas turbine and the air at the compressor outlet, the temperature of the air entering the combustion chamber from the compressor outlet is increased. Under the same combustion chamber outlet temperature conditions, fuel consumption can be reduced and the power generation efficiency of the gas turbine can be improved.

[0050] In this embodiment, the flue gas from the detonation combustion power generation outlet also exchanges heat with the air from the compressor outlet through a heat exchanger, thereby increasing the temperature of the air entering the detonation combustion chamber, reducing fuel consumption, and improving system efficiency.

[0051] In this embodiment of the invention, the detonation combustion chamber can be a continuous rotary detonation, pulse detonation, or other forms of pressurized combustion technology.

[0052] In this embodiment of the invention, a structure combining a traditional slow-ignition combustor and a detonation combustor is adopted. The traditional slow-ignition combustor is mainly responsible for the stable operation of the gas turbine, providing stable inlet air conditions for the detonation combustor, and simultaneously generating partial power according to operating conditions. The detonation combustor is mainly responsible for high-efficiency, low-pollution power generation, improving the overall power generation efficiency of the gas turbine and reducing overall pollutant emissions. Furthermore, it solves the problems of difficult start-up and unstable continuous operation of pure detonation gas turbines.

[0053] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A gas turbine with a parallel detonation combustion chamber, characterized in that, include: The slow-burning combustion unit includes a generator, a low-pressure compressor, a high-pressure compressor, and a turbine, which are coaxially connected in sequence via a first main shaft. It also includes a slow-burning combustion chamber. The low-pressure compressor's inlet is open to the atmosphere for compressing and pressurizing it. The low-pressure compressor's outlet is connected to the high-pressure compressor for further compressing and pressurizing the atmosphere. The high-pressure compressor's outlet is connected to the slow-burning combustion chamber, allowing the compressed atmosphere to enter and mix with fuel for combustion. The resulting flue gas enters the turbine, driving it to perform work and power the generator to produce electricity. The detonation combustion unit includes a detonation turbine and a detonation turbine generator connected in sequence via a second main shaft, and also includes a detonation combustion chamber; the exhaust port of the low-pressure compressor is also connected to the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and mixes with the fuel for detonation combustion; The exhaust port of the high-pressure compressor is also connected to the exhaust port of the detonation combustion chamber, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber. After the mixture is processed, it enters the detonation turbine, which drives the detonation turbine to do work, thereby driving the detonation turbine generator to generate electricity. A detonation combustion cooling system is installed outside the detonation combustion chamber to cool the walls of the detonation combustion chamber. The detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber. The air inlet of the cooling channel is connected to the exhaust port of the low-pressure compressor, and the exhaust port of the cooling channel is connected to the exhaust port of the detonation combustion chamber. This allows the air compressed by the low-pressure compressor to cool the walls of the detonation combustion chamber within the cooling channel, and then mixes with the high-speed, high-pressure flue gas generated by detonation in the exhaust section of the detonation combustion chamber before being discharged.

2. The gas turbine with a parallel detonation combustion chamber according to claim 1, characterized in that, The detonation combustion unit also includes a deceleration diffuser, which is connected to the exhaust port of the high-pressure compressor and the exhaust port of the detonation combustion chamber, respectively, so as to decelerate and diffuse the mixture before discharging it into the detonation turbine.

3. The gas turbine with a parallel detonation combustion chamber according to claim 1, characterized in that, The detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber. The air inlet of the cooling channel is connected to a fuel input pipeline, and the exhaust outlet of the cooling channel is connected to the slow-burning combustion chamber and the detonation combustion chamber, respectively, so that the fuel enters the cooling channel to cool the wall of the detonation combustion chamber, and then enters the slow-burning combustion chamber and the detonation combustion chamber, respectively.

4. The gas turbine with a parallel detonation combustion chamber according to claim 1, characterized in that, The detonation combustion cooling system includes a cooling channel surrounding the outer wall of the detonation combustion chamber, through which a circulating coolant flows.

5. The gas turbine with a parallel detonation combustion chamber according to claim 1, characterized in that, It also includes a first heat exchanger and a second heat exchanger; The second heat exchanger is connected between the exhaust port of the low-pressure compressor and the inlet of the detonation combustion chamber. The exhaust port of the detonation turbine is connected to the second heat exchanger, so that the compressed air at the outlet of the low-pressure compressor exchanges heat with the flue gas at the outlet of the detonation turbine before entering the detonation combustion chamber. The first heat exchanger is connected between the exhaust port of the high-pressure compressor and the inlet of the slow-burning combustion chamber. The exhaust port of the turbine is connected to the first heat exchanger, so that the compressed air at the outlet of the high-pressure compressor exchanges heat with the flue gas at the outlet of the turbine before entering the slow-burning combustion chamber.

6. The gas turbine with a parallel detonation combustion chamber according to claim 1, characterized in that, The first spindle and the second spindle operate at different speeds.

7. The gas turbine with a parallel detonation combustion chamber according to claim 1, characterized in that, The detonation combustion chamber employs any one of the pressurized combustion methods, including continuous rotary detonation and pulse detonation.

8. The gas turbine with a parallel detonation combustion chamber according to claim 1, characterized in that, During the start-up process of the gas turbine, the starter generator operates in motor mode; when the gas turbine is in low operating condition and normal operating condition, the starter generator operates in generator mode.

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