A gas turbine system with a distributed detonation combustion chamber

Abstract

The present invention provides a gas turbine system with a distributed detonation combustor, comprising: a gas turbine main body including a deflagration combustor, a compressor and a turbine connected coaxially, wherein the air inlet of the compressor admits air, and the exhaust port is connected to the deflagration combustor to mix and burn the compressed air with fuel; the flue gas generated by the deflagration combustor drives the turbine to do work and drives the compressor to operate; a detonation power generation system including multiple groups of detonation combustors arranged in parallel, and a turbine generator set including a detonation turbine and a generator connected coaxially. The air inlet of each group of detonation combustors is communicated with the exhaust port of the compressor to mix and detonate-burn the compressed air with fuel, and the exhaust ports of the detonation combustors are respectively communicated with the detonation turbine to make the detonation flue gas drive the detonation turbine to do work and drive the generator to generate electric energy. The present invention can expand the power adjustment range of detonation combustion, meet the requirements of long-term stable operation, and improve the overall cycle efficiency of the gas turbine.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and more particularly to a gas turbine system with a distributed detonation combustor. Background Art

[0002] A gas turbine is a mechanical device that utilizes the energy of gas to generate power. It generally 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 temperature. The high-temperature gas generated by combustion flows through the piston, causing the piston to move up and down, thereby driving the rotor to rotate. A generator is installed on the rotor, and when the rotor rotates, the generator also rotates to generate electrical energy. The auxiliary equipment includes a cooling system, an oil circuit system, an exhaust system, etc. Their functions are to help the gas engine work properly. For example, the cooling system can keep the temperature of the gas engine within a suitable range; the oil circuit system can provide lubricating oil for the gas engine; and the exhaust system can discharge the exhaust gas generated by the gas engine.

[0003] Detonation combustion is a combustion technology that realizes combustion through the propagation of detonation waves. A detonation wave is a shock wave that can propagate in a detonation reaction, enabling the reactants and oxygen to react rapidly after contact. The detonation combustion technology can be used to improve combustion efficiency, reduce pollution, and operate at higher pressures and temperatures. The detonation combustion technology is currently used in the fields of automobiles, aviation, and aerospace.

[0004] Regarding the problem that it is difficult to significantly improve the overall power generation efficiency of traditional gas turbines, detonation combustion can greatly improve the overall cycle efficiency of gas turbines while reducing Nox pollutant emissions. However, detonation combustion has problems such as difficult startup and a narrow operating range, and cannot meet the requirements of long-term stable operation. In addition, for a gas turbine that simply uses a detonation combustor to directly replace a conventional combustor, it is difficult to meet the startup requirements in engineering practice. Moreover, changes in external loads and the environment, etc., which lead to changes in the engine operating conditions, are also likely to cause the detonation combustor to be unable to operate stably. Summary of the Invention

[0005] In view of this, the embodiments of the present application provide a gas turbine system with a distributed detonation combustor to achieve the purpose of expanding the power adjustment range of detonation combustion, meeting the requirements of long-term stable operation, and improving the overall cycle efficiency of gas turbines.

[0006] The embodiments of the present application provide the following technical solutions: A gas turbine system with a distributed detonation combustor, comprising:

[0007] A gas turbine main body, the gas turbine main body includes a compressor and a turbine coaxially connected by a main shaft, and further includes a slow combustion chamber. The air inlet of the compressor admits air and is used to compress and pressurize the air. The exhaust port of the compressor is connected to the slow combustion chamber, so that the compressed air enters the slow combustion chamber and mixes with fuel for combustion. The exhaust port of the slow combustion chamber is connected to the turbine, so that the generated flue gas drives the turbine to do work to drive the compressor to operate;

[0008] A detonation power generation system, the detonation power generation system includes multiple groups of detonation combustion chambers arranged in parallel, and a turbine generator set. The turbine generator set includes a detonation turbine and a generator coaxially connected. The air inlet of each group of detonation combustion chambers is communicated with the exhaust port of the compressor, so that the compressed air enters the detonation combustion chamber and mixes with fuel for detonation combustion. The exhaust ports of multiple groups of detonation combustion chambers are respectively communicated with the detonation turbine, so that the detonation flue gas drives the detonation turbine to do work to drive the generator to generate electric energy.

[0009] According to an embodiment of the present application, the compressor includes a low-pressure compressor and a high-pressure compressor. The air inlet of the low-pressure compressor admits air. The exhaust port of the low-pressure compressor is communicated with the air inlets of multiple groups of detonation combustion chambers and the air inlet of the high-pressure compressor, and is used to further compress and pressurize the air in the high-pressure compressor. The exhaust port of the high-pressure compressor is communicated with the slow combustion chamber.

[0010] According to an embodiment of the present application, the detonation power generation system further includes multiple groups of deceleration diffusers corresponding to multiple groups of detonation combustion chambers one by one. Multiple groups of deceleration diffusers are respectively connected between the exhaust port of the corresponding detonation combustion chamber and the air inlet of the detonation turbine to perform deceleration and pressure expansion treatment on the detonation flue gas and then discharge it into the detonation turbine.

[0011] According to an embodiment of the present application, the exhaust port of the high-pressure compressor is further communicated with the air inlets of multiple groups of deceleration diffusers, so that the compressed air and the detonation flue gas generated by the detonation combustion chamber are mixed in the deceleration diffuser, and the mixed gas then enters the detonation turbine.

[0012] According to an embodiment of the present application, it further includes a low-pressure gas main pipe and a high-pressure gas main pipe. The exhaust port of the low-pressure compressor and the air inlets of multiple groups of detonation combustion chambers are communicated through the low-pressure gas main pipe. The exhaust port of the high-pressure compressor and the air inlets of multiple groups of deceleration diffusers are communicated through the high-pressure gas main pipe.

[0013] According to an embodiment of the present application, proportional regulating valves are respectively arranged on the connecting branch pipes between the low-pressure gas main pipe and the air inlets of multiple groups of the detonation combustion chambers; proportional regulating valves are respectively arranged on the connecting branch pipes between the high-pressure gas main pipe and the air inlets of multiple groups of the deceleration diffusers.

[0014] According to an embodiment of the present application, the number of the turbine generator sets is multiple groups, and they are respectively in one-to-one correspondence with multiple groups of the detonation combustion chambers.

[0015] According to an embodiment of the present application, the number of the turbine generator sets is 1 group, and the exhaust ports of multiple detonation combustion chambers are all connected to the detonation turbine through a flue gas main pipe; wherein, the detonation turbine is a detonation turbine with adjustable guide vanes.

[0016] According to an embodiment of the present application, any one of the pressurized combustion methods including continuous rotating detonation and pulse detonation is adopted in the detonation combustion chamber.

[0017] According to an embodiment of the present application, the gas turbine main body further includes a starting motor, and the starting motor is coaxially connected to the compressor and the turbine through the main shaft.

[0018] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of the present specification at least include: In the embodiments of the present invention, multiple detonation combustion power generation devices are distributed and connected in parallel through valves at the outlets of the high- and low-pressure compressed air pipelines, and the turbine is driven by the flue gas to drive the generator to generate electricity. Each independent detonation combustion power generation device can be individually turned on and off, and can also be independently adjusted in power, greatly expanding the working range of detonation combustion and meeting the requirements of long-term stable operation. In addition, under the condition that the entire system is completely standby, all detonation combustion chambers can be completely closed to stop power generation, and the main gas turbine runs at idle speed, reducing fuel consumption. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0020] Figure 1 is a schematic structural diagram of the first embodiment of the present invention;

[0021] Figure 2 is a schematic structural diagram of the second embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] The embodiments of the present application will be described in detail below with reference to the drawings.

[0023] It should be noted that, without conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the drawings and in combination with the embodiments. The technical solutions of the present invention will be clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts belong to the scope of protection of the present invention.

[0024] As Figure 1 - Figure 2 shown, an embodiment of the present invention provides a gas turbine system with a distributed detonation combustor, including:

[0025] A gas turbine main body, the gas turbine main body includes a compressor and a turbine coaxially connected by a main shaft, and also includes a deflagration combustor. The air inlet of the compressor admits air for compressing and pressurizing the air. The exhaust port of the compressor is connected to the deflagration combustor, so that the compressed air enters the deflagration combustor and mixes with fuel for combustion. The exhaust port of the deflagration combustor is connected to the turbine, so that the generated flue gas drives the turbine to do work to drive the compressor to operate.

[0026] A detonation power generation system, the detonation power generation system includes multiple groups of detonation combustors arranged in parallel, and a turbine generator set. The turbine generator set includes a detonation turbine and a generator coaxially connected. The air inlet of each group of detonation combustors is communicated with the exhaust port of the compressor, so that the compressed air enters the detonation combustor and mixes with fuel for detonation combustion. The exhaust ports of multiple groups of detonation combustors are respectively communicated with the detonation turbine, so that the detonation flue gas drives the detonation turbine to do work to drive the generator to generate electric energy.

[0027] The structural setting and working principle of the embodiment of the present invention are as follows: In the mechanical connection part, the compressor and the turbine are connected by a first main shaft and operate at the same rotational speed. The detonation turbine and the generator are connected together by a second main shaft and operate at a second rotational speed. The gas turbine main body mainly serves as a gas source to provide a gas source for the detonation power generation system equipment. Except for supplying gas, the gas turbine main body does not output electric power externally and does not consume electric power. Multiple groups of detonation combustion power generation devices are connected in parallel to the outlet of the compressed air pipeline of the compressor through valves, and the detonation turbine is driven by the flue gas to drive the generator to generate electricity. Each independent detonation combustion power generation device can be independently turned on and off, and can also be independently adjusted in power, greatly expanding the working range of detonation combustion, meeting the requirements of long-term stable operation, and solving the problems of difficult start-up and unstable continuous operation of pure detonation engines. Moreover, under the condition that the entire system is completely on standby, all detonation combustors can be completely shut down to stop power generation, and the gas turbine main body idles to reduce fuel consumption.

[0028] In a specific embodiment, the compressor includes a low-pressure compressor and a high-pressure compressor. The air inlet of the low-pressure compressor admits air, and the exhaust port of the low-pressure compressor is connected to the air inlets of multiple sets of the detonation combustion chambers and the air inlet of the high-pressure compressor, for further compressing and supercharging the air in the high-pressure compressor. The exhaust port of the high-pressure compressor is connected to the deflagration combustion chamber.

[0029] Specifically, the ambient air is supercharged by the low-pressure compressor and then leads to the high-pressure compressor and multiple detonation combustion chambers. The air entering the high-pressure compressor is further compressed in the high-pressure compressor, enters the deflagration combustion chamber to mix with fuel and burn. The total pressure remains basically unchanged while the total temperature rises, generating high-temperature flue gas to drive the turbine to do work, driving the low-pressure compressor and the high-pressure compressor to operate, and then discharging into the atmosphere. The air entering the multiple detonation combustion chambers mixes and detonates with fuel in the detonation combustion chambers. After the total pressure and total temperature both rise further, high-temperature, high-pressure, and high-speed gas is generated to drive the detonation turbine to do work and drive the generator to output power externally.

[0030] In another specific embodiment, the detonation power generation system further includes multiple sets of deceleration diffusers corresponding to the multiple sets of detonation combustion chambers one by one. The multiple sets of deceleration diffusers are respectively connected between the exhaust ports of the corresponding detonation combustion chambers and the air inlets of the detonation turbines, so as to perform deceleration and pressure expansion treatment on the detonation flue gas and then discharge it into the detonation turbines. The deceleration diffuser is used to process the high-temperature, high-pressure, and high-speed gas. The high-temperature, high-pressure, and high-speed gas is further decelerated and pressure-expanded in the deceleration diffuser, the static pressure further rises, the temperature drops, and then it is discharged into the detonation turbine. After entering the detonation turbine to drive the detonation turbine to do work, the exhaust gas is discharged to the atmosphere.

[0031] In order to further reduce the temperature and speed of the high-temperature, high-pressure, and high-speed gas generated in the detonation combustion chamber, in one embodiment, the exhaust port of the high-pressure compressor is also connected to the air inlets of multiple sets of the deceleration diffusers, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber in the deceleration diffuser, and the mixed gas then enters the detonation turbine. The high-temperature, high-pressure, and high-speed detonation flue gas is mixed with the high-pressure air from the high-pressure compressor, and after being processed by the deceleration diffuser, it forms high-temperature flue gas with a temperature, pressure, and speed suitable for the detonation turbine to accept, solving the problem that the detonation gas temperature is too high and the detonation turbine cannot work, improving the life and reliability of the turbine, and reducing costs.

[0032] Further, in this embodiment, a low-pressure gas main pipe and a high-pressure gas main pipe are further included. The exhaust port of the low-pressure compressor is communicated with the intake ports of multiple groups of the detonation combustors through the low-pressure gas main pipe, and the exhaust port of the high-pressure compressor is communicated with the intake ports of multiple groups of the deceleration diffusers through the high-pressure gas main pipe. Moreover, proportional regulating valves are respectively arranged on the connecting branch pipes between the low-pressure gas main pipe and the intake ports of multiple groups of the detonation combustors; proportional regulating valves are respectively arranged on the connecting branch pipes between the high-pressure gas main pipe and the intake ports of multiple groups of the deceleration diffusers. The flow rate of each independent detonation combustor can be controlled by adjusting the proportional regulating valves respectively.

[0033] In one embodiment, as Figure 1 shown, the number of the turbine generator sets is multiple groups, and they respectively correspond to multiple groups of the detonation combustors one by one. Multiple turbine generator sets cooperate with multiple groups of the detonation combustors to form multiple independent power generation devices in the detonation power generation system, which can ensure the continuous and stable operation of the entire networking system for a long time.

[0034] In another embodiment, as Figure 2 shown, the number of the turbine generator sets is 1 group, and the exhaust ports of multiple detonation combustors are all connected to the detonation turbine through a flue gas main pipe; wherein, the detonation turbine is a detonation turbine with adjustable guide vanes. The flue gas from the outlets of all detonation combustors is aggregated into a unified flue gas main pipe, and the outlet of the flue gas main pipe is connected to a turbine with adjustable guide vanes to drive the turbine to do work. Each independent detonation combustor can be individually started and stopped, or the flow rate can be independently adjusted. When multiple detonation combustors start and stop, or the power changes cause changes in the flue gas flow rate and pressure in the flue gas main pipe, the turbine adjusts the angle of the adjustable guide vanes to ensure the working efficiency of the turbine.

[0035] An adjustable turbine guide vane refers to the blades in a turbine system, which can change the angle during operation so that the turbine system can adapt to different working conditions. This technology can improve the efficiency and flexibility of gas turbines and turboprop aircraft. The common structures of adjustable turbine guide vanes are:

[0036] Flip type: This kind of guide vane changes its angle by flipping the whole blade to adjust the supercharging efficiency.

[0037] Movable type: This kind of guide vane can change its angle by moving at the root or top of the blade to adjust the supercharging efficiency.

[0038] Telescopic type: This kind of guide vane can change its length by the telescoping of the blade, thereby adjusting the supercharging efficiency.

[0039] Hybrid type: This kind of guide vane is a combination of the above several structures, and changes its angle and length through multiple methods to adjust the supercharging efficiency.

[0040] In the embodiments of the present invention, the detonation combustion chamber may be a continuous rotating detonation, a pulse detonation, or other forms of pressure-boosting combustion technology.

[0041] In one embodiment, the gas turbine main body further includes a starting motor, and the starting motor is coaxially connected to the compressor and the turbine through the main shaft. This starting motor is only used during the starting process to drive the compressor to operate. After entering the normal working condition, the turbine does work to drive the compressor to operate, and the starting motor is shut down.

[0042] As described above, the above are only specific embodiments of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed in the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A gas turbine system with a distributed detonation combustion chamber, characterized in that, Comprising: A gas turbine main body, the gas turbine main body includes a compressor and a turbine coaxially connected by a main shaft, and also includes a subsonic combustion chamber. The air inlet of the compressor admits air and is used to compress and pressurize the air. The exhaust port of the compressor is connected to the subsonic combustion chamber, so that the compressed air enters the subsonic combustion chamber and mixes with fuel for combustion. The exhaust port of the subsonic combustion chamber is connected to the turbine, so that the generated flue gas drives the turbine to do work to drive the compressor to operate. A detonation power generation system, the detonation power generation system includes multiple groups of detonation combustion chambers arranged in parallel, and a turbine generator set. The turbine generator set includes a detonation turbine and a generator coaxially connected. The air inlet of each group of detonation combustion chambers is communicated with the exhaust port of the compressor, so that the compressed air enters the detonation combustion chamber and mixes with fuel for detonation combustion. The exhaust ports of multiple groups of detonation combustion chambers are respectively communicated with the detonation turbine, so that the detonation flue gas drives the detonation turbine to do work to drive the generator to generate electric energy.

2. The gas turbine system of the distributed detonation combustion chamber according to claim 1, characterized in that, The compressor includes a low-pressure compressor and a high-pressure compressor. The air inlet of the low-pressure compressor admits air. The exhaust port of the low-pressure compressor is communicated with the air inlets of multiple groups of detonation combustion chambers and the air inlet of the high-pressure compressor, and is used to further compress and pressurize the air in the high-pressure compressor. The exhaust port of the high-pressure compressor is communicated with the subsonic combustion chamber.

3. The gas turbine system of the distributed detonation combustor according to claim 2, characterized in that, The detonation power generation system further includes multiple groups of deceleration diffusers corresponding to multiple groups of detonation combustion chambers one by one. Multiple groups of deceleration diffusers are respectively connected between the exhaust port of the corresponding detonation combustion chamber and the air inlet of the detonation turbine to perform deceleration and pressure expansion treatment on the detonation flue gas and then discharge it into the detonation turbine.

4. The gas turbine system of the distributed detonation combustion chamber according to claim 3, characterized in that, The exhaust port of the high-pressure compressor is also communicated with the air inlets of multiple groups of deceleration diffusers, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber in the deceleration diffuser, and the mixture then enters the detonation turbine.

5. The gas turbine system of the distributed detonation combustor according to claim 4, characterized in that, It further includes a low-pressure gas main pipe and a high-pressure gas main pipe. The exhaust port of the low-pressure compressor and the air inlets of multiple groups of detonation combustion chambers are communicated through the low-pressure gas main pipe. The exhaust port of the high-pressure compressor and the air inlets of multiple groups of deceleration diffusers are communicated through the high-pressure gas main pipe.

6. The gas turbine system of the distributed detonation combustor according to claim 5, characterized in that, Proportioning regulating valves are respectively arranged on the connecting branch pipes between the low-pressure gas main pipe and the air inlets of multiple groups of detonation combustion chambers; proportioning regulating valves are respectively arranged on the connecting branch pipes between the high-pressure gas main pipe and the air inlets of multiple groups of deceleration diffusers.

7. The gas turbine system of the distributed detonation combustion chamber according to claim 1, characterized in that, The number of the turbine generator sets is multiple groups, and they respectively correspond to multiple groups of detonation combustion chambers one by one.

8. The gas turbine system of the distributed detonation combustion chamber according to claim 1, characterized in that, The number of the turbine generator sets is 1 group. The exhaust ports of multiple detonation combustion chambers are all connected to the detonation turbine through a flue gas main pipe; wherein, the detonation turbine is a detonation turbine with adjustable guide vanes.

9. The gas turbine system of the distributed detonation combustor according to claim 1, characterized in that, Any one of the pressurized combustion methods including continuous rotating detonation and pulse detonation is adopted in the detonation combustion chamber.

10. The gas turbine system of the distributed detonation combustion chamber according to claim 1, characterized in that, The gas turbine main body further includes a starting motor, and the starting motor is coaxially connected with the compressor and the turbine through the main shaft.

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