A detonation gas turbine with a steam cycle system

Abstract

The present invention provides a detonation gas turbine with a steam circulation system, comprising: a detonation combustion chamber, which is provided with a main channel cavity and a cooling channel, wherein the main channel cavity is used for detonation combustion, and the cooling channel is used to cool the detonation combustion chamber; a slow combustion combustion chamber and a first turbine, wherein the flue gas outlets of the slow combustion combustion chamber and the detonation combustion chamber are both connected to the first turbine; a heating and pressurizing device, wherein the first inlet is connected to the cooling channel outlet of the detonation combustion chamber, and the second inlet is connected to the flue gas outlet of the first turbine, and the cooling water is heated and pressurized again by the waste heat of the flue gas to form supercritical water; the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water drives the second turbine to perform work; the water outlet of the second turbine is connected to the cooling channel inlet of the detonation combustion chamber, so that the cooling water flows back to the cooling channel, forming a cooling water circulation system. The present invention can significantly reduce system power loss and improve the overall cycle efficiency of the combustion engine.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a detonation gas turbine with a steam cycle system. 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] Detonation combustion can significantly improve the overall cycle efficiency of gas turbines while reducing NOx emissions. However, due to the extremely high heat density of the detonation combustion chamber, a large amount of cooling is required, which results in a significant loss of energy and power and efficiency. Summary of the Invention

[0005] In view of this, an embodiment of the present application provides a detonation gas turbine with a steam cycle system to achieve the purpose of reducing system power loss and improving the overall cycle efficiency of the gas turbine.

[0006] The embodiment of the present application provides the following technical solution: a detonation gas turbine with a steam cycle system, comprising:

[0007] A detonation combustion chamber, wherein a main channel cavity and a cooling channel are provided in the detonation combustion chamber. The main channel cavity is used for detonation combustion, and cooling water is introduced into the cooling channel for cooling the detonation combustion chamber;

[0008] A slow-burn combustion chamber and a first turbine, wherein the flue gas outlets of the slow-burn combustion chamber and the detonation combustion chamber are both connected to the first turbine, so that the flue gas generated by combustion drives the first turbine to perform work;

[0009] a heating and pressurizing device, wherein a first inlet of the heating and pressurizing device is connected to the outlet of the cooling channel of the detonation combustion chamber, so that the cooling water after heat exchange enters the heating and pressurizing device; a second inlet of the heating and pressurizing device is connected to the flue gas outlet of the first turbine, so that the flue gas after driving the first turbine to do work enters the heating and pressurizing device, and the residual heat of the flue gas is used to heat and pressurize the cooling water again, so that the cooling water reaches a supercritical state, forming supercritical water;

[0010] The second turbine, the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water drives the second turbine to do work; the water outlet of the second turbine is connected to the inlet of the cooling channel of the detonation combustion chamber, so that the cooling water after driving the second turbine to do work flows back to the cooling channel, forming a cooling water circulation system.

[0011] According to one embodiment of the present application, the detonation combustion chamber includes a detonation combustion chamber shell, the inner cavity of the detonation combustion chamber shell is coaxially sleeved with a detonation outer ring and a detonation inner ring from the outside to the inside, the detonation outer ring and the detonation inner ring are both tubular structures, and the main flow channel chamber for detonation combustion is formed between the annular walls of the detonation outer ring and the detonation inner ring, and the air inlet of the main flow channel chamber is connected to the air for mixing the air with the fuel in the main flow channel chamber for detonation combustion;

[0012] A first annular cavity is formed between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and cooling water is passed into the first annular cavity as an external cooling channel; an internal cooling channel is provided in the inner cavity of the detonation inner ring, and cooling water is passed into the inner cooling channel.

[0013] According to one embodiment of the present application, the detonation combustion chamber shell also includes a cooling inner ring, which is a columnar structure and is coaxially sleeved in the inner cavity of the detonation inner ring, so that a second ring cavity is formed between the cooling inner ring and the detonation inner ring, and the second ring cavity constitutes the inner cooling channel.

[0014] According to one embodiment of the present application, a condenser is further included, which is arranged between the water outlet pipe of the second turbine and the cooling channel inlet of the detonation combustion chamber, and is used to condense the cooling water at the water outlet pipe of the second turbine and then pass it into the cooling channel.

[0015] According to one embodiment of the present application, a circulation pump is further included, and the circulation pump is arranged on the pipeline between the outlet of the condenser and the inlet of the cooling channel of the detonation combustion chamber.

[0016] According to one embodiment of the present application, the heating and pressurizing device includes a plurality of water pipes, and a reserved gap is provided between two adjacent water pipes, and the reserved gap forms a smoke cavity.

[0017] According to one embodiment of the present application, the heating and pressurizing device further includes a housing, the housing including a water storage chamber provided on a water inlet side and a steam chamber provided on a water outlet side, the water pipe being provided between the water storage chamber and the steam chamber, the water inlet end of the water pipe being connected to the water storage chamber, and the water outlet end of the water pipe being connected to the steam chamber.

[0018] The water storage chamber is connected to the cooling channel outlet of the detonation combustion chamber through the first inlet, the steam chamber is connected to the second turbine through the first outlet, and the flue gas inlet of the flue gas chamber is connected to the flue gas outlet of the first turbine through the second inlet.

[0019] According to one embodiment of the present application, the smoke outlet of the smoke cavity is connected to the atmosphere.

[0020] According to one embodiment of the present application, control valves are respectively provided on the first inlet and the first outlet.

[0021] According to one embodiment of the present application, it also includes a compressor, which is coaxially connected to the first turbine, the air inlet of the compressor is connected to the air, and the exhaust port of the compressor is connected to the air inlet of the main flow channel chamber in the detonation combustion chamber and the air inlet of the slow combustion combustion chamber.

[0022] The detonation gas turbine of the embodiment of the present invention uses cooling water to fully cool the detonation combustion chamber, and uses the waste heat of the flue gas after driving the first turbine of the gas turbine to work to reheat the cooling water after heat exchange, so that it reaches a supercritical state, and uses the generated supercritical water to drive the second turbine to work, and drives the cooling water after the second work to condense and then flow back to the cooling channel of the detonation combustion chamber for heat exchange again, completing the cycle of the entire system.

[0023] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: on the basis of ensuring the cooling effect of the detonation combustion chamber, the embodiments of the present invention further heat and pressurize the cooling water after heat exchange to form supercritical water, thereby driving the turbine to do work, and finally returning it to the detonation combustion chamber after condensation, recovering the energy lost in cooling, thereby greatly reducing the power loss of the system, improving the power utilization rate, and thereby improving the overall cycle efficiency of the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] 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.

[0025] Figure 1 is a structural block diagram of a detonation gas turbine according to an embodiment of the present invention;

[0026] Figure 2 1 is a schematic structural diagram of a detonation combustion chamber according to an embodiment of the present invention;

[0027] Figure 3 1 is a schematic structural diagram of a heating and pressurizing device according to an embodiment of the present invention;

[0028] In the figure, 1-detonation outer ring, 2-detonation inner ring, 3-main channel chamber, 4-external cooling channel, 5-inner cooling channel, 6-cooling inner ring, 7-water pipe, 8-smoke cavity, 9-water storage cavity, 10-steam cavity. DETAILED DESCRIPTION

[0029] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0030] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0031] like Figure 1As shown, an embodiment of the present invention provides a detonation gas turbine with a steam cycle system, comprising: a detonation combustion chamber, wherein a main channel chamber and a cooling channel are provided in the detonation combustion chamber, wherein the main channel chamber is used for detonation combustion, and cooling water is introduced into the cooling channel for cooling the detonation combustion chamber; a slow combustion combustion chamber and a first turbine, wherein the flue gas outlets of the slow combustion combustion chamber and the detonation combustion chamber are both connected to the first turbine, so that the flue gas generated by the combustion drives the first turbine to do work; a heating and pressurizing device, wherein a first inlet of the heating and pressurizing device is connected to the cooling channel outlet of the detonation combustion chamber, so that the cooling water after heat exchange enters The heating and pressurizing device; the second inlet of the heating and pressurizing device is connected to the flue gas outlet of the first turbine, so that the flue gas after driving the first turbine to do work enters the heating and pressurizing device, and the cooling water is heated and pressurized again by the waste heat of the flue gas, so that the cooling water reaches a supercritical state and forms supercritical water; the second turbine, the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water drives the second turbine to do work; the water outlet pipe of the second turbine is connected to the cooling channel inlet of the detonation combustion chamber, so that the cooling water after driving the second turbine to do work flows back to the cooling channel to form a cooling water circulation system.

[0032] In this embodiment, the gas turbine includes a compressor. Its air inlet receives air, and its outlet connects to the inlets of a conventional slow-burn combustion chamber and a detonation combustion chamber, compressing the air and then passing it into the slow-burn and detonation combustion chambers, respectively. Within the slow-burn combustion chamber, air and fuel mix and combust, producing high-temperature flue gas. Within the detonation combustion chamber, air and fuel undergo detonation combustion. The high-temperature flue gas generated by both the slow-burn and detonation combustions acts on a first turbine, which drives a generator to output electrical energy, serving as the primary energy source for the gas turbine. Because the detonation combustion chamber operates at relatively high pressures and temperatures, a cooling system is required to maintain the gas engine's temperature within a suitable range. Therefore, in this embodiment of the present invention, a cooling channel is provided within the detonation combustion chamber to cool the detonation combustion chamber. However, excessive cooling dissipates significant energy, resulting in a loss of power and efficiency.

[0033] In order to reduce energy loss, this embodiment is provided with a heating and pressurizing device to introduce the flue gas after the first turbine does work and the cooling water in the cooling channel. After the cooling water exchanges heat in the detonation combustion chamber, the temperature of the cooling water does not reach the critical water temperature. The temperature of the flue gas discharged from the first turbine is 370°C~540°C. Therefore, the flue gas discharged from the first turbine of the gas turbine is used to heat the cooling water again, and the thermal energy of the flue gas is fully utilized to form supercritical water in the cooling water. The supercritical water, that is, water vapor, is used to drive the second turbine of the gas turbine to do work, so that the second turbine drives the generator to output power again. This not only reduces power loss, but also improves the cycle efficiency of the entire gas turbine and reduces pollutant emissions.

[0034] Supercritical water is water that is liquid under standard conditions but forms vapor when heated. When the temperature and pressure are raised from standard conditions to the critical point of water, its properties become intermediate between liquid and gas. It fills the entire space like a gas, but its density is similar to that of a liquid, creating a supercritical fluid.

[0035] In one embodiment of this embodiment, the gas turbine system further includes a condenser, which is disposed between the water outlet of the second turbine and the inlet of the cooling channel of the detonation combustion chamber, and is used to condense the cooling water at the water outlet of the second turbine before it is passed into the cooling channel. After the supercritical water propels the second turbine to perform work, the water at the outlet of the second turbine returns to normal, is cooled by the condenser, condenses into cooling water, and then flows into the cooling channel of the detonation combustion chamber to perform cooling work again.

[0036] Furthermore, the present invention further includes a circulation pump, which is arranged on the pipeline between the outlet of the condenser and the inlet of the cooling channel of the detonation combustion chamber. Cooling water enters the detonation combustion chamber through the circulation pump for cooling, thus completing the system circulation.

[0037] like Figure 2 As shown, in another embodiment of the present invention, the detonation combustion chamber includes a detonation combustion chamber shell, the inner cavity of the detonation combustion chamber shell is coaxially sleeved with a detonation outer ring and a detonation inner ring from the outside to the inside, the detonation outer ring and the detonation inner ring are both tubular structures, and the main flow channel chamber for detonation combustion is formed between the annular walls of the detonation outer ring and the detonation inner ring, and the air inlet of the main flow channel chamber is connected to air for mixing the air with the fuel in the main flow channel chamber for detonation combustion; a first annular cavity is formed between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and cooling water is introduced into the first annular cavity as an external cooling channel; an internal cooling channel is provided in the inner cavity of the detonation inner ring, and cooling water is introduced into the internal cooling channel.

[0038] In this embodiment, a structural setting of a detonation combustion chamber shell, a detonation outer ring 1 and a detonation inner ring 2 being coaxially sleeved is adopted, and the annular chamber formed between the detonation outer ring 1 and the detonation inner ring 2 is used as the main channel chamber 3 for detonation combustion. At the same time, a first annular cavity is set on the outer ring of the detonation outer ring 1 as an outer cooling channel 4, and an inner cooling channel 5 is set on the inner ring of the detonation inner ring 2. Circulating cooling water is set on both the inner and outer layers of the main channel chamber 3, which can quickly cool down the detonation combustion chamber, greatly improving the cooling effect, ensuring the long-term stable operation of the detonation combustion chamber, and greatly reducing the thermal deformation caused by the increase in the combustion chamber temperature, thereby ensuring the coaxiality and accuracy of the combustion chamber annular cavity structure.

[0039] Furthermore, in this solution, a cooling inner ring 6 is provided in the detonation combustion chamber shell. The cooling inner ring 6 is a columnar structure and is coaxially sleeved in the inner cavity of the detonation inner ring 2, so that a second annular cavity is formed between the cooling inner ring 6 and the detonation inner ring 2, and the second annular cavity constitutes the inner cooling channel 5.

[0040] like Figure 3 As shown, in another embodiment of the present invention, the heating and pressurizing device includes multiple water pipes 7, with a reserved gap between two adjacent water pipes 7, forming a flue gas cavity 8. Flue gas discharged from the first turbine is introduced into the flue gas cavity 8. The flue gas surrounds the outer walls of the multiple water pipes 7 and fully exchanges heat with the cooling water in the water pipes 7, further heating and pressurizing the cooling water to a critical water state.

[0041] When this solution is implemented, the heating and pressurizing device also includes a shell, which includes a water storage chamber 9 respectively arranged on the water inlet side and a steam chamber 10 respectively arranged on the water outlet side. The water pipe 7 is arranged in the water storage chamber 9 and the steam chamber 10, and the water inlet end of the water pipe 7 is respectively connected to the water storage chamber 9, and the water outlet end of the water pipe 7 is respectively connected to the steam chamber 10; the water storage chamber 9 is connected to the cooling channel outlet of the detonation combustion chamber through the first inlet, and the steam chamber 10 is connected to the second turbine through the first outlet, and the flue gas inlet of the flue gas chamber 8 is connected to the flue gas outlet of the first turbine through the second inlet.

[0042] In this solution, a water storage chamber 9 and a steam chamber 10 are provided on either side of the housing. The introduced cooling water first enters the water storage chamber 9, ensuring that the cooling water is evenly distributed throughout each water pipe 7. The structural arrangement also ensures that the flue gas can uniformly and fully exchange heat with the cooling water. The heated water vapor is concentrated through the steam chamber 10 and then discharged. After heat exchange, the flue gas temperature has been reduced, so the flue gas outlet of the flue gas chamber 8 can be vented to the atmosphere.

[0043] In this embodiment, control valves are further provided at the first inlet and the first outlet. To ensure sufficient heat exchange between the cooling water and the flue gas in the heating and pressurizing device, the control valves at the first inlet and the first outlet can be closed for a predetermined period of time, allowing sufficient contact and heat exchange between the cooling water and the flue gas over a period of time, thereby causing the cooling water to reach a critical water state.

[0044] In other embodiments of the present invention, the gas turbine may be provided with multiple detonation combustion chambers, each uniformly distributed circumferentially within the gas turbine casing. Existing detonation combustion chamber structures, to achieve detonation combustion, are designed so that the height of the combustion chamber passage can only be adjusted within a narrow range. Therefore, when used in engines with slightly higher power, a single narrow passage and a large-diameter circular ring structure are required. This is very difficult to manufacture and manufacture, and precision is difficult to ensure. Furthermore, thermal deformation caused by the increased combustion chamber temperature during operation can further significantly deteriorate the coaxiality and precision of this large-diameter circular ring throughout the passage. Furthermore, because the detonation combustion chamber has a narrow operating range, for example, at a set power of 100, the detonation combustion chamber can only achieve detonation combustion within a range of 90-100, while gas turbines are required to operate stably within a wider range of 0-100. Therefore, compared to conventional detonation combustion engines with a single large-diameter combustion chamber, a multiple-combustion chamber structure facilitates cooling while enabling the control of the opening and closing of any detonation combustion chamber, enabling a wider range of gas turbine power adjustment. This effectively improves combustion efficiency, reduces manufacturing difficulty, and ensures structural design precision.

[0045] The gas turbine system of the embodiment of the present invention can rapidly cool the detonation combustion chamber through external and internal cooling channels provided therein, significantly improving the cooling effect and ensuring long-term stable operation of the detonation combustion chamber. It also significantly reduces thermal deformation caused by elevated combustion chamber temperatures, ensuring the coaxiality and precision of the combustion chamber's annular structure. Furthermore, while maintaining the cooling effect of the detonation combustion chamber, the cooling water after heat exchange is further heated and pressurized to form supercritical water, which then drives the turbine to produce work. Finally, after condensation, it flows back to the detonation combustion chamber, recovering cooling energy. This significantly reduces system power loss, improves power utilization, and thus enhances the overall cycle efficiency of the combustion turbine.

[0046] 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 detonation gas turbine with a steam cycle system, characterized in that: include: A detonation combustion chamber, wherein a main channel cavity and a cooling channel are provided in the detonation combustion chamber. The main channel cavity is used for detonation combustion, and cooling water is introduced into the cooling channel for cooling the detonation combustion chamber; A slow-burn combustion chamber and a first turbine, wherein the flue gas outlets of the slow-burn combustion chamber and the detonation combustion chamber are both connected to the first turbine, so that the flue gas generated by combustion drives the first turbine to perform work; a heating and pressurizing device, wherein a first inlet of the heating and pressurizing device is connected to the outlet of the cooling channel of the detonation combustion chamber, so that the cooling water after heat exchange enters the heating and pressurizing device; a second inlet of the heating and pressurizing device is connected to the flue gas outlet of the first turbine, so that the flue gas after driving the first turbine to do work enters the heating and pressurizing device, and the residual heat of the flue gas is used to heat and pressurize the cooling water again, so that the cooling water reaches a supercritical state, forming supercritical water; The second turbine, the first outlet of the heating and pressurizing device is connected to the second turbine, so that the supercritical water drives the second turbine to do work; the water outlet of the second turbine is connected to the inlet of the cooling channel of the detonation combustion chamber, so that the cooling water after driving the second turbine to do work flows back to the cooling channel, forming a cooling water circulation system.

2. The detonation gas turbine according to claim 1, characterized in that The detonation combustion chamber includes a detonation combustion chamber shell, wherein an inner cavity of the detonation combustion chamber shell is coaxially sleeved with a detonation outer ring and a detonation inner ring in sequence from the outside to the inside, wherein the detonation outer ring and the detonation inner ring are both tubular structures, and the main flow channel chamber for detonation combustion is formed between the annular walls of the detonation outer ring and the detonation inner ring, and an air inlet of the main flow channel chamber is connected to air for mixing the air with the fuel in the main flow channel chamber for detonation combustion; A first annular cavity is formed between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and cooling water is passed into the first annular cavity as an external cooling channel; an internal cooling channel is provided in the inner cavity of the detonation inner ring, and cooling water is passed into the inner cooling channel.

3. The detonation gas turbine according to claim 2, characterized in that: The detonation combustion chamber shell also includes a cooling inner ring, which is a columnar structure and is coaxially sleeved in the inner cavity of the detonation inner ring, so that a second ring cavity is formed between the cooling inner ring and the detonation inner ring, and the second ring cavity constitutes the inner cooling channel.

4. The detonation gas turbine according to claim 1, characterized in that It also includes a condenser, which is arranged between the water outlet of the second turbine and the cooling channel inlet of the detonation combustion chamber, and is used to condense the cooling water at the water outlet of the second turbine and then pass it into the cooling channel.

5. The detonation gas turbine according to claim 4, characterized in that: It also includes a circulation pump, which is arranged on a pipeline between the outlet of the condenser and the inlet of the cooling channel of the detonation combustion chamber.

6. The detonation gas turbine according to claim 1, characterized in that The heating and pressurizing device comprises a plurality of water pipes, and a reserved gap is provided between two adjacent water pipes, and the reserved gap forms a smoke cavity.

7. The detonation gas turbine according to claim 6, characterized in that The heating and pressurizing device further comprises a housing, wherein the housing comprises a water storage chamber provided on a water inlet side and a steam chamber provided on a water outlet side, the water pipe being provided between the water storage chamber and the steam chamber, the water inlet end of the water pipe being connected to the water storage chamber, and the water outlet end of the water pipe being connected to the steam chamber. The water storage chamber is connected to the cooling channel outlet of the detonation combustion chamber through the first inlet, the steam chamber is connected to the second turbine through the first outlet, and the flue gas inlet of the flue gas chamber is connected to the flue gas outlet of the first turbine through the second inlet.

8. The detonation gas turbine according to claim 7, characterized in that The smoke outlet of the smoke cavity is connected to the atmosphere.

9. The detonation gas turbine according to claim 7, characterized in that: Control valves are respectively provided on the first inlet and the first outlet.

10. The detonation gas turbine according to claim 1, characterized in that It also includes a compressor, which is coaxially connected to the first turbine, the air inlet of the compressor is connected to air, and the exhaust port of the compressor is connected to the air inlet of the main channel chamber in the detonation combustion chamber and the air inlet of the slow combustion combustion chamber.

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