A gas turbine with a secondary combustion detonation combustion chamber

Abstract

The present invention provides a gas turbine with a supplemental combustion detonation combustion chamber, comprising: a gas turbine main body comprising a starter generator, a low-pressure compressor, a high-pressure turbine, and a low-pressure turbine coaxially connected in sequence via a main shaft; a slow-burn combustion chamber, the air inlet of which is connected to the exhaust of the low-pressure compressor, which in turn is connected to the air inlet of the high-pressure turbine; a detonation combustion chamber, the air inlet of which is connected to the exhaust of the high-pressure turbine, which in turn is connected to the air inlet of the low-pressure turbine; the air inlet of the low-pressure compressor is connected to the atmosphere, and the compressed atmosphere enters the slow-burn combustion chamber and mixes with fuel to burn, generating flue gas that enters the high-pressure turbine and drives the high-pressure turbine to produce work; the flue gas discharged from the high-pressure turbine enters the detonation combustion chamber, mixes with fuel to undergo detonation combustion, and generates detonation flue gas that enters the low-pressure turbine and drives the low-pressure turbine to produce work; the work of the high-pressure and low-pressure turbines drives the starter generator to generate electricity. The present invention can effectively improve the overall cycle efficiency of the gas turbine and reduce pollutant emissions.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine with a supplementary combustion detonation combustion chamber. 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] For traditional gas turbines, especially when they are used in combined cycle systems, the flue gas of the gas turbine needs to be directed to the waste heat boiler. However, when the gas turbine operates under variable operating conditions, the exhaust temperature changes with the operating conditions. Therefore, it is impossible to ensure that the temperature and flow of the flue gas entering the waste heat boiler are always at the optimal efficiency point of the waste heat boiler and the downstream steam turbine.

[0005] When gas turbines are used in combined cooling, heating and power generation, there is also the problem that the calorific value of the flue gas often cannot well match the cooling and heating requirements when meeting the power demand. Summary of the Invention

[0006] In view of this, an embodiment of the present application provides a gas turbine with a supplemental combustion detonation combustion chamber, so that in the gas turbine-steam combined cycle, by adjusting the supplemental combustion detonation combustion chamber in the high- and low-pressure turbines, the outlet temperature of the gas turbine can be adjusted in a larger range, and in the gas turbine-steam combined cycle system, the downstream waste heat boiler can be ensured to operate in a more efficient working range; in the gas turbine trigeneration, by adjusting the power of the supplemental combustion detonation combustion chamber, the flue gas heat can be adjusted in a larger range, and the needs of electricity, heat and cooling can be met at the same time.

[0007] The embodiment of the present application provides the following technical solution: a gas turbine with a secondary combustion detonation combustion chamber, comprising:

[0008] A gas turbine main body, the gas turbine main body comprising a generator, a low-pressure compressor, a high-pressure turbine, and a low-pressure turbine coaxially connected in sequence via a main shaft;

[0009] a slow-burn combustion chamber, wherein the air inlet of the slow-burn combustion chamber is connected to the exhaust port of the low-pressure compressor, and the exhaust port of the slow-burn combustion chamber is connected to the air inlet of the high-pressure turbine;

[0010] a detonation combustion chamber, wherein the air inlet of the detonation combustion chamber is connected to the exhaust port of the high-pressure turbine, and the exhaust port of the detonation combustion chamber is connected to the air inlet of the low-pressure turbine;

[0011] The air inlet of the low-pressure compressor is connected to the atmosphere and is used to compress and boost the atmosphere. The compressed atmosphere enters the slow-burn combustion chamber, mixes with the fuel and burns, and the resulting flue gas enters the high-pressure turbine to drive the high-pressure turbine to perform work. The flue gas discharged from the high-pressure turbine enters the detonation combustion chamber, mixes with the fuel and detonates and burns in the detonation combustion chamber, and the resulting detonation flue gas enters the low-pressure turbine to drive the low-pressure turbine to perform work.

[0012] The high-pressure turbine and the low-pressure turbine perform work, driving the generator to generate electrical energy.

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

[0014] According to one embodiment of the present application, the detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, the 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, so that the atmosphere compressed by the low-pressure compressor cools the wall of the detonation combustion chamber in the cooling channel, and then mixes with the high-speed and high-pressure flue gas generated by the detonation in the exhaust section of the detonation combustion chamber and is discharged to the low-pressure turbine.

[0015] According to one embodiment of the present application, the detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, the air inlet of the cooling channel is connected to the fuel input pipeline, and the exhaust port of the cooling channel is respectively connected to the slow combustion chamber and the detonation combustion chamber, so that the fuel enters the cooling channel to cool the wall of the detonation combustion chamber, and then enters the slow combustion chamber and the detonation combustion chamber respectively.

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

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

[0018] According to one embodiment of the present application, regulating control valves are respectively provided on the fuel input pipelines connected to the slow combustion chamber and the detonation combustion chamber.

[0019] According to one embodiment of the present application, when the gas turbine is in the starting process, the starter-generator is in the motor working mode; when the gas turbine is in low operating conditions and normal working conditions, the starter-generator is in the generator working mode.

[0020] According to one embodiment of the present application, the detonation combustion chamber does not work when the power generation power and flue gas emission heat of the slow combustion chamber meet the requirements. When the power generation power meets the requirements but the flue gas emission heat does not meet the system requirements, the detonation combustion chamber works.

[0021] The embodiment of the present invention adopts a structure in which a traditional slow-burn combustion chamber burns in the front and a detonation combustion chamber performs supplementary combustion in the back. The flue gas generated by the combustion in the traditional slow-burn combustion chamber drives the high-pressure turbine rotor to rotate, and the flue gas generated by the detonation combustion in the detonation combustion chamber drives the low-pressure turbine rotor to rotate. The high-pressure turbine and the low-pressure turbine work together to improve the power generation efficiency of the entire gas turbine. Among them, the traditional slow-burn combustion chamber is mainly used for the stable operation of the gas turbine, providing stable inlet air conditions for the detonation combustion chamber, and at the same time, realizing partial power generation according to the working conditions. The supplementary detonation combustion chamber is mainly used for high-efficiency, low-pollution power generation, improving the power generation efficiency of the entire gas turbine, and reducing overall pollutant emissions.

[0022] Compared with the prior art, the beneficial effects achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: Compared with traditional slow-burn gas turbines, the use of a detonation combustion chamber for supplementary combustion effectively improves the overall cycle efficiency of the gas turbine and reduces overall pollutant emissions; at the same time, the use of excess oxygen after slow-burn combustion as the inlet oxygen for the detonation combustion chamber provides stable inlet air conditions for the detonation combustion chamber, solving the problems of pure detonation combustion engines such as difficulty in starting and unstable continuous operation. On this basis, the matching of the flue gas outlet temperature and flow rate with the waste heat boiler under the conditions of the gas turbine-steam combined cycle is met to a wider range, and the matching of electricity, heat, and cooling under the conditions of the gas turbine trigeneration is met to a wider range, while also improving the energy utilization rate of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] 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.

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

[0025] Figure 2 Schematic diagram of the structure of a gas turbine according to an embodiment of the present invention. DETAILED DESCRIPTION

[0026] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0027] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of this application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments, and the technical solutions of the present invention will be clearly and completely described. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0028] like Figure 1 As shown, Figure 1 This is a schematic diagram of a traditional gas turbine structure. Its mechanical connection structure is as follows: the starter-generator, low-pressure compressor, high-pressure compressor, and turbine are connected by 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. During power generation, the turbine drives the low-pressure compressor, high-pressure compressor, and motor, which outputs power. The low-pressure compressor draws in air, which is then pressurized and enters the high-pressure compressor. The high-pressure compressor then further pressurizes the air before entering the combustion chamber, where it mixes with fuel and burns. The resulting high-temperature flue gas drives the turbine to produce work, driving the low-pressure compressor, high-pressure compressor, and motor.

[0029] 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 where the traditional slow-burn combustion chamber is used for front combustion and the detonation combustion chamber is used for back combustion to solve these problems. It also solves the problems of pure detonation combustion engines, such as difficulty in starting and unstable continuous operation.

[0030] like Figure 2 As shown, an embodiment of the present invention provides a gas turbine with a secondary combustion detonation combustion chamber, comprising:

[0031] A gas turbine main body, the gas turbine main body comprising a generator, a low-pressure compressor, a high-pressure turbine, and a low-pressure turbine coaxially connected in sequence via a main shaft;

[0032] A slow combustion chamber, the air inlet of the slow combustion chamber being connected to the exhaust port of the low-pressure compressor, and the exhaust port of the slow combustion chamber being connected to the air inlet of the high-pressure turbine; a detonation combustion chamber, the air inlet of the detonation combustion chamber being connected to the exhaust port of the high-pressure turbine, and the exhaust port of the detonation combustion chamber being connected to the air inlet of the low-pressure turbine;

[0033] The air inlet of the low-pressure compressor is connected to the atmosphere, and is used to compress and boost the atmosphere. The compressed atmosphere enters the slow-burn combustion chamber, mixes with the fuel and burns, and the generated flue gas enters the high-pressure turbine, driving the high-pressure turbine to do work; the flue gas discharged from the high-pressure turbine enters the detonation combustion chamber, mixes with the fuel and detonates and burns in the detonation combustion chamber, and the generated detonation flue gas enters the low-pressure turbine, driving the low-pressure turbine to do work; the high-pressure turbine and the low-pressure turbine do work, driving the generator to generate electrical energy.

[0034] In this embodiment of the present invention, a dual-stage turbine structure with a high-pressure turbine and a low-pressure turbine is employed. This dual-stage turbine achieves higher efficiency. After the flue gas expands and generates work in the first-stage high-pressure turbine, it enters the second-stage low-pressure turbine to generate work again. The high- and low-pressure turbines mentioned above refer to the turbine inlet pressures. The high-pressure turbine is in the front, and the combustion flue gas expands and reduces its pressure before entering the second-stage turbine. Therefore, the second-stage turbine is called the low-pressure turbine.

[0035] Among them, the detonation combustion chamber does not work when the power generation power and flue gas emission heat of the slow combustion chamber meet the requirements. When the power meets the requirements but the flue gas emission heat does not meet the system requirements, the detonation combustion chamber starts to work and performs supplementary combustion.

[0036] The structural arrangement and operating principle of the embodiment of the present invention are as follows: In the mechanical connection portion, the starter generator, low-pressure compressor, high-pressure turbine, and low-pressure turbine are connected via a main shaft and operate at the same speed. During the gas turbine startup process, the starter generator operates in motor mode, driving the low-pressure turbine and high-pressure turbine via the main shaft. Under low operating conditions, the starter generator operates in generator mode, with the high-pressure turbine and low-pressure turbine driving the low-pressure compressor and the starter generator, and the starter generator outputs power. During the gas turbine startup process and under low operating conditions, the post-combustion detonation combustor does not operate. Under normal operating conditions, the starter generator operates in generator mode, with the high-pressure turbine and low-pressure turbine driving the low-pressure compressor and the starter generator, and the starter generator outputs power. Simultaneously, under normal operating conditions, the post-combustion detonation combustor operates, further increasing the temperature and pressure of the gas entering the low-pressure turbine, driving the low-pressure turbine to produce work.

[0037] Among them, the atmospheric air is pressurized by the low-pressure compressor and enters the slow-burn combustion chamber. After mixing with the fuel and burning, the generated flue gas enters the high-pressure turbine to perform work.

[0038] The outlet temperature of a traditional slow-burn combustor is mainly limited by the temperature resistance of the combustor material and the downstream turbine. Therefore, the temperature of the outlet combustion flue gas generally operates between 1000-1700K. When the combustion equivalence ratio is equal to 1, the temperature of the flue gas generated by the complete reaction of the fuel and oxygen in the air is greater than 2200K. Therefore, the combustion equivalence ratio in a traditional slow-burn combustor is less than 1. As a result, the flue gas entering the high-pressure turbine contains a large amount of oxygen. After the burned flue gas performs work in the high-pressure turbine, the temperature and pressure drop. It enters the detonation combustion chamber used for supplementary combustion, where it mixes with the fuel again and undergoes detonation combustion, causing the temperature and pressure of the flue gas to rise again. After entering the low-pressure turbine, it drives the low-pressure turbine to perform work and is then discharged into the atmosphere. The use of a detonation combustion chamber for supplementary combustion effectively improves the overall cycle efficiency of the gas turbine, reduces overall pollutant emissions, and provides stable inlet air conditions for the detonation combustion chamber, solving the problems of pure detonation combustion engines, such as difficulty in starting and unstable continuous operation. On this basis, the flue gas outlet temperature and flow rate can be matched with the waste heat boiler under the conditions of gas turbine-steam combined cycle in a larger range, and the electricity-heat-cold matching can be met under the conditions of gas turbine trigeneration of heat, cooling and power in a larger range, while improving the energy utilization rate of the system.

[0039] Since the detonation combustion chamber is a high pressure and temperature working environment, a cooling system is required to keep the temperature of the gas engine within an appropriate range. Therefore, in an embodiment of the present invention, a detonation combustion cooling system is provided outside the detonation combustion chamber to cool the wall surface of the detonation combustion chamber.

[0040] In one specific embodiment, the detonation combustion chamber is cooled using exhaust air from a low-pressure compressor. The detonation combustion cooling system comprises 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 atmospheric air compressed by the low-pressure compressor to cool the walls of the detonation combustion chamber within the cooling channel. The air is then mixed with the high-speed, high-pressure flue gas generated by the detonation in the exhaust section of the detonation combustion chamber and discharged into the low-pressure turbine to perform work.

[0041] Because the detonation combustion chamber is located at the high-pressure turbine outlet, the inlet pressure of the detonation combustion chamber is lower than the high-pressure turbine inlet and the low-pressure compressor outlet pressure. Although the outlet pressure of the detonation combustion chamber increases after detonation combustion, it is still lower than the outlet pressure of the low-pressure compressor. Therefore, after cooling the detonation combustion chamber, the air at the outlet of the low-pressure compressor can also mix with the exhaust gas at the outlet of the detonation combustion chamber, reducing the temperature of the exhaust gas at the outlet of the detonation combustion chamber and forming a high-temperature exhaust gas that is suitable for the low-pressure turbine to protect it.

[0042] In another specific embodiment, the detonation combustion chamber is cooled using fuel cooling. The specific structure is as follows: the detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber. The air inlet of the cooling channel is connected to the fuel input pipeline, and the exhaust port of the cooling channel is connected to the slow combustion chamber and the detonation combustion chamber, respectively. Fuel enters the cooling channel to cool the wall of the detonation combustion chamber and then enters the slow combustion chamber and the detonation combustion chamber, respectively. Furthermore, regulating control valves are respectively installed on the fuel input pipelines connected to the slow combustion chamber and the detonation combustion chamber to facilitate operation and control.

[0043] In another specific embodiment, an external liquid cooling cycle can be used to cool the detonation combustion chamber. Specifically, the detonation combustion cooling system includes a cooling channel disposed around the outer wall of the detonation combustion chamber, into which circulating coolant flows, specifically by a circulating pump.

[0044] In other embodiments, a structure combining the above-mentioned cooling methods such as air cooling discharged from the low-pressure compressor, fuel cooling, and external liquid cooling circulation can be used, which can be independently controlled by control valves in the pipeline and can be selected according to the high-temperature resistance performance of the detonation combustion chamber.

[0045] In an embodiment of the present invention, the detonation combustion chamber may be a continuous rotating detonation, a pulse detonation, or other forms of pressurized combustion technology.

[0046] In this embodiment of the present invention, a conventional slow-burn combustor is employed in the front, followed by a detonation combustor. The conventional slow-burn combustor primarily ensures stable operation of the gas turbine, providing stable inlet air conditions for the detonation combustor while also contributing to a portion of the power generation capacity based on operating conditions. The detonation combustor primarily provides high-efficiency, low-pollution power generation, improving overall turbine efficiency and reducing overall pollutant emissions. Furthermore, this design addresses the challenges of pure detonation turbines, such as difficulty starting and unstable continuous operation.

[0047] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A gas turbine with a secondary combustion detonation combustion chamber, characterized in that: include: A gas turbine main body, the gas turbine main body comprising a generator, a low-pressure compressor, a high-pressure turbine, and a low-pressure turbine coaxially connected in sequence via a main shaft; a slow-burn combustion chamber, wherein the air inlet of the slow-burn combustion chamber is connected to the exhaust port of the low-pressure compressor, and the exhaust port of the slow-burn combustion chamber is connected to the air inlet of the high-pressure turbine; a detonation combustion chamber, wherein the air inlet of the detonation combustion chamber is connected to the exhaust port of the high-pressure turbine, and the exhaust port of the detonation combustion chamber is connected to the air inlet of the low-pressure turbine; The air inlet of the low-pressure compressor is connected to the atmosphere and is used to compress and boost the atmosphere. The compressed atmosphere enters the slow-burn combustion chamber, mixes with the fuel and burns, and the resulting flue gas enters the high-pressure turbine to drive the high-pressure turbine to perform work. The flue gas discharged from the high-pressure turbine enters the detonation combustion chamber, mixes with the fuel and detonates and burns in the detonation combustion chamber, and the resulting detonation flue gas enters the low-pressure turbine to drive the low-pressure turbine to perform work. The high-pressure turbine and the low-pressure turbine work to drive the generator to generate electrical energy; A detonation combustion cooling system is provided outside the detonation combustion chamber for cooling the wall surface of the detonation combustion chamber; The detonation combustion cooling system includes a cooling channel arranged around 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, so that the atmosphere compressed by the low-pressure compressor cools the wall of the detonation combustion chamber in the cooling channel, and then mixes with the high-speed and high-pressure flue gas generated by the detonation in the exhaust section of the detonation combustion chamber and is discharged to the low-pressure turbine.

2. The gas turbine with a secondary combustion detonation combustion chamber according to claim 1, characterized in that: The detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, the air inlet of the cooling channel is connected to the fuel input pipeline, and the exhaust port of the cooling channel is respectively connected to the slow combustion chamber and the detonation combustion chamber, so that the fuel enters the cooling channel to cool the wall of the detonation combustion chamber, and then enters the slow combustion chamber and the detonation combustion chamber respectively.

3. The gas turbine with a secondary combustion detonation combustion chamber according to claim 1, characterized in that: The detonation combustion cooling system includes a cooling channel arranged around the outer wall of the detonation combustion chamber, and a circulating coolant flows into the cooling channel.

4. The gas turbine with a secondary combustion detonation combustion chamber according to claim 1, characterized in that: The detonation combustion chamber adopts any one of the pressurized combustion modes including continuous rotating detonation and pulse detonation.

5. The gas turbine with a secondary combustion detonation combustion chamber according to claim 1, characterized in that: Regulating control valves are respectively provided on the fuel input pipelines connected to the slow combustion chamber and the detonation combustion chamber.

6. The gas turbine with a secondary combustion detonation combustion chamber according to claim 1, characterized in that: When the gas turbine is in the starting process, the starter-generator is in the motor working mode; when the gas turbine is in low working condition and normal working state, the starter-generator is in the generator working mode.

7. The gas turbine with a secondary combustion detonation combustion chamber according to claim 1, characterized in that: The detonation combustion chamber does not work when the power generation power and flue gas emission heat of the slow combustion chamber meet the requirements. When the power generation power meets the requirements but the flue gas emission heat does not meet the system requirements, the detonation combustion chamber works.

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