An all-electric detonation gas turbine system

Abstract

The present invention provides an all-electric detonation gas turbine system, comprising: a first compressor unit, comprising a first compressor and a first compressor motor connected via a first coupling; a second compressor unit, comprising a second compressor and a second compressor motor connected via a second coupling; a turbine unit, comprising a turbine and a turbine motor connected via a third coupling; a detonation combustion chamber, wherein air is introduced into the air inlets of the first compressor and the second compressor, and the exhaust port of the first compressor is connected to the air inlet of the detonation combustion chamber; the exhaust port of the second compressor is connected to the exhaust port of the detonation combustion chamber, and both are connected to the turbine, so that the compressed air is mixed with the detonation flue gas, and the mixed gas drives the turbine to perform work, thereby driving the turbine motor to generate electricity; and a DC bus, to which the first compressor motor, the second compressor motor, the turbine motor, and the user load are respectively connected. The gas turbine system of the present invention can achieve optimal efficiency and stability for the entire system.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to an all-electric detonation gas turbine 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] Traditional gas turbines primarily improve their overall cycle thermal efficiency by increasing the compressor pressure ratio and combustor outlet temperature. However, due to limitations in materials, processes, and aerodynamic design, significant increases in either the compressor pressure ratio or combustor outlet temperature are difficult, limiting overall power generation efficiency. Traditional gas turbines also face challenges in reducing pollutant emissions. Compared to traditional technologies, detonation combustion can significantly improve the overall cycle efficiency of gas turbines while reducing NOx emissions. However, detonation combustion also presents challenges such as difficulty starting and a narrow operating range.

[0005] In addition, the compressor, turbine, and generator in traditional gas turbines are rigidly connected by the rotor and always operate at the same operating speed. At the same time, the compressor, turbine, and load power must be matched, and component performance matching is difficult. Therefore, under non-design point operating conditions, it is difficult to ensure that all components operate at the optimal efficiency point, resulting in decreased component efficiency and low efficiency of the entire machine components under non-design point operating conditions.

[0006] In addition, traditional gas turbines have a slow response speed when the load changes suddenly, and are prone to voltage and frequency changes under isolated grid operation conditions, resulting in poor stability. Summary of the Invention

[0007] In view of this, an embodiment of the present application provides an all-electric detonation gas turbine system to achieve the purpose of optimizing the efficiency and stability of the entire system.

[0008] The present application provides the following technical solution: an all-electric detonation gas turbine system, comprising:

[0009] a first compressor assembly, the first compressor assembly comprising a first compressor and a first compressor motor, the first compressor and the first compressor motor being connected via a first coupling;

[0010] a second compressor assembly, the second compressor assembly comprising a second compressor and a second compressor motor, the second compressor and the second compressor motor being connected via a second coupling;

[0011] a turbine assembly, the turbine assembly comprising a turbine and a turbine motor, the turbine and the turbine motor being connected via a third coupling;

[0012] Detonation combustion chamber, air is introduced into the air inlets of the first compressor and the second compressor for compressing and supercharging the air, the exhaust port of the first compressor is connected to the air inlet of the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and is mixed with fuel for detonation combustion; the exhaust port of the second compressor is connected to the exhaust port of the detonation combustion chamber and is jointly connected to the turbine, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber, and the mixed air enters the turbine, drives the turbine to perform work, and drives the turbine motor to generate electricity;

[0013] A DC bus is connected to the first compressor motor, the second compressor motor, the turbine motor and a user load respectively.

[0014] According to an embodiment of the present application, the first compressor motor, the second compressor motor, the turbine motor and the user load are respectively connected to the DC bus through a bidirectional AC-DC circuit.

[0015] According to an embodiment of the present application, it further includes a supercapacitor energy storage and a battery pack, and the supercapacitor energy storage and the battery pack are both connected to the DC bus.

[0016] According to an embodiment of the present application, the first compressor assembly includes a plurality of first compressors and a plurality of first compressor motors, and the plurality of first compressors and the plurality of first compressor motors are independently connected via a plurality of first couplings respectively;

[0017] The second compressor assembly includes a plurality of second compressors and a plurality of second compressor motors, and the plurality of second compressors and the plurality of second compressor motors are independently connected via a plurality of second couplings.

[0018] According to one embodiment of the present application, the turbine unit includes multiple turbines and multiple turbine motors, and the multiple turbines and multiple turbine motors are independently connected through multiple third couplings respectively; the number of the detonation combustion chambers is multiple and consistent with the number of the turbines, and the exhaust port of a single detonation combustion chamber is connected to a single turbine.

[0019] According to one embodiment of the present application, there are multiple detonation combustion chambers, and the exhaust ports of the multiple detonation combustion chambers are connected to the turbine through a flue gas main; wherein the turbine is a turbine with adjustable guide vanes.

[0020] According to one embodiment of the present application, it also includes a first compressed air main pipe and a second compressed air main pipe, and the exhaust ports of the multiple first compressors and the air inlets of the multiple detonation combustion chambers are connected through the first compressed air main pipe, and the exhaust ports of the multiple second compressors and the exhaust ports of the multiple detonation combustion chambers are connected through the second compressed air main pipe.

[0021] According to one embodiment of the present application, proportional regulating valves are respectively provided on the air inlet and the exhaust port of the detonation combustion chamber.

[0022] 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.

[0023] 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.

[0024] Compared with the prior art, the at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects:

[0025] (1) Multiple compressors and turbines can operate at different speeds and loads, thus achieving optimal overall system efficiency.

[0026] (2) When the external load changes dramatically, such as load shedding, the supercapacitor energy storage system works to stabilize the DC bus and ensure the stability of the system.

[0027] (3) The battery pack can ensure overload operation for a long time.

[0028] (4) At the same time, when the external load is too small and the overall efficiency of the gas turbine is low, the gas turbine system can be shut down and the battery pack can be used for power supply to ensure that the efficiency of the system is maximized under long-term conditions.

[0029] (5) In view of the narrow working range of the detonation combustion chamber, the present invention adopts two independent compressors. At the same time, the two compressors can independently adjust the load, outlet pressure and temperature. Therefore, by matching the two compressors, the stable operation of the detonation combustion chamber under various working conditions can be met. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] 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.

[0031] Figure 1 1 is a schematic structural diagram of a first embodiment of an all-electric detonation gas turbine system according to the present invention;

[0032] Figure 2 is a schematic structural diagram of a second embodiment of the all-electric detonation gas turbine system of the present invention;

[0033] Figure 3 It is a structural schematic diagram of the third embodiment of the all-electric detonation gas turbine system of the present invention. DETAILED DESCRIPTION

[0034] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0035] 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.

[0036] like Figure 1 As shown, an embodiment of the present invention provides an all-electric detonation gas turbine system, comprising:

[0037] a first compressor assembly, the first compressor assembly comprising a first compressor and a first compressor motor, the first compressor and the first compressor motor being connected via a first coupling; a second compressor assembly, the second compressor assembly comprising a second compressor and a second compressor motor, the second compressor and the second compressor motor being connected via a second coupling; a turbine assembly, the turbine assembly comprising a turbine and a turbine motor, the turbine and the turbine motor being connected via a third coupling;

[0038] Detonation combustion chamber, air is introduced into the air inlets of the first compressor and the second compressor for compressing and supercharging the air, the exhaust port of the first compressor is connected to the air inlet of the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and is mixed with fuel for detonation combustion; the exhaust port of the second compressor is connected to the exhaust port of the detonation combustion chamber and is jointly connected to the turbine, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber, and the mixed air enters the turbine, drives the turbine to perform work, and drives the turbine motor to generate electricity;

[0039] A DC bus is connected to the first compressor motor, the second compressor motor, the turbine motor and a user load respectively.

[0040] In the mechanical connection part of the present invention, the first compressor unit, the second compressor unit and the turbine unit are respectively connected by independent couplings. The three units can operate at different speeds and loads respectively, avoiding the problem of difficult component performance matching, thereby achieving optimal overall system efficiency.

[0041] In one embodiment, the first compressor motor, the second compressor motor, and the turbine motor are respectively connected to the DC bus through a bidirectional AC-DC circuit. In addition, the DC bus is also connected to a user load through a bidirectional AC-DC circuit, and the load end can output three-phase electricity.

[0042] The operating principle of this embodiment is as follows: After being compressed by the first compressor, air enters the detonation combustion chamber, where it mixes with fuel to produce detonation combustion, generating high-temperature flue gas. After being compressed by the second compressor, the air mixes with the high-temperature flue gas at the detonation combustion chamber outlet. After the flue gas is cooled, it enters the turbine to produce work. The turbine drives the motor to produce work, outputting power to the compressor motor and user loads via the DC bus. The compressed air and detonation fuel gas are mixed to form high-temperature flue gas suitable for the turbine, resolving the problem of turbine failure due to excessively high detonation fuel gas temperatures. This improves the life and reliability of the turbine and reduces costs.

[0043] In one embodiment, it also includes supercapacitor energy storage and a battery pack, and the supercapacitor energy storage and the battery pack are both connected to the DC bus. When the external load changes drastically, such as load shedding, the supercapacitor energy storage system works to stabilize the DC bus and ensure the stability of the system. The battery pack can ensure overload operation for a long time. At the same time, when the external load is too small and the overall efficiency of the gas turbine is low, the gas turbine system can be shut down and rely solely on the battery pack for power supply to ensure that the efficiency of the system is maximized under long-term conditions. This embodiment adds supercapacitor energy storage and battery pack energy storage to the DC bus, which can well absorb power shocks and maintain power balance, thereby improving the stability of the overall system.

[0044] In another embodiment of the present invention, Figure 2 As shown, the first compressor group includes multiple first compressors and multiple first compressor motors, and the multiple first compressors and the multiple first compressor motors are independently connected through multiple first couplings; the second compressor group includes multiple second compressors and multiple second compressor motors, and the multiple second compressors and the multiple second compressor motors are independently connected through multiple second couplings.

[0045] Multiple compressors are arranged in a distributed manner and can operate under different loads and speeds. This solves the problem of difficulty in achieving the optimal efficiency of the system due to the power characteristics of a single gas turbine when large-scale applications require multiple gas turbines to be networked and operated. The system can provide better and more stable inlet conditions for the detonation combustion chamber, ensuring its stable operation.

[0046] In a preferred embodiment of this invention, the turbine assembly includes multiple turbines and multiple turbine motors, each independently connected via multiple third couplings. The number of detonation combustion chambers is equal to the number of turbines, and the exhaust port of each detonation combustion chamber is connected to a single turbine. In this embodiment, each compressor, turbine, and detonation combustion chamber can be opened and closed independently, and the load of each compressor, detonation combustion chamber, and turbine can be adjusted independently.

[0047] In another preferred embodiment of this invention, Figure 3As shown, there are multiple detonation combustion chambers, and the exhaust ports of the multiple detonation combustion chambers are all connected to the turbine through a flue gas main; wherein, the turbine is a turbine with adjustable guide vanes. In this solution, the flue gas generated by the multiple detonation combustion chambers all enters the flue gas main, and all the flue gas in the flue gas main enters the turbine with adjustable guide vanes to perform work, driving the generator to generate electricity. The outlet of the flue gas main is connected to a turbine with adjustable guide vanes. When the number of working detonation combustion chambers changes, resulting in a change in flue gas flow, the working inlet conditions of the turbine are guaranteed by adjusting the angle of the adjustable turbine guide vanes. In addition, the turbine inlet is equipped with an adjustable guide vane structure, which can ensure working efficiency within a large flow change range.

[0048] In this embodiment, a first compressed air main pipe and a second compressed air main pipe are further included. The exhaust ports of the multiple first compressors and the air inlets of the multiple detonation combustion chambers are connected through the first compressed air main pipe, and the exhaust ports of the multiple second compressors and the exhaust ports of the multiple detonation combustion chambers are connected through the second compressed air main pipe.

[0049] The compressed air mains are configured so that some compressor outlets connect to the first compressed air main and some to the second compressed air main. The pressures of the first and second compressed air mains can be different or the same. Separating the first and second compressed air mains improves system efficiency, but all compressor outlets can also be connected to a single main pipe.

[0050] In this embodiment, proportional control valves are provided at the air inlet and exhaust ports of the detonation combustion chambers. Each detonation combustion chamber is connected to the first compressed air main via a proportional control valve. The proportional control valves can be used to adjust the bleed air volume for each detonation combustion chamber. Compressed air from the first compressed air main enters the detonation combustion chamber and mixes with fuel for detonation combustion, generating high-temperature flue gas. The high-temperature flue gas at the detonation combustion chamber outlet mixes with compressed air from the second compressed air main, cools down, and then enters the turbine to generate power. The flow rate of the mixed cooling air can be adjusted via the proportional control valve. To address the narrow operating range of the detonation combustion chamber, proportional control valves are used to extract air and mixed air from the compressed air main, ensuring that each detonation combustion chamber always operates at the optimal design point.

[0051] 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.

[0052] In one 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 detonation combustion chamber. Fuel enters the cooling channel to cool the wall of the detonation combustion chamber before entering the detonation combustion chamber. Furthermore, a regulating control valve is provided on the fuel input pipeline connected to the detonation combustion chamber to facilitate operation and control.

[0053] 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.

[0054] In other embodiments, a structure combining multiple cooling methods such as the above-mentioned fuel cooling and external liquid cooling circulation can also be adopted, which can be independently controlled by control valves on the pipeline and can be selected for use according to the high temperature resistance performance of the detonation combustion chamber.

[0055] 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.

[0056] 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. An all-electric detonation gas turbine system, characterized in that: include: a first compressor assembly, the first compressor assembly comprising a first compressor and a first compressor motor, the first compressor and the first compressor motor being connected via a first coupling; a second compressor assembly, the second compressor assembly comprising a second compressor and a second compressor motor, the second compressor and the second compressor motor being connected via a second coupling; a turbine assembly, the turbine assembly comprising a turbine and a turbine motor, the turbine and the turbine motor being connected via a third coupling; Detonation combustion chamber, air is introduced into the air inlets of the first compressor and the second compressor for compressing and supercharging the air, the exhaust port of the first compressor is connected to the air inlet of the detonation combustion chamber, so that the compressed air enters the detonation combustion chamber and is mixed with fuel for detonation combustion; the exhaust port of the second compressor is connected to the exhaust port of the detonation combustion chamber and is jointly connected to the turbine, so that the compressed air is mixed with the detonation flue gas generated by the detonation combustion chamber, and the mixed air enters the turbine, drives the turbine to perform work, and drives the turbine motor to generate electricity; A DC bus is connected to the first compressor motor, the second compressor motor, the turbine motor and a user load respectively.

2. The all-electric detonation gas turbine system according to claim 1, characterized in that: The first compressor motor, the second compressor motor, the turbine motor and the user load are respectively connected to the DC bus through a bidirectional AC-DC circuit.

3. The all-electric detonation gas turbine system according to claim 1, characterized in that: It also includes a supercapacitor energy storage and a battery pack, both of which are connected to the DC bus.

4. The all-electric detonation gas turbine system according to claim 1, characterized in that: The first compressor assembly includes a plurality of first compressors and a plurality of first compressor motors, wherein the plurality of first compressors and the plurality of first compressor motors are independently connected via a plurality of first couplings; The second compressor assembly includes a plurality of second compressors and a plurality of second compressor motors, and the plurality of second compressors and the plurality of second compressor motors are independently connected via a plurality of second couplings.

5. The all-electric detonation gas turbine system according to claim 4, characterized in that: The turbine unit includes multiple turbines and multiple turbine motors, and the multiple turbines and multiple turbine motors are independently connected through multiple third couplings respectively; the number of the detonation combustion chambers is multiple and consistent with the number of the turbines, and the exhaust port of a single detonation combustion chamber is connected to a single turbine.

6. The all-electric detonation gas turbine system according to claim 4, characterized in that: There are multiple detonation combustion chambers, and the exhaust ports of the multiple detonation combustion chambers are connected to the turbine through a flue gas main pipe; wherein the turbine is a turbine with adjustable guide vanes.

7. The all-electric detonation gas turbine system according to claim 5 or 6, characterized in that: It also includes a first compressed air main pipe and a second compressed air main pipe, wherein the exhaust ports of the plurality of first compressors and the air inlets of the plurality of detonation combustion chambers are connected via the first compressed air main pipe, and the exhaust ports of the plurality of second compressors and the exhaust ports of the plurality of detonation combustion chambers are connected via the second compressed air main pipe.

8. The all-electric detonation gas turbine system according to claim 7, characterized in that: Proportional regulating valves are respectively provided on the air inlet and the exhaust port of the detonation combustion chamber.

9. The all-electric detonation gas turbine system according to claim 1, characterized in that: The detonation combustion chamber adopts any one of the pressurized combustion modes including continuous rotating detonation and pulse detonation.

10. The all-electric detonation gas turbine system according to claim 9, characterized in that: A detonation combustion cooling system is provided outside the detonation combustion chamber for cooling the wall surface of the detonation combustion chamber.

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