CN212563463U - Miniature gas turbine starting system - Google Patents
Miniature gas turbine starting system Download PDFInfo
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- CN212563463U CN212563463U CN202020422450.0U CN202020422450U CN212563463U CN 212563463 U CN212563463 U CN 212563463U CN 202020422450 U CN202020422450 U CN 202020422450U CN 212563463 U CN212563463 U CN 212563463U
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Abstract
The utility model provides a micro gas turbine starting system, which comprises a micro gas turbine, wherein the micro gas turbine is connected with a motor through a rotor, and the micro gas turbine starting system also comprises a controller, wherein the controller comprises an acquisition module, a determination module, a judgment module and a control module; the acquisition module is configured to acquire an environmental parameter and a fuel parameter; the determining module is configured to determine that the micro gas turbine satisfies an ignition condition; the judging module is configured to judge whether the ignition operation is successful; the control module is configured to determine control parameters of the starting process of the micro gas turbine based on the data fed back by the obtaining module, the determining module and the judging module, and control the operation of the motor and the ignition operation of the micro gas turbine. The utility model discloses can ensure the reliable start-up of miniature gas turbine under the ambient condition of difference.
Description
Technical Field
The utility model relates to a miniature gas turbine correlation technique field especially relates to a miniature gas turbine starting system.
Background
The start-up control of a micro gas turbine is one of the most important control contents of a micro gas turbine system. The ignition success rate is low in the starting process of the existing micro gas turbine, and the starting failure is easy to happen. Particularly, as the application of the micro gas turbine becomes wide, the micro gas turbine needs to work in environment working areas with different temperatures, humidity, altitudes and the like, and the environmental factors greatly influence the air pressure, the combustion performance of fuel oil and the temperature change in the combustion process of the air and fuel oil mixture, thereby influencing the starting process of the micro gas turbine. The unsuccessful ignition results in frequent starting of the gas turbine system, affecting the reliability of the micro gas turbine and reducing the service life of the micro gas turbine.
Therefore, designing a starting system of a micro gas turbine to ensure reliable starting of the micro gas turbine under different environmental conditions is a technical problem to be solved urgently by those skilled in the art.
Disclosure of Invention
In order to solve the above technical problem, an object of the present invention is to provide a micro gas turbine starting system, which can ensure reliable starting of the micro gas turbine under different environmental conditions.
The technical scheme of the utility model as follows:
a micro gas turbine starting system comprises a micro gas turbine and a controller, wherein the micro gas turbine is connected with a motor through a rotor, and the controller comprises an acquisition module, a determination module, a judgment module and a control module;
the acquisition module is configured to acquire an environmental parameter and a fuel parameter; the determining module is configured to determine that the micro gas turbine satisfies an ignition condition; the judging module is configured to judge whether the ignition operation is successful; the control module is configured to determine control parameters of the starting process of the micro gas turbine based on the data fed back by the obtaining module, the determining module and the judging module, and control the operation of the motor and the ignition operation of the micro gas turbine.
Further, the control module is configured to determine control parameters for the micro gas turbine startup process based on a table lookup or an artificial neural network model.
Further, the device also comprises an environmental parameter sensor, and the controller acquires the measured environmental parameter through the environmental parameter sensor.
The controller obtains the current environmental parameters updated on the remote server at regular time through the remote communication module.
Further, an external energy source is included and configured to provide energy to rotate the motor.
Further, the external energy source is a battery pack.
Further, the device also comprises a speed sensor, and the controller determines the rotation speed of the rotor through the speed sensor.
The controller controls air supply pressure through the air path valve and controls fuel supply pressure through the fuel regulating valve.
Further, a temperature sensor is arranged at an exhaust port of the combustion chamber of the micro gas turbine, and the controller judges whether the ignition operation is successful or not through the temperature sensor.
Further, the controller is configured to detect the motor current in real time, and when the motor current is less than a predetermined threshold, the motor is disengaged.
Compared with the prior art, the utility model discloses following beneficial effect has:
1. the utility model provides a miniature gas turbine starting system has fully considered the influence of external environment factor and fuel parameter to miniature gas turbine start-up, and it can ensure that miniature gas turbine reliably starts under environment such as different temperatures, humidity, height above sea level to improve miniature gas turbine's reliability and life.
2. The utility model discloses the accessible acquires environmental parameter locally or long-rangely to alright do benefit to the implementation according to the corresponding sensor of miniature gas turbine actual operating condition selectivity configuration or remote communication module.
3. The utility model provides a miniature gas turbine starting system through the reasonable setting to the module, can the reduce system's complexity for the system easily extends and implements.
Drawings
Fig. 1 is a schematic diagram of a starting system in an embodiment of the present invention.
Fig. 2 is a flowchart of a starting method according to an embodiment of the present invention.
Detailed Description
In order to better understand the technical solution of the present invention, the present invention will be further explained with reference to the following specific embodiments and the accompanying drawings.
According to an aspect of the present invention, embodiments of the present invention provide a micro gas turbine starting system, as shown in fig. 1.
The starting system of the embodiment mainly comprises a micro gas turbine, a motor and a controller. The micro gas turbine usually consists of a compressor, a turbine (also called turbine), a combustion chamber and a regenerator, and the micro gas turbine is generally connected with an electric motor (the micro gas turbine and the electric motor are also called a micro gas turbine generator set or a micro gas turbine set). The motor, compressor wheel, and turbine wheel of the unit are coaxially mounted on the rotor, supported and fixed by bearings (typically air bearings). The motor of the unit is designed to be used in two directions, and is used as the motor in the starting process, and the micro gas turbine is driven to work by external energy supply; when the generator works normally, the generator outputs electric energy to the outside, namely, the existing starting integrated motor.
The starting process of the micro gas turbine in the embodiment is mainly controlled by the controller. The controller mainly comprises an acquisition module, a determination module, a judgment module and a control module, wherein the acquisition module, the determination module and the judgment module are all connected with the control module.
The acquisition module is mainly used for acquiring environmental parameters and fuel parameters, the acquisition module can acquire the environmental parameters locally or remotely, the system can be provided with corresponding environmental parameter sensors, the acquisition module acquires the environmental parameters measured by the sensors, the system can also be provided with a remote communication module, and the controller acquires the current environmental parameters updated regularly on a remote server through the remote communication module. The heat value, type, composition and other information of the fuel are written into the controller in advance, and the fuel parameters can be obtained by selecting proper fuel options at the time of starting. The acquisition module sends the acquired data to the control module, and the control module determines control parameters of the starting process of the micro gas turbine based on the environmental parameters and the fuel parameters.
The determining module is mainly used for determining that the micro gas turbine meets the ignition condition, the determining module sends data to the control module after determining that the micro gas turbine meets the ignition condition, and the control module executes the ignition operation by starting the igniter.
The judging module is mainly used for judging whether the ignition operation is successful. Specifically, the determination module may determine whether the ignition operation is successful based on a temperature of the exhaust gas measured by a temperature sensor disposed at an exhaust port of the micro gas turbine combustor.
The control module is mainly used for determining control parameters of the starting process of the micro gas turbine based on data fed back by the acquisition module, the determination module and the judgment module, and controlling the operation of the motor and the ignition operation of the micro gas turbine. The operation of the starting motor can be started by supplying energy from an external energy source (such as a battery pack) to enable the motor to rotate, the speed of the rotor can be measured by the speed sensor when the motor rotates, after the rotor reaches the ignition speed, the control module can open the air pump to supply air and the fuel pump to supply fuel, the air supply pressure value is adjusted to the expected air pressure through the air path valve, the fuel supply is adjusted to the expected pressure through the fuel adjusting valve, the nozzle is opened to inject air and fuel mixture into the combustion chamber, and the igniter is opened to ignite the air and fuel mixture. After ignition is successful, along with fuel combustion, the motor current is gradually reduced, the motor current can be detected in real time, when the motor current is reduced to a certain threshold value, the motor is disconnected, and the motor disconnection means that the motor finishes the running state of the motor.
The starting process of the gas turbine generator set is specifically described below by taking the motor as an example for starting the integrated motor.
The gas turbine controller (Electronic Control Unit, abbreviated as ECU) realizes the closed-loop Control of the output power of the gas turbine by controlling actuators such as a pump body, a valve body, an ignition controller and the like in an oil-gas circuit, combining information fed back by each sensor and matching with a motor power controller (Data Processing Center, abbreviated as DPC).
Specifically, after receiving the starting signal, the ECU sends a motor driving mode instruction to the DPC; and switching the DPC to a motor driving mode, carrying out frequency conversion on the direct current of the built-in battery of the gas turbine by the DPC, driving the motor to work, and driving the gas turbine to increase the rotating speed by the motor.
And opening the fuel valve after the rotating speed of the gas turbine is increased to the ignition rotating speed, and entering an ignition program. Air enters the air compressor from the air inlet channel to be compressed and then enters the heat regenerator and is preheated by high-temperature gas exhausted from the turbine, the preheated compressed air enters the combustion chamber to be mixed with fuel and combusted, the high-temperature high-pressure gas after the combustion chamber is fully combusted enters the turbine to impact the turbine, so that the turbine of the turbine rotates, the cold compressed air before entering the combustion chamber is preheated by the exhaust pipe after the turbine exhausts, and the turbine drives the air compressor to rotate together to the self-sustaining speed due to the fact that the turbine is connected with the air compressor and the motor through the rotating shaft.
After the gas turbine reaches the self-sustaining rotating speed, the DPC is hung up, the motor idles and continues to increase the accelerator, and the turbine continues to increase the power, so that the rotating speed is increased to the working rotating speed. The ECU sends a generator mode command to the DPC; the DPC is switched to a generator mode, and alternating current output by the motor is rectified and transformed to output voltage and current required by a user.
According to the micro gas turbine starting system provided by the embodiment, the controller is used for acquiring a plurality of parameters in the starting process of the micro gas turbine, so that the motor operation and the gas turbine ignition operation are controlled, and the starting success rate of the micro gas turbine in various environments can be improved.
According to another aspect of the present invention, an embodiment of the present invention provides a method for starting a micro gas turbine, as shown in fig. 2.
The method for starting the micro gas turbine mainly comprises the following steps:
s110: and acquiring environmental parameters and fuel parameters, and determining control parameters of the starting process of the micro gas turbine based on the environmental parameters and the fuel parameters.
The environmental parameters include, but are not limited to, one or more of ambient temperature, humidity, air pressure, and the like. The controller may obtain these environmental parameters locally or remotely. In particular, the system may be equipped with corresponding sensors, the controller acquiring these environmental parameters measured by the sensors. The system can also be provided with a remote communication module, and the controller acquires the current environmental parameters updated regularly on the remote server through the remote communication module.
The fuel parameter is a parameter related to the heating value of the fuel. For example, the fuel parameter may be directly a fuel calorific value, or may be a type or composition of the fuel, and the controller may determine the corresponding calorific value according to the type or composition of the fuel. The application does not limit the type of the fuel, and the fuel can be gas fuel, liquid fuel or solid fuel; the fuel can be a single-component fuel or a mixed fuel.
Based on the environmental parameter and the fuel parameter, the controller may determine a control parameter for the micro gas turbine startup process. For example: temperature rise value, fuel quantity and air quantity corresponding to different rotating speeds, and the like. The method for determining the control parameters of the starting process of the micro gas turbine can be determined by a table look-up method or an artificial neural network model.
If the artificial neural network model is adopted for determination, the acquired environmental parameters and fuel parameters are used as input parameters of the trained artificial neural network model, and control parameters are output by the model.
Working in environment with large temperature difference day and night, and feeding back the outside temperature.
S120: the motor is started and accelerated to ignition speed.
The micro gas turbine usually consists of a compressor, a turbine (also called turbine), a combustion chamber and a regenerator, and the micro gas turbine is generally connected with an electric motor (the micro gas turbine and the electric motor are also called a micro gas turbine generator set or a micro gas turbine set). The motor, compressor wheel, and turbine wheel of the unit are coaxially mounted on the rotor, supported and fixed by bearings (typically air bearings). The motor of the unit is designed to be used in two directions, and is used as the motor in the starting process, and the micro gas turbine is driven to work by external energy supply; when in normal work, the generator is used as a generator and outputs electric energy to the outside.
In some embodiments, the motor is started, and an external energy source (e.g., a battery pack) powers the motor to rotate and accelerate the motor at a first acceleration rate, causing the rotor speed to gradually increase to ignition speed.
In other embodiments, after the motor is started, the running state of the unit is detected, and the rotor is accelerated to the ignition speed. The specific method for detecting the running state of the unit is that the motor is accelerated at the second acceleration, if the speed of the rotor can be successfully accelerated to the first speed (for example, 1000 revolutions per minute or 1000rpm), the running condition of the motor is determined to be good, and the motor can be continuously accelerated to the ignition speed at the first acceleration. If the speed of the rotor fails to increase to the first speed, the unit can automatically stop for self-checking, and if no abnormal unit is found, the unit can be restarted. If the abnormal condition is found, the fault code is reported to the upper-level controller to wait for further processing. The running state of the unit is detected, so that the serious consequence of unit damage caused by acceleration of the unit under the condition that the unit possibly has faults can be avoided. For example, due to failure of the air bearing, the rotor fails to suspend, and the bearing rubs against the rotor, forcing the rotor to accelerate may cause severe wear to the rotor and bearing, bending deformation of the rotor, and even damage to the unit components.
And S130, determining that the combustion engine meets the ignition condition, and starting an igniter to perform ignition operation.
The ignition conditions were:
(1) the rotor speed reaches the ignition speed;
(2) after condition (1) is satisfied, the rotor is maintained at the ignition speed, the air pump air supply and the fuel pump fuel supply are turned on, and the air supply pressure and the fuel supply pressure are adjusted to the first desired air pressure and the first desired fuel supply pressure. The air supply pressure is regulated by an air passage valve and the fuel supply pressure is regulated by a fuel regulating valve. Wherein the first desired air pressure and the first desired fueling pressure are determined based on the environmental parameter and the fuel parameter. For example, the use of diesel fuel is greater than the first desired fuel supply pressure using kerosene. As another example, the first desired fuel supply pressure may be lower in high altitude areas than in low altitude areas.
After the two ignition conditions are met, the nozzle is opened to spray air and fuel mixture into the combustion chamber, and the igniter is started to ignite the air and fuel mixture.
S140: and judging whether the ignition operation is successful.
The effective judgment of whether the ignition is successful plays an important role in the successful start of the unit. If the ignition is not successful, the next operation is carried out, so that the starting failure is caused, the unit frequently executes the starting operation, not only is unnecessary energy consumed, but also the unit is damaged, the reliability of the unit is influenced, and the service life is shortened. The ignition success can be judged as follows.
Whether ignition is successful or not can be judged based on whether the temperature rise of the exhaust gas temperature within a certain period of time reaches a set value or not, or whether the exhaust gas temperature within a certain period of time reaches a set value and whether the exhaust gas temperature itself reaches an expected value or not.
In some embodiments, the determination may be made by determining the temperature rise of the exhaust gas over a period of time. For example, after the ignition operation, the temperature rise of the exhaust gas temperature within 5s is 20 ℃ or more, and the ignition operation is considered to be successful. The values 5s and 20 ℃ are determined on the basis of the environmental parameters and the fuel parameters. For example, the environmental temperature is different, and the length of the judgment time and/or the magnitude of the temperature rise can be set to different values. For another example, with fuels having different heat values, the length of the judgment time and/or the magnitude of the temperature rise may be set to be different. Preferably, in order to more effectively judge whether the ignition operation is successful, the temperature rise of the exhaust gas temperature within a certain time period can be detected for a plurality of times (such as 2 times, 3 times, 4 times and the like). And if the temperature rise requirement within a certain time is met for 2-3 times, the ignition is considered to be successful.
In other embodiments, in order to further efficiently determine whether the ignition operation is successful, the reliability of the determination result is ensured. In addition to meeting the condition that the temperature of the exhaust gas rises to a certain value or more within a certain period of time, the temperature of the exhaust gas itself needs to reach a desired set value (e.g., 250 ℃, 300 ℃ and the like), which is also related to environmental parameters and fuel parameters.
The temperature of the exhaust gas is measured by a temperature sensor arranged at the exhaust port of the combustion chamber of the combustion engine.
S150: after the ignition operation is successful, fuel is combusted, so that the speed of the rotor of the micro gas turbine is continuously increased until the motor is disconnected.
After the ignition is successful, the mixture of the fuel and the air is combusted in the combustion chamber to form high-temperature gas, the high-temperature gas then flows into the turbine to expand and do work, the turbine generates output power, and the turbine and the motor jointly drive the rotor to increase the speed. The motor current is gradually reduced, the motor current is detected in real time, when the motor current is reduced to a certain threshold value (which can be set, for example, 0.05A), the motor is disconnected (namely, the motor finishes the motor running state), then the rotor is independently driven by the turbine to rotate, and the motor is converted into the generator running state.
In some embodiments, in order to control the stable acceleration of the unit, the rotor is controlled in two stages after the ignition is successful and the speed of the rotor rises until the motor is disconnected. The controller controls the rotor speed to increase in a step mode to the first rotor speed, and then the rotor speed is continuously increased until the motor is disconnected.
In other embodiments, the heated components of the unit are not heated uniformly enough after ignition is successful. In order to enable the combustion chamber to have a uniformly heated process, the unit is guaranteed to have good thermal symmetry in the starting process, the starting process is safer, meanwhile, the combustion chamber can reach the specified temperature so as to improve the economical efficiency of fuel oil, and the gentle heating process of the combustion chamber is increased. Specifically, the controller controls the rotor speed to be increased stepwise first to the first rotor speed, and then maintains the rotor speed at the first rotational speed while reducing the fuel supply amount to a given value. The fueling quantity at this stage is lower than the fueling quantity at the ignition stage in step 130. The reason is that the fuel supply amount in the ignition stage is generally large in order to ensure successful ignition, and the smooth heating process of the combustion chamber needs to ensure that the temperature of the combustion chamber can be smoothly increased to a specified temperature without influencing the stability and safety of the unit.
The method for starting the micro gas turbine fully considers various influence factors in the starting process of the micro gas turbine, and can ensure the reliable starting of the micro gas turbine under different environmental conditions by reasonably setting the starting conditions of the micro gas turbine.
The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be appreciated by a person skilled in the art that the scope of the invention as referred to in the present application is not limited to the embodiments with a specific combination of the above-mentioned features, but also covers other embodiments with any combination of the above-mentioned features or their equivalents without departing from the inventive concept. For example, the features described above have similar functions to (but are not limited to) those disclosed in this application.
Claims (10)
1. A micro gas turbine starting system comprises a micro gas turbine, wherein the micro gas turbine is connected with a motor through a rotor, and the micro gas turbine starting system is characterized by further comprising a controller, wherein the controller comprises an acquisition module, a determination module, a judgment module and a control module;
the acquisition module is configured to acquire an environmental parameter and a fuel parameter; the determining module is configured to determine that the micro gas turbine satisfies an ignition condition; the judging module is configured to judge whether the ignition operation is successful; the control module is configured to determine control parameters of the starting process of the micro gas turbine based on the data fed back by the obtaining module, the determining module and the judging module, and control the operation of the motor and the ignition operation of the micro gas turbine.
2. The micro gas turbine engine starting system according to claim 1, wherein the control module is further configured to determine control parameters for the micro gas turbine engine starting process based on a table lookup or an artificial neural network model.
3. The micro gas turbine startup system of claim 1, further comprising an environmental parameter sensor, wherein the controller obtains a measured environmental parameter via the environmental parameter sensor.
4. The micro gas turbine starting system according to claim 1, further comprising a remote communication module and a remote server, wherein the controller obtains the current environmental parameters updated periodically on the remote server through the remote communication module.
5. The micro gas turbine starting system according to claim 1, further comprising an external energy source configured to provide energy to rotate the electric machine.
6. The micro gas turbine starting system according to claim 5, wherein the external energy source is a battery pack.
7. The micro gas turbine engine starting system of claim 1, further comprising a speed sensor, wherein the controller determines the rotor rotational speed via the speed sensor.
8. The micro gas turbine startup system of claim 1,
the air pump and the fuel pump are connected with the combustion chamber of the micro gas turbine, an air path valve is arranged on a pipeline between the air pump and the combustion chamber, a fuel regulating valve is arranged on a pipeline between the fuel pump and the combustion chamber, and the controller controls air supply pressure through the air path valve and controls fuel supply pressure through the fuel regulating valve.
9. The micro gas turbine starting system according to claim 1, wherein a temperature sensor is provided at a combustion chamber exhaust port of the micro gas turbine, and the controller determines whether an ignition operation is successful or not by the temperature sensor.
10. The micro gas turbine startup system of claim 1 wherein the controller is further configured to sense the motor current in real time and disengage the motor when the motor current is less than a set threshold.
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| CN202020422450.0U CN212563463U (en) | 2020-03-29 | 2020-03-29 | Miniature gas turbine starting system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114718736A (en) * | 2022-05-13 | 2022-07-08 | 哈尔滨工程大学 | Optimal ignition position regulating and controlling method suitable for gas turbine under different environments |
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2020
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114718736A (en) * | 2022-05-13 | 2022-07-08 | 哈尔滨工程大学 | Optimal ignition position regulating and controlling method suitable for gas turbine under different environments |
| CN114718736B (en) * | 2022-05-13 | 2024-05-17 | 哈尔滨工程大学 | Optimal ignition position regulating and controlling method of gas turbine suitable for different environments |
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Effective date of registration: 20210415 Address after: 100176 room 1202a, 12 / F, block B, building 1, yard 19, Ronghua Middle Road, economic and Technological Development Zone, Daxing District, Beijing Patentee after: Jin Pu Address before: 100029 room 104, No.101, building 3, yard a 29, North Third Ring Middle Road, Xicheng District, Beijing Patentee before: Zhiyue Tengfeng Technology Group Co.,Ltd. Patentee before: Jin Pu |
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Effective date of registration: 20230419 Address after: 518063 10 Nanshan District Road, Gaoxin south, Nanshan District, Shenzhen, Guangdong. Patentee after: Liu Muhua Address before: 100176 room 1202a, 12 / F, block B, building 1, yard 19, Ronghua Middle Road, economic and Technological Development Zone, Daxing District, Beijing Patentee before: Jin Pu |