CN111441869A - Method and system for starting micro gas turbine - Google Patents
Method and system for starting micro gas turbine Download PDFInfo
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- CN111441869A CN111441869A CN202010233095.7A CN202010233095A CN111441869A CN 111441869 A CN111441869 A CN 111441869A CN 202010233095 A CN202010233095 A CN 202010233095A CN 111441869 A CN111441869 A CN 111441869A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/264—Ignition
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
Abstract
The invention provides a method and a system for starting a micro gas turbine, wherein the starting method comprises the following steps: acquiring an environmental parameter and a fuel parameter, and determining a control parameter of the starting process of the micro gas turbine based on the environmental parameter and the fuel parameter; starting the motor and accelerating the motor to an ignition speed; determining that the micro gas turbine meets an ignition condition, and starting an igniter to execute an ignition operation; judging whether the ignition operation is successful; after the ignition operation is successful, fuel is combusted, so that the speed of the micro gas turbine rotor is continuously increased until the motor is disconnected. The invention can ensure the reliable start of the micro gas turbine under different environmental conditions.
Description
Technical Field
The invention relates to the technical field related to a micro gas turbine, in particular to a method and a system for starting the micro gas turbine.
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 system and a method for starting 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-mentioned problems, an object of the present invention is to provide a method and a system for starting a micro gas turbine, which can ensure reliable starting of the micro gas turbine under different environmental conditions.
The technical scheme of the invention is as follows:
according to one aspect of the present invention, there is provided a method of starting a micro gas turbine,
the micro gas turbine is connected with a motor through a rotor, and the starting method comprises the following steps:
acquiring an environmental parameter and a fuel parameter, and determining a control parameter of the starting process of the micro gas turbine based on the environmental parameter and the fuel parameter;
starting the motor and accelerating the motor to an ignition speed;
determining that the micro gas turbine meets an ignition condition, and starting an igniter to execute an ignition operation;
judging whether the ignition operation is successful;
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.
Further, the acquiring the environmental parameter and the fuel parameter includes:
acquiring environmental parameters through an installed sensor or acquiring current environmental parameters updated regularly on a remote server through a equipped remote communication module;
the pre-written fuel heating value, type, composition dependent fuel parameters are obtained by selecting the appropriate fuel option at start-up.
Further, the determining the control parameter of the micro gas turbine starting process based on the environmental parameter and the fuel parameter comprises:
and determining the control parameters by a table look-up method or a trained artificial neural network model.
Further, the starting and accelerating the motor to the ignition speed includes:
the motor is rotated by energy provided by an external energy source and accelerated at a first acceleration, causing the rotor speed to gradually increase to an ignition speed.
Further, the starting and accelerating the motor to the ignition speed includes:
after the motor is started, firstly, the motor is accelerated at a second acceleration;
if the speed of the rotor is successfully increased to the set first speed, accelerating the motor to the ignition speed at a first acceleration;
if the speed of the rotor is not successfully increased to the set first speed, the machine is stopped for self-checking, if no abnormal unit is found, the machine is restarted, and if abnormal unit is found, a fault code is reported to the first-level controller to wait for further processing.
Further, the determining that the micro gas turbine satisfies the ignition condition, and the turning on the igniter to perform the ignition operation includes:
determining that the rotor speed reaches an ignition speed;
maintaining the rotor at an ignition speed, turning on an air pump to supply air and a fuel pump to supply fuel, and adjusting an air supply pressure to a first desired air pressure and a fuel supply pressure to a first desired fuel supply pressure, wherein the air supply pressure and the fuel supply pressure are determined based on an environmental parameter and a fuel parameter;
after the above conditions are met, the igniter is started to execute the ignition operation.
Further, the determining whether the ignition operation is successful includes:
whether the ignition is successful or not is judged based on whether the temperature rise of the tail gas temperature within a certain time period reaches a set value or not, or whether the tail gas temperature reaches the set value within a certain time period and whether the tail gas temperature per se reaches an expected value or not.
Further, said firing operation being successful and the burning of fuel to continue the increase in micro gas turbine rotor speed until the motor is disengaged comprises:
after the ignition operation is successful and the rotor speed is increased to the motor disconnection period, firstly, the rotor speed is controlled to be gradually increased to a set first speed in a stepped mode, and then the rotor speed is continuously increased until the motor disconnection period is reached;
or after the ignition operation is successful and the rotor speed is increased to the disconnection of the motor, the rotor speed is controlled to be gradually increased to the set first speed, the rotor speed is kept at the first speed, and the fuel supply amount is reduced to the given value.
Further, said firing operation being successful and the burning of fuel to continue the increase in micro gas turbine rotor speed until the motor is disengaged comprises:
after the ignition operation is successful, the current of the motor is detected in real time, and when the current of the motor is reduced to a certain set threshold value, the motor is disconnected.
According to another aspect of the invention, a starting system using the micro gas turbine starting method is provided, which comprises a micro gas turbine, a controller and a control module, 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.
Compared with the prior art, the invention has the following beneficial effects:
1. the method for starting the micro gas turbine fully considers the influence of external environmental factors and fuel parameters on the starting of the micro gas turbine, and can ensure the reliable starting of the micro gas turbine under the environments of different temperatures, humidity, altitudes and the like so as to improve the reliability and the service life of the micro gas turbine.
2. The invention can obtain the environmental parameters locally or remotely, so that corresponding sensors or remote communication modules can be selectively configured according to the actual working conditions of the micro gas turbine, and the implementation is facilitated.
3. The invention fully considers the influence of various factors on the starting success rate in the starting process of the micro gas turbine, avoids the frequent starting of the unit due to unreasonable ignition conditions by setting more reasonable ignition conditions, reduces the capacity loss, can effectively improve the starting success rate of the micro gas turbine, and can improve the reliability and the service life of the unit.
4. The starting system of the micro gas turbine provided by the invention can reduce the complexity of the system through reasonably arranging the modules, so that the system is easy to expand and implement.
5. In the process of starting the motor and accelerating the motor to the ignition speed, the invention can realize real-time detection of the running state of the unit, and avoid the serious consequence of unit damage caused by accelerating the unit in case of possible fault of the unit.
Drawings
FIG. 1 is a schematic diagram of a start-up system in an embodiment of the present invention.
Fig. 2 is a flowchart of a start-up method in an embodiment of the invention.
Detailed Description
In order to better understand the technical scheme of the invention, the invention is further explained by combining the specific embodiment and the attached drawings of the specification.
According to one aspect of the present invention, an embodiment of the present invention provides 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 and combining information fed back by each sensor 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. Fuel parameter information such as calorific value, type, composition and the like of the fuel is written into the controller in advance, and the fuel parameter can be obtained by selecting a proper fuel option at the time of starting.
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 starting method of a micro gas turbine, wherein the micro gas turbine is connected with a motor through a rotor, the starting method is characterized by comprising the following steps:
acquiring an environmental parameter and a fuel parameter, and determining a control parameter of the starting process of the micro gas turbine based on the environmental parameter and the fuel parameter;
starting the motor and accelerating the motor to an ignition speed;
determining that the micro gas turbine meets an ignition condition, and starting an igniter to execute an ignition operation;
judging whether the ignition operation is successful;
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.
2. The micro gas turbine startup method of claim 1, wherein the obtaining environmental parameters and fuel parameters comprises:
acquiring environmental parameters through an installed sensor or acquiring current environmental parameters updated regularly on a remote server through a equipped remote communication module;
the pre-written fuel heating value, type, composition dependent fuel parameters are obtained by selecting the appropriate fuel option at start-up.
3. The micro gas turbine startup method of claim 1, wherein the determining control parameters for the micro gas turbine startup process based on the environmental parameters and the fuel parameters comprises:
and determining the control parameters by a table look-up method or a trained artificial neural network model.
4. The micro gas turbine starting method according to claim 1, wherein the starting and accelerating the electric machine to the firing rate comprises:
the motor is rotated by energy provided by an external energy source and accelerated at a first acceleration, causing the rotor speed to gradually increase to an ignition speed.
5. The micro gas turbine starting method according to claim 1, wherein the starting and accelerating the electric machine to the firing rate comprises:
after the motor is started, firstly, the motor is accelerated at a second acceleration;
if the speed of the rotor is successfully increased to the set first speed, accelerating the motor to the ignition speed at a first acceleration;
if the speed of the rotor is not successfully increased to the set first speed, the machine is stopped for self-checking, if no abnormal unit is found, the machine is restarted, and if abnormal unit is found, a fault code is reported to the first-level controller to wait for further processing.
6. The micro gas turbine starting method according to claim 1, wherein the determining that the micro gas turbine satisfies an ignition condition, and the turning on an igniter to perform an ignition operation includes:
determining that the rotor speed reaches an ignition speed;
maintaining the rotor at an ignition speed, turning on an air pump to supply air and a fuel pump to supply fuel, and adjusting an air supply pressure to a first desired air pressure and a fuel supply pressure to a first desired fuel supply pressure, wherein the air supply pressure and the fuel supply pressure are determined based on an environmental parameter and a fuel parameter;
after the above conditions are met, the igniter is started to execute the ignition operation.
7. The micro gas turbine startup method of claim 1, wherein the determining whether the ignition operation was successful comprises:
whether the ignition is successful or not is judged based on whether the temperature rise of the tail gas temperature within a certain time period reaches a set value or not, or whether the tail gas temperature reaches the set value within a certain time period and whether the tail gas temperature per se reaches an expected value or not.
8. The micro gas turbine startup method of claim 1, wherein after the ignition operation is successful, combusting the fuel to continue increasing the micro gas turbine rotor speed until the electric machine is disengaged comprises:
after the ignition operation is successful and the rotor speed is increased to the motor disconnection period, firstly, the rotor speed is controlled to be gradually increased to a set first speed in a stepped mode, and then the rotor speed is continuously increased until the motor disconnection period is reached;
or after the ignition operation is successful and the rotor speed is increased to the disconnection of the motor, the rotor speed is controlled to be gradually increased to the set first speed, the rotor speed is kept at the first speed, and the fuel supply amount is reduced to the given value.
9. The micro gas turbine starting method according to claim 1 or 8, wherein after the ignition operation is successful, combusting the fuel to continuously increase the micro gas turbine rotor speed until the motor is disengaged comprises:
after the ignition operation is successful, the current of the motor is detected in real time, and when the current of the motor is reduced to a certain set threshold value, the motor is disconnected.
10. A starting system using the micro gas turbine starting method according to any one of claims 1 to 9, comprising a micro gas turbine connected with a motor through a rotor, and further comprising a controller, wherein the controller comprises an obtaining module, a determining module, a judging 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.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111878239A (en) * | 2020-08-06 | 2020-11-03 | 中国人民解放军海军工程大学 | Gas turbine starting control system and method |
| CN112696269A (en) * | 2020-11-18 | 2021-04-23 | 靳普 | Multi-rotor micro gas turbine and starting method thereof |
| CN112727602A (en) * | 2020-11-18 | 2021-04-30 | 靳普 | Air-blowing type micro gas turbine and starting method thereof |
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| CN112727602B (en) * | 2020-11-18 | 2023-12-26 | 刘慕华 | Air-blowing type micro gas turbine and starting method thereof |
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