CN111855221A - Combustion state monitoring method and system for gas turbine - Google Patents
Combustion state monitoring method and system for gas turbine Download PDFInfo
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- CN111855221A CN111855221A CN202010738622.XA CN202010738622A CN111855221A CN 111855221 A CN111855221 A CN 111855221A CN 202010738622 A CN202010738622 A CN 202010738622A CN 111855221 A CN111855221 A CN 111855221A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M11/00—Safety arrangements
- F23M11/04—Means for supervising combustion, e.g. windows
- F23M11/045—Means for supervising combustion, e.g. windows by observing the flame
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Abstract
The invention provides a combustion state monitoring method of a gas turbine, which comprises the following steps: s1: detecting a combustion state by using a flame detector, wherein if flame is detected, the gas turbine normally burns, and if flame is not detected by the flame detector, alarming and displaying and carrying out the next step; s2: and detecting the rotating speed of the gas turbine and the exhaust temperature of the turbine, wherein if the rotating speed of the gas turbine is greater than a first threshold value a and the exhaust temperature of the turbine is less than a second threshold value b, the flame is in a extinguished state, otherwise, the gas turbine burns normally. The combustion state monitoring method of the gas turbine provided by the invention monitors the ignition state of the gas turbine by combining the change of the rotating speed and the exhaust temperature of the gas turbine and hardware of the flame detector under different states, solves the problem of misjudgment caused by hardware damage or blocked detection light path when the combustion state of the gas turbine is monitored by the flame detector, and provides a combustion state monitoring method which is simpler and has rapid response.
Description
Technical Field
The invention belongs to the field of aircraft engines, and particularly relates to a method and a system for monitoring a combustion state of a gas turbine.
Background
With the progress of technology, the advantages of compact structure, quick start, smooth operation, high thermal efficiency and the like of a gas turbine have become one of the core power equipment of the 21 st century. The working principle of the gas turbine is that the air compressor compresses air, the compressed air and fuel injected into the combustion chamber generate combustion reaction after entering the combustion chamber, heat is released and changed into high-temperature compressed gas, then the turbine rotates to do work under the pushing of the high-temperature compressed gas, and the fuel in the combustion chamber burns to release heat, which is a precondition for the operation of the gas turbine. If the flame cannot be established during ignition, the start-up or even the shutdown check needs to be restarted; if during normal operation, flameout occurs, unburned fuel may enter the turbine for combustion, causing detonation. It is therefore necessary to closely monitor the flame conditions in the combustion chamber of a gas turbine at all times, both from a normal and a safe operating point of view.
The conventional combustion state monitoring method of the gas turbine monitors the flame state in real time in a mode of installing flame detector hardware, the flame detector has the advantages of rapidness in detection and small time delay, but the requirement on cleanliness is high, and the flame detector is easy to block a light path due to adhesion of oil stains, ash and the like, so that the flame detector fails to detect.
The utility model discloses a utility model patent application number 201821608935.8 discloses a combustion chamber ultraviolet flame detector subassembly, this flame detector subassembly has improved the detection precision through the mode of addding the cap in inside, and the prevention light path that can certain degree is blocked up, but its problem of solving light window pollution and light path jam fundamentally to the method of addding the cap inside the combustion chamber is higher to the material and the processing requirement of cap because of the combustion chamber inside ambient temperature is higher, realizes the difficulty.
The invention patent with the application number of 201510676700.7 discloses a method for controlling engine flameout protection, which provides a method for controlling engine flameout protection, but is mainly applied to diesel fuel engines, and has more parameters required to be calibrated and more complex judgment.
The invention patent with application number 201510070117.1 discloses a gas turbine flame detection system and method, which provides a method for judging the ignition state of a gas turbine by detecting the change of gas flow velocity in a combustion chamber, but because the temperature of the combustion chamber is higher, the requirement on materials is harsh, and especially electrical elements can hardly endure high temperature, the method is difficult to realize, the corresponding time is slow, and the condition of misjudgment is easy to occur.
Therefore, it is desirable to provide a simpler and more accurate method for monitoring the combustion state of a gas turbine combustion chamber to detect the combustion state of the gas turbine combustion chamber.
Disclosure of Invention
In order to solve the problems, the invention provides a method and a system for monitoring the combustion state of a gas turbine.
In order to achieve the above object, the present invention provides a gas turbine combustion state monitoring method, comprising the steps of: s1: detecting a combustion state by using a flame detector, wherein if flame is detected, the gas turbine normally burns, and if flame is not detected by the flame detector, alarming and displaying and carrying out the next step; s2: and detecting the rotating speed of the gas turbine and the exhaust temperature of the turbine, wherein if the rotating speed of the gas turbine is greater than a first threshold value a and the exhaust temperature of the turbine is less than a second threshold value b, the flame is in a extinguished state, otherwise, the gas turbine burns normally.
The method for monitoring the combustion state of the gas turbine, provided by the invention, is also characterized in that: the flame detector is an ultraviolet flame detector.
The method for monitoring the combustion state of the gas turbine, provided by the invention, is also characterized in that: the flame probe of the ultraviolet flame detector is fixed outside a combustion chamber of the gas turbine, and an observation window for observing the flame by the flame probe is arranged on the combustion chamber.
The method for monitoring the combustion state of the gas turbine, provided by the invention, is also characterized in that: the flame detector is directly inserted into a combustion chamber of the gas turbine to detect flame.
The method for monitoring the combustion state of the gas turbine, provided by the invention, is also characterized in that: the rotational speed of the gas turbine is detected by a rotational speed sensor provided in the gas turbine.
The method for monitoring the combustion state of the gas turbine, provided by the invention, is also characterized in that: the first threshold value a is 80% of the rated speed of the gas turbine.
The method for monitoring the combustion state of the gas turbine, provided by the invention, is also characterized in that: the turbine exhaust temperature is detected by a thermocouple temperature sensor associated with the gas turbine.
The method for monitoring the combustion state of the gas turbine, provided by the invention, is also characterized in that: the second threshold value b is 85% of the rated exhaust temperature of the gas turbine.
Another object of the present invention is to provide a gas turbine combustion state monitoring system for performing the monitoring method of any one of the above, the monitoring system comprising: a flame detector for detecting a flame within a combustion chamber of the gas turbine; the rotating speed sensor is used for acquiring the rotating speed of the gas turbine; a thermocouple temperature sensor for acquiring a turbine exhaust temperature of the gas turbine; and the processor is connected with the flame detector, the rotating speed sensor and the thermocouple temperature sensor and is used for processing the data acquired by the flame detector, the rotating speed sensor and the thermocouple temperature sensor.
Has the advantages that:
the combustion state monitoring method of the gas turbine provided by the invention monitors the ignition state of the gas turbine by combining the change of the rotating speed and the exhaust temperature of the gas turbine and hardware of the flame detector under different states, solves the problem of misjudgment caused by hardware damage or blocked detection light path when the combustion state of the gas turbine is monitored by the flame detector, and provides a combustion state monitoring method which is simpler and has rapid response.
The combustion state monitoring system of the gas turbine can monitor the combustion state of the gas turbine more simply, conveniently and accurately, only a processor can be set by acquiring through a rotating speed sensor and a thermocouple temperature sensor which are arranged on the gas turbine, and the replacement cost of the gas turbine is saved.
Drawings
FIG. 1 is a flow chart of a method for monitoring combustion conditions of a gas turbine provided by the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
It is to be understood that the terminology used herein is for the purpose of describing particular example embodiments only, and is not intended to be limiting. As used herein, the singular forms "a", "an" and "the" may be intended to include the plural forms as well, unless the context clearly indicates otherwise. The terms "comprises," "comprising," "including," and "having" are inclusive and therefore specify the presence of stated features, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, steps, operations, elements, components, and/or groups thereof. The method steps, processes, and operations described herein are not to be construed as necessarily requiring their performance in the particular order described or illustrated, unless specifically identified as an order of performance. It should also be understood that additional or alternative steps may be used.
As shown in FIG. 1, the present invention provides a method for monitoring combustion state of a gas turbine, comprising the steps of:
s1: detecting a combustion state by using a flame detector, wherein if flame is detected, the gas turbine normally burns, and if flame is not detected by the flame detector, alarming and displaying and carrying out the next step;
s2: and detecting the rotating speed of the gas turbine and the exhaust temperature of the turbine, wherein if the rotating speed of the gas turbine is greater than a first threshold value a and the exhaust temperature of the turbine is less than a second threshold value b, the flame is in a extinguished state, otherwise, the gas turbine burns normally.
The gas turbine ignition status is monitored by a combination of the gas turbine speed and exhaust temperature changes under different conditions and flame detector hardware. When the flame detector detects flame, the gas turbine is in an ignition state, when the flame detector cannot detect flame, the operating state of the gas turbine is confirmed according to the rotating speed and the exhaust temperature of the gas turbine, when the exhaust temperature and the rotating speed of the gas turbine reach a specified threshold value, the gas turbine is in a flameout state, otherwise, the hardware of the flame detector is damaged or a detection light path is blocked, the upper computer gives an alarm at the moment, but does not stop, and only when all conditions are met, the shutdown operation is carried out when the conclusion that the flame is extinguished is obtained.
In the non-shutdown state, the gas generator will maintain a certain rotor speed, and if below a certain threshold, the gas generator is considered to be shutdown. The running state of the gas turbine is comprehensively judged by combining the rotating speed of the gas turbine, the flame detector, the exhaust temperature of the turbine and other properties, so that the gas turbine can be subjected to flameout protection in time after flameout, and emergency shutdown caused by the fault of the flame detector or the blockage of a flame observation window is avoided. The first threshold value a and the second threshold value b are confirmed according to the change conditions of the rotating speed of the gas turbine and the exhaust temperature of the turbine in the shutdown process of the gas turbine, and the threshold values of different gas turbines under different operation conditions are different.
In another embodiment, the flame detector is an ultraviolet flame detector, a flame probe of the ultraviolet flame detector is fixed outside a combustion chamber of the gas turbine, and the combustion chamber is provided with an observation window required for observing the flame by the flame probe. The flame detector detects the flame intensity of the combustion chamber part in the gas turbine, when ultraviolet rays with the wavelength of 190-.
In another embodiment, a flame detector is inserted directly into the combustion chamber of the gas turbine to detect a flame. The high-temperature-resistant flame detector can avoid light path blockage caused by blockage of the observation window, and further the condition that flame fails to be detected is avoided.
In another embodiment, the rotational speed of the gas turbine is detected by a rotational speed sensor associated with the gas turbine. The turbine exhaust temperature is sensed by a thermocouple temperature sensor associated with the gas turbine. The rotating speed and the turbine exhaust temperature of the gas turbine are acquired through a rotating speed sensor and a thermocouple temperature sensor which are configured on the gas turbine, and the control system hardware reads and processes the two signals and then judges and processes the signals in a control logic.
In another embodiment, the first threshold value a is 80% of the rated speed of the gas turbine. The second threshold value b is 85% of the rated exhaust gas temperature of the gas turbine.
A gas turbine combustion state monitoring system for performing the gas turbine combustion state monitoring method as described in fig. 1, the system comprising:
a flame detector for detecting a flame within a combustion chamber of the gas turbine;
the rotating speed sensor is used for acquiring the rotating speed of the gas turbine;
a thermocouple temperature sensor for acquiring a turbine exhaust temperature of the gas turbine;
and the processor is connected with the flame detector, the rotating speed sensor and the thermocouple temperature sensor and is used for processing the data acquired by the flame detector, the rotating speed sensor and the thermocouple temperature sensor.
In summary, the combustion state monitoring method and system for the gas turbine provided by the invention comprehensively judge the operation state of the gas turbine by combining the rotation speed change rate of the gas turbine, the flame detector and the turbine exhaust temperature, so that the gas turbine can be flameout protected in time after flameout, and the emergency shutdown of the gas turbine caused by the fault of the flame detector or the blockage of the flame observation window is avoided.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are also included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A method of monitoring combustion conditions in a gas turbine, the method comprising the steps of:
s1: detecting a combustion state by using a flame detector, wherein if flame is detected, the gas turbine normally burns, and if flame is not detected by the flame detector, alarming and displaying and carrying out the next step;
s2: and detecting the rotating speed of the gas turbine and the exhaust temperature of the turbine, wherein if the rotating speed of the gas turbine is greater than a first threshold value a and the exhaust temperature of the turbine is less than a second threshold value b, the flame is in a extinguished state, otherwise, the gas turbine burns normally.
2. The gas turbine combustion state monitoring method as set forth in claim 1, wherein the flame detector is an ultraviolet flame detector.
3. The method for monitoring the combustion state of the gas turbine as claimed in claim 2, wherein the flame probe of the ultraviolet flame detector is fixed outside the combustion chamber of the gas turbine, and the combustion chamber is provided with an observation window required for the flame probe to observe the flame.
4. The gas turbine combustion state monitoring method according to claim 1, wherein the flame detector is directly inserted into a combustion chamber of the gas turbine to detect a flame.
5. The method of monitoring a combustion state of a gas turbine according to claim 1, wherein the rotational speed of the gas turbine is detected by a rotational speed sensor provided in the gas turbine.
6. The gas turbine combustion state monitoring method according to claim 5, wherein the first threshold value a is 80% of a rated rotation speed of the gas turbine.
7. The gas turbine combustion state monitoring method of claim 1, wherein the turbine exhaust temperature is detected by a thermocouple temperature sensor provided in the gas turbine.
8. The gas turbine combustion state monitoring method according to claim 7, wherein the second threshold value b is 85% of the rated exhaust temperature of the gas turbine.
9. A gas turbine combustion state monitoring system for monitoring a combustion state of a gas turbine by the gas turbine combustion state monitoring method according to any one of claims 1 to 8.
10. A gas turbine combustion state monitoring system according to claim 9, the system comprising:
a flame detector for detecting a flame within a combustion chamber of the gas turbine;
the rotating speed sensor is used for acquiring the rotating speed of the gas turbine;
a thermocouple temperature sensor for acquiring a turbine exhaust temperature of the gas turbine;
and the processor is connected with the flame detector, the rotating speed sensor and the thermocouple temperature sensor and is used for processing the data acquired by the flame detector, the rotating speed sensor and the thermocouple temperature sensor.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010738622.XA CN111855221A (en) | 2020-07-28 | 2020-07-28 | Combustion state monitoring method and system for gas turbine |
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| CN202010738622.XA CN111855221A (en) | 2020-07-28 | 2020-07-28 | Combustion state monitoring method and system for gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113916829A (en) * | 2021-11-12 | 2022-01-11 | 西安热工研究院有限公司 | Gas turbine combustion monitoring and diagnosing device based on TDLAS technology |
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