CN112326257A - Combustion stability state monitoring and diagnosing system of gas turbine - Google Patents
Combustion stability state monitoring and diagnosing system of gas turbine Download PDFInfo
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- CN112326257A CN112326257A CN202011314042.4A CN202011314042A CN112326257A CN 112326257 A CN112326257 A CN 112326257A CN 202011314042 A CN202011314042 A CN 202011314042A CN 112326257 A CN112326257 A CN 112326257A
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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
- 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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
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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
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The invention discloses a combustion stability state monitoring and diagnosing system of a gas turbine, which comprises a sensor cooling structure (1), a dynamic pressure sensor (2), a high-frequency data acquisition unit (3) and a data analysis processor (4); the sensor cooling structure (1) and the inner wall of a pressure measuring hole of a combustion chamber (5) of a tested object are arranged in parallel, the dynamic pressure sensor (2) is arranged on the upper end face of the sensor cooling structure (1), the high-frequency data collector (3) is connected with the dynamic pressure sensor (2), and the data analysis processor (4) is connected with the high-frequency data collector (3). The dynamic pressure sensor cooling structure is adopted, the circulating cooling water is used for cooling the high-temperature flue gas, the length of the pressure sensing cavity is shortened, the attenuation of the pressure sensing cavity to a combustion pressure pulsation signal can be reduced, and the measurement accuracy of the combustion pressure pulsation is improved.
Description
Technical Field
The invention relates to a combustion stability state monitoring and diagnosing system, in particular to a combustion stability state monitoring and diagnosing system of a gas turbine.
Background
A dry low-nitrogen lean-burn premixed combustion technology is generally adopted on a heavy-duty gas turbine to meet the requirement of low emission of combustion pollutants, but due to poor stability of lean-burn premixed combustion, unstable combustion is easy to occur when the operation parameters of the gas turbine deviate from the design parameters. The phenomenon of combustion instability is a core problem which must be considered and faced by gas turbine development and operation maintenance personnel, and is mainly characterized by severe pulsation of pressure in a combustion chamber and sharp whistling sound, and is mainly generated by coupling resonance formed by heat release rate of combustion and pressure pulsation transmitted back and forth. The combustion heat release of the premixed flame is mainly concentrated at the front edge position of the flame, and the unsteady corrugation of the flame surface can cause tiny pressure pulsation under the action of turbulence. When these pulses are transmitted back and forth in the combustion chamber, the wrinkling of the flame surface is caused again, the instantaneous combustion heat release rate is increased, and larger pressure pulses are excited, thus entering a vicious cycle of thermoacoustic coupling. If the pressure pulsation cannot be properly dissipated, the unstable combustion phenomenon occurs, the problems of backfire of a combustion chamber, blow-out of nozzle flame, incomplete combustion and the like occur, and even the flame tube bulge cracks in serious cases, the expensive hot channel component of the combustion engine is damaged, and the maintenance period of the hot channel component is shortened.
In order to solve the problem of stability of lean-burn premixed combustion of a heavy-duty gas turbine, a combustion stability state monitoring system is installed on a combustion chamber by a gas turbine production manufacturer, and the fault that thermal channel parts such as the combustion chamber of the gas turbine, a turbine and the like are damaged due to large combustion pressure pulsation is prevented by monitoring the combustion pressure pulsation in the combustion chamber in real time. The existing combustion stability state monitoring system mainly measures the pressure pulsation condition in a combustion chamber through a dynamic pressure sensor, but because the combustion chamber is filled with high-temperature flue gas after combustion all the time, the measured environment temperature is far higher than the working temperature allowed by the dynamic pressure sensor, the existing combustion stability state monitoring system is mainly solved through two methods, firstly, the dynamic pressure sensor is installed in an unburnt cold state area outside the combustion chamber, the dynamic pressure sensor is prevented from being in direct contact with the high-temperature flue gas, secondly, the high-temperature flue gas in the combustion chamber is led to the outside of the combustion chamber through a long pressure leading pipe, and the temperature of the flue gas at the tail end of the pressure leading pipe is lower than the working temperature allowed by the dynamic. The two methods above find use in the following problems: 1) the dynamic pressure sensor is arranged in an unburned cold state area outside the combustion chamber, the dynamic pressure sensor cannot directly measure and obtain combustion pressure pulsation inside the combustion chamber, only can indirectly measure the pressure pulsation condition of the combustion pressure pulsation in the combustion chamber after the combustion pressure pulsation is attenuated by the fuel nozzle structure, and the measurement result has a certain difference with a real value; 2) because the flue gas temperature is higher, the flue gas temperature can be reduced to the allowable working temperature of the dynamic pressure sensor only by a longer pressure guiding pipe, and the longer pressure guiding pipe has an attenuation effect on the combustion pressure pulsation, so that the difference exists between the measurement result and the real pressure pulsation in the combustion chamber. In addition, the existing combustion stability state monitoring system is only provided with an alarm value and a trip value, only the amplitude of combustion pressure pulsation is evaluated, and the amplitude of the pressure pulsation is an unstable combustion result index and has no capability of predicting in advance.
Disclosure of Invention
The invention provides a combustion stability state monitoring and diagnosing system of a gas turbine, which aims to solve the problem that the existing combustion stability state monitoring system of a heavy gas turbine cannot predict combustion instability of the gas turbine in advance and improve the measurement accuracy of combustion pressure pulsation. According to the invention, the frequency and amplitude information of the combustion pressure pulsation are obtained by adopting fast Fourier transform and short-time Fourier transform calculation, and the amplitude increasing rate of each frequency is calculated, so that whether the gas turbine has the unstable combustion phenomenon can be predicted in advance according to the amplitude increasing rate of each frequency. In addition, the dynamic pressure sensor cooling structure is adopted, the circulating cooling water is used for cooling the high-temperature flue gas, the length of the pressure sensing cavity is shortened, the attenuation of the pressure sensing cavity to a combustion pressure pulsation signal can be reduced, and the measurement accuracy of the combustion pressure pulsation is improved.
The invention is realized by adopting the following technical scheme:
a combustion stability state monitoring and diagnosing system of a gas turbine comprises a sensor cooling structure, a dynamic pressure sensor, a high-frequency data collector and a data analysis processor; the sensor cooling structure is arranged parallel and level with the inner wall of the pressure measuring hole of the combustion chamber of the tested object, the dynamic pressure sensor is arranged on the upper end face of the sensor cooling structure, the high-frequency data acquisition unit is connected with the dynamic pressure sensor, and the data analysis processor is connected with the high-frequency data acquisition unit.
The invention has the further improvement that the high-frequency data acquisition unit is connected with the dynamic pressure sensor through a sensor shielding cable.
The invention is further improved in that the data analysis processor is connected with the high-frequency data collector through a USB data line.
A further development of the invention is that the dynamic pressure sensor is a piezoresistive or piezoelectric type dynamic pressure sensor.
The invention has the further improvement that the high-frequency data acquisition unit has the function of multi-channel parallel acquisition and can provide power for the dynamic pressure sensor.
The invention has the further improvement that the data analysis processor is provided with combustion stability state monitoring and diagnosing software, can control the sampling frequency of the high-frequency data acquisition device, has the capability of carrying out real-time fast Fourier transform, short-time Fourier transform and pressure pulsation amplitude growth rate calculation and analysis on the combustion pressure pulsation signals obtained by measurement, and displays the combustion pressure pulsation measurement and analysis results in real time.
The invention is further improved in that the sensor cooling structure consists of a cooling structure main body, a cooling water input pipe, a cooling water output pipe and a semi-infinite damping pipe; the center of the cooling structure main body is provided with a circular tube-shaped pressure sensing containing cavity, two rectangular clapboards are arranged inside the cooling structure main body to divide the cooling structure main body into a left half area and a right half area, the bottoms of the left half area and the right half area are communicated, cooling water can enter from a cooling water input pipe, then flows downwards to the bottom of the left half area, then enters the bottom of the right half area through a bottom communicating flow path, and then flows upwards through a cooling water output pipe to flow out of the sensor cooling structure; a semi-infinite damping tube is arranged at the mounting position of a dynamic pressure sensor of the sensor cooling structure and is communicated with a circular tube-shaped pressure sensing cavity at the center of a cooling structure main body.
The invention is further improved in that the cooling structure main body is of a cylindrical structure.
The invention has the further improvement that when the cooling device works, cooling circulating water enters the left half area of the sensor cooling structure from the cooling water input pipe, enters the right half area of the sensor cooling structure through the communication channel at the bottom of the sensor cooling structure, and then flows out of the sensor cooling structure through the cooling water output pipe; high-temperature flue gas in a tested combustion chamber passes through a circular tube-shaped pressure sensing cavity in the center of a sensor cooling structure, is cooled by cooling water and then reaches the measuring end face of a dynamic pressure sensor, and then enters a semi-infinite damping tube; the dynamic pressure sensor converts sensed pressure pulsation signals into electric signals and then transmits the electric signals to the high-frequency data acquisition unit, the high-frequency data acquisition unit acquires the sensor electric signals at a high speed and then converts the electric signals into digital signals, the digital signals are transmitted to the data analysis processor, the data analysis processor stores the obtained pressure pulsation digital signals in real time, fast Fourier transform, short Fourier transform and pressure pulsation amplitude growth rate calculation are carried out on the pressure pulsation digital signals, the combustion stability state is diagnosed according to the pressure pulsation amplitude and the amplitude growth rate, and calculation and diagnosis results are displayed and stored in real time.
The invention has at least the following beneficial technical effects:
the invention provides a combustion stability state monitoring and diagnosing system of a gas turbine, which adopts fast Fourier transform and short-time Fourier transform to calculate and obtain the frequency and the amplitude of combustion pressure pulsation, provides an evaluation index of the amplitude increase rate of the combustion pressure pulsation, analyzes the increase amount of the combustion pressure pulsation amplitude within 1s, and prevents the combustion pressure pulsation and combustion chamber components from being damaged due to large pressure pulsation when the combustion pressure pulsation amplitude does not touch an unstable combustion alarm value or a trip value and the combustion pressure pulsation amplitude increase rate is abnormal, thereby predicting the occurrence of unstable combustion in advance, giving measures for inhibiting the combustion pressure pulsation in time and preventing the occurrence of the situation that the combustion pressure pulsation jumps and the combustion chamber components are damaged due to large pressure pulsation. In addition, the invention designs a sensor cooling structure, and adopts cooling circulating water to cool the dynamic pressure sensor, so that the dynamic pressure sensor can be ensured to work in an allowable working temperature range all the time, and the dynamic pressure sensor is prevented from being burnt by high-temperature smoke; meanwhile, the cooling structure of the sensor has the cooling effect on high-temperature smoke stagnant in the pressure sensing cavity, so that the length of the pressure sensing cavity can be greatly shortened, the attenuation influence of the pressure sensing cavity on combustion pressure pulsation is further reduced, and the measurement accuracy of the combustion pressure pulsation is improved; in addition, the semi-infinite damping tube is adopted on the cooling structure of the sensor, so that pressure pulsation transmitted into the pressure sensing cavity can be transmitted forwards without reflection all the time, the phenomenon of standing wave resonance generated by combustion pressure pulsation in the pressure sensing cavity is avoided, and false frequency and amplitude signals of the measurement result of the combustion pressure pulsation can be effectively prevented.
Drawings
FIG. 1 is a schematic diagram of an embodiment of a combustion stability status monitoring and diagnosing system for a gas turbine.
Description of reference numerals:
1. a sensor cooling structure; 2. a dynamic pressure sensor; 3. a high-frequency data acquisition unit; 4. a data analysis processor; 5. a combustion chamber; 6. a cooling water input pipe; 7. a cooling water output pipe; 8. cooling the structural body; 9. semi-infinite damping tube.
Detailed Description
The following detailed description of specific embodiments of the invention refers to the accompanying drawings.
Referring to fig. 1, a combustion stability state monitoring and diagnosing system of a gas turbine according to the present embodiment mainly includes: the device comprises a sensor cooling structure 1, a dynamic pressure sensor 2, a high-frequency data collector 3 and a data analysis processor 4.
The sensor cooling structure 1 mainly comprises a cooling structure main body 8, a cooling water input pipe 6, a cooling water output pipe 7 and a semi-infinite damping pipe 9.
The dynamic pressure sensor 2 adopts a piezoresistive high-temperature dynamic pressure sensor;
the high-frequency data collector 3 adopts an 8-channel parallel collector, and the highest sampling frequency is 200 kHz.
The data analysis processor 4 is a notebook computer with a 16GB hard disk as a memory of 1TB, the computer is provided with combustion stability state monitoring and diagnosing software, test parameters such as sampling frequency, measuring range and sensitivity of a dynamic sensor of the high-frequency data collector 3 can be set, meanwhile, the data analysis processor has the capability of carrying out real-time fast Fourier transform, short-time Fourier transform and pressure pulsation amplitude growth rate calculation and analysis on a measuring signal, and displays and stores a measuring and analyzing result in real time.
The combustion chamber 5 is a gas turbine single-tube combustion chamber.
A cooling structure main body 8 in the sensor cooling structure 1 is of a cylindrical structure, and a circular tube-shaped pressure sensing cavity is designed in the center. For preventing that the cooling water directly from the cooling water input tube gets into the back and directly flows out from the cooling water output tube, be provided with two rectangle baffles in cooling structure main part 8 inside, with cooling structure main part 8 halving about two half regions, about the regional bottom UNICOM of two half regions, cooling water gets into the back from cooling water input tube 6, down flows to the bottom in left half region earlier, then gets into the bottom in right half region through bottom UNICOM flow path, upward flows through cooling water output tube 7 and flows out sensor cooling structure 1 again. In order to prevent the pressure pulsation from forming sound pressure standing waves in the circular tube-shaped pressure sensing cavity in the center of the cooling structure main body 8 and causing measurement results to generate false pressure pulsation frequency and amplitude signals, a semi-infinite damping tube 9 is arranged at the mounting position of the dynamic pressure sensor of the sensor cooling structure 1, and the semi-infinite damping tube 9 is communicated with the circular tube-shaped pressure sensing cavity in the center of the cooling structure main body 8.
The semi-infinite damping tube 9 in the sensor cooling structure 1 has an inner diameter of 4mm and a length of 20 m.
The connection mode of the combustion stability state monitoring and diagnosing system of the gas turbine is as follows: the sensor cooling structure 1 and the inner wall of a pressure measuring hole of a tested object combustion chamber 5 are arranged in parallel and level, the dynamic pressure sensor 2 is arranged on the upper end surface of the sensor cooling structure 1, the high-frequency data acquisition device 3 is connected with the dynamic pressure sensor 2 through a sensor shielding cable, and the data analysis processor 4 is connected with the high-frequency data acquisition device 3 through a USB data line.
The working process of the combustion stability state monitoring and diagnosing system of the gas turbine is as follows:
1) the components of the combustion stability state monitoring and diagnosing system of the gas turbine are connected according to the embodiment, and the tightness of the installation position of the dynamic pressure sensor 2 and the sensor cooling structure 1 is checked.
2) And (4) turning on power switches of the data analysis processor 4 and the high-frequency data collector 3, and checking the reliability of signal transmission of the combustion stability state monitoring and diagnosing system of the gas turbine.
3) And starting a cooling circulating water system, wherein cooling circulating water enters the left half area of the sensor cooling structure 1 from the cooling water input pipe 6, enters the right half area of the sensor cooling structure 1 through a communication channel at the bottom of the sensor cooling structure 1, and then flows out of the sensor cooling structure 1 through the cooling water output pipe 7.
4) The gas turbine is ignited and started, the gas turbine stably runs under the test working condition, high-temperature smoke in the tested combustion chamber 5 passes through the circular tube-shaped pressure sensing cavity in the center of the sensor cooling structure 1, is cooled by cooling water and then reaches the measuring end face of the dynamic pressure sensor 2, and then enters the semi-infinite damping tube 9. Because the end of the semi-infinite damping tube 9 is sealed, the flow velocity of the high-temperature smoke in the circular tube-shaped pressure sensing cavity and the semi-infinite damping tube 9 is very small and is close to a stagnation state, so that the heat exchange between the high-temperature smoke in the sensor cooling structure and the high-temperature smoke in the combustion chamber 5 is greatly reduced, the cooled smoke in the circular tube-shaped pressure sensing cavity is kept at a lower temperature state all the time, the dynamic pressure sensor 2 can be effectively isolated from being in direct contact with the high-temperature smoke in the combustion chamber, and the effect of well protecting the dynamic pressure sensor 2 is achieved.
5) The dynamic pressure sensor 2 converts the combustion pressure pulsation sensed in real time into a voltage signal, and then the voltage signal is transmitted to the high-frequency data acquisition unit 3 through the sensor shielding cable, the voltage signal is converted into a digital signal after the high-frequency data acquisition unit 3 acquires the voltage signal at a high speed, and the digital signal is transmitted to the data analysis processor 4 through the USB data line.
6) The data analysis processor 4 stores the obtained pressure pulsation digital signals in real time, carries out fast Fourier transform, short-time Fourier transform and pressure pulsation amplitude increase rate calculation on the pressure pulsation digital signals, divides the Fourier transform result into three frequency band intervals of a low frequency band (10-100 Hz), a middle frequency band (100-300 Hz) and a high frequency band (300-1000 Hz), and can judge that the combustion instability phenomenon occurs in the combustion chamber when the pressure pulsation amplitudes of the low frequency band, the middle frequency band and the high frequency band respectively last for 10s and are higher than 40kPa, 32kPa and 10kPa, or when the pressure pulsation amplitude increase rates of the low frequency band, the middle frequency band and the high frequency band respectively last for 30s and are higher than 50Pa/s, 30Pa/s and 10Pa/s, and simultaneously displays and stores the calculation and diagnosis results in real time.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. The present invention is not limited to the above-described embodiments, which are described in the specification and illustrated only for illustrating the principle of the present invention, but various changes and modifications may be made within the scope of the present invention as claimed without departing from the spirit and scope of the present invention.
Claims (9)
1. The combustion stability state monitoring and diagnosing system of the gas turbine is characterized by comprising a sensor cooling structure (1), a dynamic pressure sensor (2), a high-frequency data collector (3) and a data analysis processor (4); the sensor cooling structure (1) and the inner wall of a pressure measuring hole of a combustion chamber (5) of a tested object are arranged in parallel, the dynamic pressure sensor (2) is arranged on the upper end face of the sensor cooling structure (1), the high-frequency data collector (3) is connected with the dynamic pressure sensor (2), and the data analysis processor (4) is connected with the high-frequency data collector (3).
2. The combustion stability state monitoring and diagnosing system of the gas turbine as claimed in claim 1, wherein the high frequency data collector (3) is connected with the dynamic pressure sensor (2) through a sensor shielded cable.
3. The combustion stability state monitoring and diagnosing system of a gas turbine as claimed in claim 1, wherein the data analysis processor (4) is connected with the high frequency data collector (3) through a USB data line.
4. The combustion stability status monitoring and diagnosing system of a gas turbine as claimed in claim 1, wherein the dynamic pressure sensor (2) is a piezoresistive or piezoelectric type dynamic pressure sensor.
5. The combustion stability state monitoring and diagnosing system of the gas turbine as claimed in claim 1, wherein the high frequency data collector (3) has a function of multi-channel parallel collection and can provide power for the dynamic pressure sensor (2).
6. The combustion stability state monitoring and diagnosing system of the gas turbine as claimed in claim 1, wherein the data analysis processor (4) is installed with combustion stability state monitoring and diagnosing software, can control the sampling frequency of the high-frequency data collector (3), has the capability of performing real-time fast fourier transform, short-time fourier transform and pressure pulsation amplitude growth rate calculation and analysis on the combustion pressure pulsation signal obtained by measurement, and displays the combustion pressure pulsation measurement and analysis results in real time.
7. The combustion stability state monitoring and diagnosing system of a gas turbine as claimed in claim 1, wherein the sensor cooling structure (1) is composed of a cooling structure body (8), a cooling water input pipe (6), a cooling water output pipe (7) and a semi-infinite damping pipe (9); a circular tube-shaped pressure sensing cavity is arranged in the center of the cooling structure main body (8), two rectangular partition plates are arranged inside the cooling structure main body (8) to divide the cooling structure main body (8) into a left half area and a right half area, the bottoms of the left half area and the right half area are communicated, cooling water can flow downwards to the bottom of the left half area after entering from a cooling water input pipe (6), then flow into the bottom of the right half area through a bottom communication flow path, and then flow upwards to flow through a cooling water output pipe (7) to flow out of the sensor cooling structure (1); a semi-infinite damping tube (9) is arranged at the mounting position of a dynamic pressure sensor (2) of a sensor cooling structure (1), and the semi-infinite damping tube (9) is communicated with a circular tube-shaped pressure sensing cavity at the center of a cooling structure main body (8).
8. The combustion stability state monitoring and diagnosing system of a gas turbine as claimed in claim 7, wherein the cooling structure body (8) is a cylindrical structure.
9. The combustion stability state monitoring and diagnosing system of a gas turbine as claimed in claim 7, wherein, in operation, the cooling circulation water enters the left half area of the sensor cooling structure (1) from the cooling water input pipe (6), enters the right half area of the sensor cooling structure (1) through the communication channel at the bottom of the sensor cooling structure (1), and then flows out of the sensor cooling structure (1) through the cooling water output pipe (7); high-temperature flue gas in a tested combustion chamber (5) passes through a circular tube-shaped pressure sensing cavity in the center of a sensor cooling structure (1), is cooled by cooling water, reaches the measuring end face of a dynamic pressure sensor (2), and then enters a semi-infinite damping tube (9); the dynamic pressure sensor (2) converts a sensed pressure pulsation signal into an electric signal and then transmits the electric signal to the high-frequency data acquisition unit (3), the high-frequency data acquisition unit (3) acquires the electric signal of the sensor at a high speed and then converts the electric signal into a digital signal, the digital signal is transmitted to the data analysis processor (4), the data analysis processor (4) stores the obtained pressure pulsation digital signal in real time, and performs fast Fourier transform, short-time Fourier transform and pressure pulsation amplitude growth rate calculation on the pressure pulsation digital signal, diagnoses the combustion stability state according to the pressure pulsation amplitude and the amplitude growth rate, and displays and stores the calculation and diagnosis result in real time.
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| CN202011314042.4A CN112326257A (en) | 2020-11-21 | 2020-11-21 | Combustion stability state monitoring and diagnosing system of gas turbine |
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| CN202011314042.4A CN112326257A (en) | 2020-11-21 | 2020-11-21 | Combustion stability state monitoring and diagnosing system of gas turbine |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113267291A (en) * | 2021-05-28 | 2021-08-17 | 清华大学 | Early warning monitoring method and device for combustion oscillation phenomenon |
| CN113588280A (en) * | 2021-08-27 | 2021-11-02 | 华能国际电力股份有限公司 | System suitable for monitoring combustion state parameters of gas turbine |
| 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 |
| CN114109814A (en) * | 2021-11-05 | 2022-03-01 | 中国航发西安动力控制科技有限公司 | Flow pulsation monitoring system and method for aviation electric fuel pump |
| CN114811650A (en) * | 2022-06-01 | 2022-07-29 | 清华大学 | Electric heating stable combustion device and method and storage medium |
| CN115751379A (en) * | 2022-09-27 | 2023-03-07 | 南京航空航天大学 | Quarter wave tube for suppressing combustion instability and control method thereof |
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2020
- 2020-11-21 CN CN202011314042.4A patent/CN112326257A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113267291A (en) * | 2021-05-28 | 2021-08-17 | 清华大学 | Early warning monitoring method and device for combustion oscillation phenomenon |
| CN113588280A (en) * | 2021-08-27 | 2021-11-02 | 华能国际电力股份有限公司 | System suitable for monitoring combustion state parameters of gas turbine |
| CN114109814A (en) * | 2021-11-05 | 2022-03-01 | 中国航发西安动力控制科技有限公司 | Flow pulsation monitoring system and method for aviation electric fuel pump |
| CN114109814B (en) * | 2021-11-05 | 2023-10-20 | 中国航发西安动力控制科技有限公司 | Flow pulsation monitoring system and method for aviation electric fuel pump |
| 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 |
| CN114811650A (en) * | 2022-06-01 | 2022-07-29 | 清华大学 | Electric heating stable combustion device and method and storage medium |
| CN115751379A (en) * | 2022-09-27 | 2023-03-07 | 南京航空航天大学 | Quarter wave tube for suppressing combustion instability and control method thereof |
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