KR20170066090A - Device for diagnosing the combustion state of a gas turbine by using an ultrasonic wave - Google Patents

Device for diagnosing the combustion state of a gas turbine by using an ultrasonic wave Download PDF

Info

Publication number
KR20170066090A
KR20170066090A KR1020150172675A KR20150172675A KR20170066090A KR 20170066090 A KR20170066090 A KR 20170066090A KR 1020150172675 A KR1020150172675 A KR 1020150172675A KR 20150172675 A KR20150172675 A KR 20150172675A KR 20170066090 A KR20170066090 A KR 20170066090A
Authority
KR
South Korea
Prior art keywords
ultrasonic
combustor
flame
combustion
gas turbine
Prior art date
Application number
KR1020150172675A
Other languages
Korean (ko)
Other versions
KR101804191B1 (en
Inventor
이민철
Original Assignee
인천대학교 산학협력단
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 인천대학교 산학협력단 filed Critical 인천대학교 산학협력단
Priority to KR1020150172675A priority Critical patent/KR101804191B1/en
Priority to JP2016517513A priority patent/JP6308599B2/en
Priority to PCT/KR2016/000599 priority patent/WO2017094965A1/en
Publication of KR20170066090A publication Critical patent/KR20170066090A/en
Application granted granted Critical
Publication of KR101804191B1 publication Critical patent/KR101804191B1/en

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K11/00—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00
    • G01K11/22—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using measurement of acoustic effects
    • G01K11/24—Measuring temperature based upon physical or chemical changes not covered by groups G01K3/00, G01K5/00, G01K7/00 or G01K9/00 using measurement of acoustic effects of the velocity of propagation of sound
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics

Abstract

An apparatus for diagnosing a gas turbine combustion state using ultrasonic waves is disclosed. An apparatus for diagnosing a gas turbine combustion state using ultrasonic waves according to the present invention comprises: a combustion diagnosis tube having an opening at one end thereof, communicating with an internal space of a combustor for a gas turbine, and the other end protruding outward; An ultrasonic transmitter provided at the other end of the combustion diagnosis tube to generate a transmission ultrasonic wave toward the combustor through the combustion diagnosis tube; An ultrasonic receiver provided in the combustion diagnosis tube for receiving the transmission ultrasonic wave to generate a first reception signal and receiving a reflected wave returned by the inner reflection surface of the combustor among the transmission ultrasonic waves to generate a second reception signal; And a control unit connected to the ultrasonic transmitter and the ultrasonic receiver for controlling the flame temperature (T) in the combustor based on the first and second reception signals and a separation distance (L) between the ultrasonic receiver and the reflection surface. And a control unit. According to the present invention, there is provided an ultrasonic transmitter for directing a transmitted ultrasonic wave in a direct direction of a flame in a combustor, and an algorithm for utilizing a maximum of two ultrasonic receivers for receiving a reflected ultrasonic wave and a reflected wave passing through a flame in the combustor, respectively It is possible to more directly measure the flame temperature in the combustor, thereby increasing the precision or accuracy of the temperature measurement.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a gas turbine combustion state diagnostic apparatus using an ultrasonic wave,

The present invention relates to an apparatus for diagnosing a gas turbine combustion state using ultrasonic waves, and more particularly, to an apparatus for diagnosing a gas turbine combustion state using ultrasound, To a gas turbine combustion condition diagnostic apparatus.

The gas turbine power generation system is capable of effectively preventing combustion of the combustor due to unstable combustion in the gas turbine combustor through precise monitoring of the flame state of the fuel injected and burned from the nozzle, Development is underway.

In order to monitor or control the flame condition of the fuel, a dynamic pressure sensor is mounted on the gas turbine combustor side to analyze the magnitude and frequency of the dynamic pressure. When a dynamic pressure signal over a predetermined range is detected, And measures are to be carried out step by step.

However, external factors causing combustion instability may be various causes such as fuel quality imbalance, driver malfunction, atmospheric temperature and humidity change, and aging of the equipment, and it is difficult to accurately diagnose the instability of the combustion state merely by monitoring the combustion dynamic pressure As a result, various sensors are being added to the gas turbine combustion condition diagnosis apparatus in addition to the combustion condition monitoring through the dynamic pressure sensor.

In addition, as the technology of Integrated Gasification Combined Cycle (IGCC) is highlighted, syngas is supplied to the gas turbine power generation system for combustion. In this case, the fluctuation of the shear pressure occurs, causing unstable combustion, The necessity of combustion diagnosis is increasing.

Recently, various power generation fuels such as Biogas, DME (Dimethyl Ether) and SNG (Synthetic Natural Gas) and renewable energy have been applied to gas turbine power generation systems. Since the combustion phenomenon greatly varies depending on the characteristics of each fuel, Accurate combustion diagnosis is required.

In particular, since the content of harmful substances such as NO x and CO in the exhaust gas varies depending on the flame temperature in the combustor, precise measurement of the flame temperature in the combustor has an important meaning as a criterion for determining whether the fuel is incomplete or not .

Of these prior arts, U.S. Patent Publication No. 2008-0243352 discloses that the combustion state can be monitored by a gas turbine comprising several sensors designed to measure different performance-related parameters of the turbine, generator, and ambient environment . Wherein the groups of surplus temperature sensors monitor the ambient temperature around the gas turbine, the compressor discharge temperature, the turbine exhaust gas temperature, and the temperature measurements of the gas stream passing through the gas turbine, respectively, and the pressure of the gas stream passing through the gas turbine Groups of surplus pressure sensors to measure will monitor the static and dynamic pressure levels at different locations, i.e., compressor inlet and outlet and turbine exhaust, respectively. In addition, a group of surplus humidity sensors, for example a group of wet bulb and dry bulb thermometers, measure the ambient humidity in the inlet duct of the compressor, the groups of surplus sensors include flow sensors that sense various parameters related to the operation of the gas turbine, , A flame detector sensor, a valve position sensor, a guide blade angle sensor, and the like.

And U.S. Patent No. 7853433 of the prior art teaches sampling of combustor thermoacoustic oscillations indicative of combustion conditions with sensors such as dynamic pressure sensors, accelerometers, high temperature microphones, optical sensors and / or ion sensors And subsequent detection and classification of combustion anomalies by wavelet analysis.

U.S. Patent Publication No. 2012-0150413 describes a technique for determining an upstream bulk temperature in one or more combustors of an engine using acoustic pyrometry in a gas turbine exhaust system.

These prior art teach techniques for an integrated gas turbine monitoring and control system to share common controls with common sensors to detect bursts or indications of combustor failures or defects that can occur extensively during combustion.

However, in relation to the measurement of flame temperature in a combustor, rather than directly calculating the flame temperature in the actual combustor, it is an indirect method of calculating the flame temperature by mounting a plurality of sensors such as an acoustic pyrometer device on the outside of the combustor housing. There is a problem that it is difficult to install and maintain the sensor because the sensor is complicatedly mounted.

U.S. Published Patent Application No. 2008-0243352 (published on October 2, 2008) United States Patent No. 7853433 (public announcement date: December 14, 2010) US Published Patent Application No. 2012-0150413 (Published on June 14, 2012)

It is an object of the present invention to provide a flame temperature measurement method and a flame temperature measurement method which can achieve a more accurate flame temperature measurement by calculating a flame temperature in a combustor having important meaning as a criterion for determining incomplete combustion of a fuel, And to provide an apparatus for diagnosing a gas turbine combustion state using an ultrasonic wave which can facilitate installation and maintenance.

The above object is achieved by a combustion diagnosis device comprising: a combustion diagnosis tube having an opening at one end and communicating with an inner space of a combustor for a gas turbine, the other end protruding outward; An ultrasonic transmitter provided at the other end of the combustion diagnosis tube to generate a transmission ultrasonic wave toward the combustor through the combustion diagnosis tube; An ultrasonic receiver provided in the combustion diagnosis tube for receiving the transmission ultrasonic wave to generate a first reception signal and receiving a reflected wave returned by the inner reflection surface of the combustor among the transmission ultrasonic waves to generate a second reception signal; And a control unit connected to the ultrasonic transmitter and the ultrasonic receiver for controlling the flame temperature (T) in the combustor based on the first and second reception signals and a separation distance (L) between the ultrasonic receiver and the reflection surface. And a gas turbine combustion state diagnostic apparatus using the ultrasonic wave.

The control unit calculates a delay time? T from the reception of the transmission ultrasonic wave to the reception of the reflected wave based on the first and second reception signals and calculates a delay time? T of the ultrasonic waves in the combustor by the speed expression C flame = 2L / After calculating the velocity (C flame ), the relationship between the ultrasonic velocity and the temperature

Figure pat00001
The flame temperature T can be calculated.

The ultrasonic receiver includes a first ultrasonic receiver inside the combustion diagnosis tube and a second ultrasonic receiver spaced apart toward the combustor, and sequentially receives the transmission ultrasonic waves to generate a first reception signal and a second reception signal, And generates the second -2 reception signal and the 1-2 reception signal by sequentially receiving the reflected waves returned by the inner reflection surface of the combustor among the transmission ultrasonic waves, A distance between the first ultrasonic receiver and the second ultrasonic receiver, a distance between the first ultrasonic receiver and the second ultrasonic receiver, a distance between the first ultrasonic receiver and the second ultrasonic receiver, And a control unit for measuring the flame temperature T in the combustor based on a distance L3 between the opening and the reflecting surface of the combustor.

Wherein, the delay △ t 1 based on the first received signal 1-1,2-1, the 2-1, 2-2 delay △ t 2 on the basis of the received signal, the second- on the basis of the received signal 2,1-2 calculating the delay △ t 3, respectively, and the expression rate C 1 = L 1 / △ the speed (C 1) of the transmission ultrasonic waves by t 1, the speed flame formula C = 2 (L 2 + L 3) / △ ultrasonic velocity (C flame) of within the combustor by t 2, the speed formula C 2 = by L 1 / △ t 3 respectively, the rate (C 2) of the reflected wave After calculation, the relationship between the ultrasonic velocity and the temperature

Figure pat00002
The flame temperature T can be calculated.

Wherein, in order to increase the accuracy of the flame temperature (T), the second of the transmission ultrasonic delay △ t 4 of the spacing distance (L2) up to the aperture in the ultrasonic receiver, the speed of the transmission ultrasonic waves (C 1 ), and the delay time? T 5 of the reflected wave with respect to the separation distance (L2) from the opening to the second ultrasonic receiver is calculated on the basis of the velocity (C 2 ) of the reflected wave then, the flame rate equation C = 2L 3 / by (△ t 2 - - △ t 4 △ t 5) can calculate the ultrasonic velocity (C flame) of within the combustor.

Wherein the control unit, "△ t 3 generated by the 'said delay △ t 3, a rate equation C 1 = L 1 / △ t 3 on the basis of the speed (C 1) of the transmission ultrasonic waves generated by the control unit The error of the measurement can be generated.

The control unit may generate a carbon monoxide (CO) generation danger signal when the calculated flame temperature (T) is 1300 ° C or lower.

The control unit may generate a nitrogen oxide (NO x ) generation danger signal when the calculated flame temperature (T) is 1600 ° C or more.

According to the present invention, there is provided an ultrasonic transmitter for directing a transmitted ultrasonic wave in a direct direction of a flame in a combustor, and an algorithm for utilizing a maximum of two ultrasonic receivers for receiving a reflected ultrasonic wave and a reflected wave passing through a flame in the combustor, respectively The flame temperature in the combustor can be more directly measured, so that it is possible to provide an apparatus for diagnosing a gas turbine combustion state using ultrasound which can increase accuracy or accuracy of temperature measurement.

Based on the precise and precise measurement of the emission characteristics of the harmful substances per fuel (including new fuel) according to the flame temperature and the combustion temperature, it is possible to accurately judge and cope with the incomplete combustion of the fuel in real time, And the harmful exhaust gas can be reduced or the like.

In addition, unlike the prior art, it is possible to simplify the number of components and structure of the apparatus for flame temperature measurement so that the installation and maintenance can be facilitated, and the combustion diagnosis tube It is possible to provide an apparatus for diagnosing a gas turbine combustion state using an ultrasonic wave which can be easily applied to a gas turbine.

1 is a perspective view illustrating an entire gas turbine to which an apparatus for diagnosing a gas turbine combustion state using ultrasonic waves according to the present invention is applied.
FIG. 2 is a view for explaining the operation of the combustion condition diagnosis apparatus according to the first embodiment of the present invention by enlarging the area shown in FIG.
FIG. 3 is a view for explaining the operation of the combustion condition diagnosis apparatus according to the second embodiment of the present invention, by enlarging the area shown in FIG.
4 is a diagram showing a relationship between a received signal and a separation distance according to the operation of FIG.
5 is a graph showing the CO emission characteristic according to the flame temperature in a combustor for a gas turbine.
6 is a graph showing NO x emission characteristics according to the flame temperature in a combustor for a gas turbine.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In the following description of the present invention, the well-known functions or constructions are not described in order to simplify the gist of the present invention.

FIG. 1 is a perspective view showing the entirety of a gas turbine to which an apparatus for diagnosing a gas turbine combustion state using ultrasonic waves according to the present invention is applied. FIG. 2 is an enlarged view of the gas turbine according to the first embodiment of the present invention. FIG. 3 is a view for explaining the operation of the combustion state diagnosis apparatus according to the second embodiment of the present invention by enlarging the area shown in FIG. 1, and FIG. 4 is a cross- FIG. 5 is a graph showing a CO emission characteristic according to a flame temperature in a combustor for a gas turbine, and FIG. 6 is a graph showing a relationship between the NO emission according to the flame temperature in the combustor for a gas turbine x emission characteristics.

Before explaining the present invention, the gas turbine 10 will be briefly described as including a compressor 12, a combustor 20, a turbine 14, an exhaust port 16, etc., as shown in FIG. 1 And the operation of the gas turbine 10 is such that the air compressed through the compressor 12 is introduced into the combustor 20 and burned together with the injected fuel and the generated high temperature and high pressure gas flows rapidly, The exhaust gas is discharged to the outside through the exhaust port 16 after rotating the exhaust manifold 14.

An apparatus 100 for diagnosing a gas turbine combustion state using ultrasonic waves according to the present invention mounted on the gas turbine 10 is provided at one side of the combustor 20 for diagnosing a flame condition in the combustor 20 for a gas turbine do.

The gas turbine combustion condition diagnosis apparatus 100 may include various types of diagnostic apparatuses such as a pressure sensor (dynamic pressure sensor, microphone or the like) for measuring the pressure in the combustor 20, a combustion diagnosis tube 110, And a device for receiving a radical signal from the self-emission signal of the flame propagated to the side of the flame.

An apparatus 100 for diagnosing a gas turbine combustion state using an ultrasonic wave according to the present invention includes a combustion diagnosis tube 110, an ultrasonic transmitter 120, and an ultrasonic transmitter 120 for precisely and accurately measuring a flame temperature T in a combustor 20 of a gas turbine, An ultrasonic receiver 130, a controller 140, and the like.

Hereinafter, each configuration of the above-described combustion condition diagnosis apparatus 100 will be described in detail.

The combustion diagnosis tube 110 is a component having a space in which the above-described diagnostic devices are mounted. The combustion diagnosis tube 110 has a long pipe shape, and has an opening 110b at one end thereof, communicates with an inner space of the combustor 20, And the other end is protruded outward.

In this way, the combustion diagnosis tube 110 is manufactured in a pipe shape protruding outwardly from the combustor 20, so that the diagnostic devices installed therein are stably driven despite the high-temperature and high-pressure flames generated in the combustor 20 And the flame condition basic information such as a self-emission signal or an acoustic wave signal generated during fuel combustion and a reflected wave RU to be described later can be smoothly introduced into the combustion diagnosis tube 110.

The combustion diagnosis tube 110 according to the first and second embodiments of the present invention is formed such that its longitudinal direction is perpendicular to the reflecting surface 20a of the combustor to be described later, So that the transmitted ultrasonic wave SU emitted from the ultrasonic transmitter 120 is reflected 180 degrees through the reflecting surface 20a of the combustor and then propagated smoothly toward the inside of the combustion diagnosis tube 110 in the form of a reflected wave RU . Here, the combustor reflection surface 20a specifies the surface on which the transmission ultrasonic wave SU is reflected from the inner surface of the combustor 20, and does not mean a surface subjected to special processing for reflection.

Although not shown in the drawing, a static charge valve (not shown) may be installed at a portion where the combustion diagnosis tube 110 and the combustor 20 are connected to each other. So that the combustion condition diagnosis apparatus 100 can be safely detached from the combustor 20 after the static charge valve is locked, if necessary.

The ultrasonic transmitter 120 is provided at the other end of the combustion diagnosis tube 110 (on the upper end side in the drawing) The direction of the ultrasonic transmitter 120 is set so as to face the reflecting surface 20a of the combustor so that the transmitting ultrasonic wave SU can be transmitted toward the reflecting surface 20a.

Accordingly, the transmitted ultrasonic wave (SU) transmitted from the ultrasonic transmitter 120 is propagated along the inner space of the combustion diagnosis tube 110, and a part thereof is received by the ultrasonic receiver 130 to be described later, And then propagates to the inside of the combustion diagnosis tube 110 again in the form of a reflected wave RU returned by the reflecting surface 20a of the combustor.

Since the specific structure and configuration of the ultrasonic transmitter 120 and the principle of ultrasonic wave generation are already known, a detailed description thereof will be omitted. However, in order to understand the contents described below, the ultrasonic velocity (C, In general, it can be expressed by the relation of C = 331.6 + 0.6 * t ° C (m / s) and it is proportional to the temperature (t ° C), so if you know the ultrasonic velocity (C) I will only mention that I can roughly judge.

The ultrasonic transmitter 120 according to the first and second embodiments of the present invention uses an ultrasonic transmitter 120 for generating a transmission ultrasonic wave SU in a band of approximately 30 kHz to 100 kHz, The frequency band can be arbitrarily selected depending on the type, the type and the manner of the gas turbine 10, and the combustion environment. However, it is preferable that the ultrasonic wave of a high frequency band, which has a relatively small influence on the combustion environment and has excellent analytical ability, is used for measuring the flame temperature (T) in the combustor 20.

2 and 3, the ultrasonic transmitter 120 according to the first and second embodiments of the present invention is slightly biased toward the side of the combustion diagnosis tube 110. [

Even if the ultrasonic transmitter 120 is slightly biased toward the side of the combustion diagnosis tube 110, the ultrasonic transmitter 120 can transmit the ultrasonic wave from the ultrasonic transmitter 120, The transmitted ultrasonic wave SU is propagated along the combustion diagnosis tube 110 and has a linearity so that it does not greatly affect the measurement of the flame temperature T. [

The ultrasonic transmitter 120 is disposed at the center of the combustion diagnosis tube 110 so as to directly face the reflecting surface 20a of the combustor within a range where there is no interference with other diagnostic devices, It is preferable for the reflected flame RU to be smoothly propagated toward the combustion diagnosis tube 110 for more accurate flame temperature T measurement.

The ultrasonic transmitter 120 transmits ultrasonic waves SU at a predetermined interval through a control unit 140 to be described later in order to allow the combustion state diagnosis apparatus 100 to measure the flame temperature T at predetermined time intervals in real time. .

The ultrasonic receiver 130 is an apparatus for receiving an ultrasonic wave to generate a reception signal, that is, an electric signal S in the form of pulse wave (or analog wave) and time information t at the time of reception, 110, and is installed at a predetermined distance from the ultrasonic receiver 130 and the combustor 20.

The ultrasonic receiver 130 according to the present invention may be configured to receive both the ultrasonic wave SU and the reflected wave RU from both the ultrasonic transmitter 120 and the reflecting surface 20a of the combustor, . The basic structure and configuration of the ultrasound receiver 130, the principle of reception signal generation, and the like are well-known technologies, and thus a detailed description thereof will be omitted.

2, the ultrasonic receiver 130 according to the first embodiment of the present invention is provided with one inside the combustion diagnosis tube 110 to receive a transmission ultrasonic wave SU and generate a first reception signal S1 generate -t 1), and thereby produce a second received signal (S1-t 2) by receiving the reflected wave (RU) returned by a combustor inner reflecting surface (20a) of the transmitted ultrasound (SU).

That is, the ultrasound transmitter 120 receives the transmitted ultrasonic wave SU through a receiver on one side oriented in the corresponding direction to generate an electric signal S1 in pulse wave form and time information t 1 at that time , Receives a reflected wave RU propagating from the reflection surface 20a of the combustor through a receiver on the other side that is oriented in the corresponding direction and outputs the pulse signal S 1 and the time information t 2 at that time .

3, the ultrasonic receiver 130 according to the second embodiment of the present invention includes two ultrasonic transmitters 120 separated from each other in the longitudinal direction within the combustion diagnosis tube 110, And a second ultrasonic receiver 134 adjacent to the combustor 20 side. At this time, each of the first and second ultrasonic receivers 132 and 134 is formed as a bi-directional receiver in which both the ultrasonic transmitter 120 and the reflecting surface 20a of the combustor are directed.

The first ultrasonic wave receiver 132 and the second ultrasonic receiver 134, the ultrasonic transmitter 120 each sequentially received by the first-first received signal (S11 t-1), the transmission transmitting ultrasound (SU) from (the 1 back by the ultrasonic receiver 132) and the second-first reception signal (S21-t 2) (the second ultrasonic receiver 134, and to generate), the transmitting ultrasound (combustor inner reflecting surface (20a) of the SU) reflected wave comes (RU) to successively receive each the second-second reception signal (S22 t-3) (a second ultrasonic receiver 134) and the first-second received signal (S12 t-4) (a first ultrasonic receiver ( 132).

The control unit 140 is electrically connected to various diagnostic apparatuses other than the ultrasonic transmitter 120 and the ultrasonic receiver 130 described above and receives signals or information generated therefrom and receives control signals And stores the received signal or information as needed, or displays the signal on a screen.

The control unit 140 is installed on a side away from the combustor 20 so as to be stably operated without being affected by the high temperature and high pressure generated in the combustor 20. The control unit 140 may be a micro controller unit, ), And the like.

(Flame temperature measurement, pressure measurement, etc.) of diagnostic devices such as an ultrasound transmitter 120 and an ultrasound receiver 130 through a computer device such as an MCU, a microcomputer, Machine language) or the like. The parts related to machine language coding for controlling the diagnostic apparatus can be performed in various manners at the level of those skilled in the art, and a detailed description thereof will be omitted.

Hereinafter, how the algorithm relating to the measurement of the flame temperature (T) using the ultrasonic wave, which is the technical core of the present invention, is performed through the control unit 140 will be described below.

If the control unit 140 according to the first embodiment of the present invention, the first and second received signals (S1-t 1, t 2-S1) and the ultrasound in a state connected to the ultrasonic transmitter 120 and ultrasonic receiver 130 The flame temperature T in the combustor 20 is measured based on the distance L between the receiver 130 and the reflecting surface 20a.

2, the control unit 140 controls the ultrasonic transmitter 120 to generate a transmitted ultrasonic wave SU at predetermined time intervals. The bidirectional ultrasonic wave receiver 130 receives the transmitted ultrasonic wave SU ) and receiving a reflected wave (RU), respectively to thereby generate first and second received signals (S1-t 1, S1- t 2).

Next, the first and second received signals (S1-t 1, t 2-S1) The control unit 140 has received the first and second transmission on the basis of the received signal (S1-t 1, t 2-S1) After calculating the delay time? T (t 2 -t 1 ) from the reception of the ultrasonic wave (SU) to the reception of the reflected wave (RU), the velocity of the ultrasonic wave in the combustor 20 is calculated by the velocity formula C flame = 2L / (C flame ).

Lastly, the control unit 140 calculates the C flame value and the constant value of the calculated ultrasonic wave

Figure pat00003
And the R value is expressed by a relational expression of ultrasonic velocity and temperature
Figure pat00004
And the flame temperature T is calculated. At this time,
Figure pat00005
R is the gas constant value, T is the flame temperature (absolute temperature), and the specific heat ratio and gas constant value are the corrected values according to the combustion state, respectively. And is inputted to the control unit 140 in a state of being stored in the database, and is used for calculating the flame temperature (T).

The relationship between the ultrasonic velocity and the temperature is obtained by summarizing the gas equations for the actual air derived from the ideal gas equation and the velocity equations derived from the wave equation, and the detailed explanation of the induction process and the like is omitted.

The combustion state diagnosis apparatus 100 according to the first embodiment described above is not a method of indirectly measuring the flame temperature T through a sensor provided outside the combustor 20 as in the conventional method, The flame temperature T in the combustor 20 can be measured more precisely than in the prior art.

In addition, since the flame temperature of the combustor 20 can be measured using only one ultrasonic transmitter 120 and one bidirectional ultrasonic receiver 130, the number of parts can be dramatically reduced compared with the conventional one, And can be easily installed and applied to the combustor 20 and the combustion diagnosis tube 110 which are currently in operation without any structural change or replacement of the expensive combustor 20 .

On the other hand, if the control unit 140 according to the second embodiment of the present invention, the first-first received signal (S11 t-1), the second-first reception signal (S21-t 2), the second-second reception signal (S22-t 3) and the first-second received signal (S12-t 4), and first and second spaced-apart distance between the ultrasonic receiver (132,134), (L1), a second ultrasonic receiver (134) and the opening (110b) The flame temperature T in the combustor 20 is measured based on the separation distance L2 between the opening portion 110b and the reflecting surface 20a of the combustor.

3 and 4, when the controller 140 controls the ultrasonic transmitter 120 to generate ultrasonic waves (SU) at predetermined time intervals, the first and second bidirectional ultrasonic receivers 132 and 134 receives the transmitted ultrasound (SU) and the reflected wave (RU) in both directions in sequence, the first-first received signal (S11 t-1), the second-first reception signal (S21 t-2) respectively, , 2-2 and generates a received signal (S22-t 3) and the first-second received signal (S12-t 4).

Next, the control unit 140 received the four received signals is the sequentially, with a delay time based on a 1-1,2-1 received signals (S11-t 1, S21- t 2) △ t 1 ( t 2 -t 1) a, the second-first, the delay time △ t 2 (t 3 -t 2 ) on the basis of the 2-2 received signals (S21-t 2, S22- t 3), the second- 2,1-2 based on the received signal (S22-t 3, S12- t 4) to calculate the delay △ t 3 (t 4 -t 3 ) , respectively. And the rate equation C 1 = L 1 / △ a transmission rate (C 1) of the ultrasound (SU) by t 1, the speed formula C flame = 2 (L 2 + L 3) / △ combustor 20 by t 2 the ultrasonic velocity (C flame) of within, is by the rate equation C 2 = L 1 / △ t 3 calculates the rate (C 2) of the reflected wave (RU), respectively.

Finally, the controller 140 determines whether a constant

Figure pat00006
Value and the R value and the speed value of the output ultrasonic wave (C 1, C 2, C flame) from the flame C Only the value is the relationship between the ultrasonic velocity and the temperature
Figure pat00007
The flame temperature T can be calculated. However, since the flame temperature T at this time is based on the average speed of ultrasonic waves propagated or reflected over the section of L 2 + L 3 , the accuracy of the flame temperature T is higher than that based on the average speed of the ultrasonic waves in the section L 3 of the pure combustor 20 It can fall.

here

Figure pat00008
R is the gas constant value, T is the flame temperature (absolute temperature), and the specific heat ratio and gas constant value are the corrected values according to the combustion state, respectively. Is inputted to the control unit 140 in the state of being stored in the database and used for the flame temperature (T) calculation is the same as the first embodiment.

The combustion state diagnosis apparatus 100 according to the second embodiment of the present invention is not a method of indirectly measuring the flame temperature T through a sensor provided outside the combustor 20 as in the prior art, The flame temperature T in the combustor 20 can be measured more precisely and more accurately than in the conventional example, as in the first embodiment.

In comparison with the first embodiment, one bidirectional ultrasound receiver 130 is added, but the number of parts is reduced compared with the conventional one. The same is true of a simple structure, which is not only easy maintenance, The combustor 20 and the combustion diagnosis tube 110 can be easily installed and operated without any structural change or replacement of the combustor 20.

In comparison with the first embodiment, a bidirectional ultrasonic receiver 130 is additionally provided along the longitudinal direction of the combustion diagnosis tube 110, and a separation interval L3 between the opening 110b and the second ultrasonic receiver 134 The reason for implementing the second embodiment in a further compartmentalizing manner is that the more precise flame temperature T is measured and the diffraction, interference, superposition of the ultrasonic waves, or the physical factors in the combustor 20, ), And so on.

That is, in order to further increase the accuracy of the measurement of the flame temperature T, the control unit 140 utilizes not only the C flame value, which is the speed value of the ultrasonic wave already calculated, but also the C 1 and C 2 values as follows.

First, the control unit 140, a second ultrasonic delay time △ t 4 of the transmission ultrasound (SU) for the receiver 134, distance (L2) up to the opening (110b) in a transmission ultrasound (SU in the L1 region ) Speed C 1 on the basis of the speed equation? T 4 = L2 / C 1 . The reason for applying the bore rate equation the speed value C 1 The value of L1 region at the speed value of the L2 segment is, L1 region and L2 region is because larger the section and the temperature difference between adjacent each other on the combustion diagnosis tube 110, the continuity of the propagation speed This is because no appreciable level of error will occur.

Next, the control unit 140, a second delay time △ t 5 of the reflected wave (RU) for a distance (L2) up to the ultrasonic receiver 134, 130 in the openings (110b), the reflected wave in the L1 region (RU) is the velocity calculated by the rate equation △ t 5 = L2 / C 2 on the basis of C 2. Again, the reason applying the bore rate equation the speed value C 2 The value of L1 region at the speed value of the L2 segment is, L1 region and L2 region are adjacent to each other section, and because large temperature differences continuity of the propagation speed on the combustion diagnosis tube 110 , There is no significant level of error.

Lastly, the control unit 140 determines the ultrasonic velocity in the pure combustor 20 section L3 by the velocity formula C flame = 2L 3 / (? T 2 -? T 4 -? T 5 ) C flame ) is calculated, and the relationship between the ultrasonic velocity and the temperature

Figure pat00009
The flame temperature T can be calculated more precisely than in the case where it is advanced.

On the other hand, in order to correct the ultrasonic wave diffraction, interference, superposition, and measurement error of the ultrasonic receiver 130 according to physical factors in the combustor 20, the controller 140 controls the second -2 received signals (S22-t 3) and the delay time calculation to 1-2 based on the received signal (S12-t 4) △ t 3 (C 2 = L calculated by the 1 / △ t 3) and a transmission When there is a difference of a predetermined range or more between the delay times? T 3 'calculated by the speed formula C 1 = L 1 /? T 3 ' based on the C 1 value of the ultrasonic wave (SU) speed, Respectively. The predetermined range at this time may be appropriately added or subtracted according to the user's needs. In order to pursue the accuracy of the measurement of the flame temperature (T), it is preferable to set the narrow range.

The reason why the measurement error can be determined in the above-described manner is that if the transmitted ultrasonic wave (SU) transmitted from the ultrasonic transmitter 120 is propagated and reflected, it is not influenced by diffraction, interference or other physical factors The velocity C 1 of the transmitted ultrasonic wave SU and the velocity C 2 of the reflected wave RU are equal to each other in the same section L1 so that the delay times? T 3 'and? T 3 3 are the same, but if not ideal, as the influence of physical factors and the like on the speeds (C 1 , C 2 ) in the L1 section as well as the delay times Δt 3 'and Δt 3 increases, , Which results in the conclusion that the measurement of the flame temperature T, which is eventually calculated based on the ultrasonic velocity, is unreliable.

Accordingly, when the calculated values of Δt 3 'and Δt 3 differ from each other by a predetermined range or more, the control unit 140 notifies the user of the measurement error and the like, and also controls the ultrasonic transmitter 120 (SU) through the ultrasonic transducer (not shown).

5, in consideration of the characteristics of combustion in which the CO emission is increased when the flame temperature T in the combustor 20 for the gas turbine is 1300 DEG C or less, the control unit 140 calculates the flame temperature T ) Is 1300 DEG C or lower, it can be implemented to generate a carbon monoxide (CO) generation danger signal.

On the other hand, as shown in FIG. 6, in consideration of the characteristic of combustion in which the NO x emission increases at the flame temperature T of 1600 ° C or higher in the combustor 20 for the gas turbine, If the temperature T is 1600 ° C or higher, it can be implemented to generate a nitrogen oxide (NO x ) generation danger signal.

The graphs of combustion characteristics of the gas turbine 10 shown in Figs. 5 and 6 are based on Fig. 9 and Fig. 7 of the contents published by the applicant of the present invention in International Journal of Hydrogen Energy.

(see http://www.sciencedirect.com/science/journal/03603199)

As described above, the danger signal generated by the control unit 140 may be transmitted to a control panel (not shown) of the gas turbine 10 and displayed to an operator.

The graph of emission characteristics of harmful substances (including new fuel, ie, IGCC, bio gas, DME (Dimethyl Ether), and SNG (Synthetic Natural Gas)) according to the flame temperature T and the combustion temperature measured according to the present invention It is possible to precisely determine and cope with the incomplete combustion of the fuel in real time, so that the combustion efficiency of the fuel can be improved and the harmful exhaust gas can be reduced.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed embodiments, but, on the contrary, It is obvious to those who have. Accordingly, such modifications or variations should not be individually understood from the technical spirit and viewpoint of the present invention, and modified embodiments should be included in the claims of the present invention.

SU: Transmission ultrasound RU: Reflected wave
S1 t-1: the first received signal S1 t-2: a second receiving signal
S11-t 1: [0075] the received signal S12-t 4: first-second received signal
S21-t 2: the second-first reception signal S22-t 3: the second-second reception signal
10: gas turbine 12: compressor
14: turbine blade 16: exhaust port
20: combustor 20a: reflecting surface
100: Gas turbine combustion condition diagnosis device using ultrasonic wave according to the present invention
110: combustion diagnosis tube 110a: opening
120: Ultrasonic transmitter 130: Ultrasonic receiver
132: first ultrasonic receiver 134: second ultrasonic receiver
140:

Claims (8)

A combustion diagnosis tube having an opening at one end and communicating with an inner space of the combustor for a gas turbine, and the other end protruding outward;
An ultrasonic transmitter provided at the other end of the combustion diagnosis tube for generating a transmission ultrasonic wave toward the combustor through the combustion diagnosis tube;
An ultrasonic receiver provided in the combustion diagnosis tube for receiving the transmission ultrasonic wave to generate a first reception signal and receiving a reflected wave returned by the inner reflection surface of the combustor among the transmission ultrasonic waves to generate a second reception signal; And
A control unit connected to the ultrasonic transmitter and the ultrasonic receiver for controlling the flame temperature T in the combustor based on the first and second reception signals and a distance L between the ultrasonic receiver and the reflection surface, Wherein the gas turbine combustion condition diagnosis apparatus comprises: The method according to claim 1,
Wherein,
Calculates a delay time? T from the transmission ultrasonic wave reception to the reflected wave reception based on the first and second reception signals,
After calculating the velocity (C flame ) of the ultrasonic wave in the combustor by the speed formula C flame = 2L /? T,
The relationship between ultrasonic velocity and temperature
Figure pat00010
Wherein said flame temperature (T) is calculated by said gas turbine combustion state detecting means. The method according to claim 1,
The ultrasonic receiver includes:
A first ultrasonic receiver in the combustion diagnosis tube and a second ultrasonic receiver spaced apart toward the combustor to sequentially receive the transmission ultrasonic waves to generate a 1-1 reception signal and a 2-1 reception signal, Second and third reception signals and a first and second reception signals by sequentially receiving the reflected waves returned by the inner reflecting surface of the combustor,
Wherein,
A second distance between the first and second ultrasonic receivers, a distance between the first and second ultrasonic receivers, a distance between the first and second ultrasonic receivers, And a control section for measuring the flame temperature (T) in the combustor based on a distance (L2) between the openings and a distance (L3) between the opening and the reflecting surface of the combustor Combustion state diagnostic device. The method of claim 3,
Wherein,
The delay time △ t 1 based on the first received signal 1-1,2-1, wherein said 2-1 and 2-2 delay △ t 2 on the basis of the received signal, wherein the 2-2,1- 2 based on the received signal and calculating the delay △ t 3, respectively,
(C 1 ) of the transmitted ultrasonic wave by the speed formula C 1 = L 1 / Δt 1 and the speed C 1 of the ultrasonic wave in the combustor by the speed formula C flame = 2 (L 2 + L 3 ) / Δt 2 speed (flame C) a, then by the rate equation C 2 = L 1 / △ t 3 calculates the rate (C 2) of the reflected wave, respectively,
The relationship between ultrasonic velocity and temperature
Figure pat00011
Wherein said flame temperature (T) is calculated by said gas turbine combustion state detecting means. 5. The method of claim 4,
In order to increase the accuracy of the flame temperature T,
The second ultrasonic transmission the delay △ t 4 of the spacing distance (L2) up to the aperture in the ultrasonic receiver, is calculated on the basis of the speed (C 1) of the transmitted ultrasound,
A delay time? T 5 of the reflected wave with respect to a separation distance (L2) from the opening to the second ultrasonic receiver is calculated on the basis of the velocity (C 2 ) of the reflected wave,
Wherein the velocity (C flame ) of the ultrasonic waves in the combustor is calculated by the velocity formula C flame = 2L 3 / (? T 2 -? T 4 -? T 5 ) Device. 5. The method of claim 4,
Wherein,
Based on the above delay time, △ t 3, the speed (C 1) of the transmission ultrasonic waves generated by said control rate equation C 1 = L 1 / △ t 3 or more, △ t 3 which is calculated by "a predetermined range And generates a measurement error signal when there is a difference between the detected temperature and the detected temperature of the gas turbine. 7. The method according to any one of claims 1 to 6,
Wherein,
And generates a carbon monoxide (CO) generation danger signal when the calculated flame temperature (T) is 1300 ° C or less. 7. The method according to any one of claims 1 to 6,
Wherein,
And a nitrogen oxide (NO x ) generation risk signal is generated when the calculated flame temperature (T) is 1600 ° C. or higher.
KR1020150172675A 2015-12-04 2015-12-04 Device for diagnosing the combustion state of a gas turbine by using an ultrasonic wave KR101804191B1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
KR1020150172675A KR101804191B1 (en) 2015-12-04 2015-12-04 Device for diagnosing the combustion state of a gas turbine by using an ultrasonic wave
JP2016517513A JP6308599B2 (en) 2015-12-04 2016-01-20 Gas turbine combustion state diagnosis device
PCT/KR2016/000599 WO2017094965A1 (en) 2015-12-04 2016-01-20 Device for diagnosing combustion state of gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020150172675A KR101804191B1 (en) 2015-12-04 2015-12-04 Device for diagnosing the combustion state of a gas turbine by using an ultrasonic wave

Publications (2)

Publication Number Publication Date
KR20170066090A true KR20170066090A (en) 2017-06-14
KR101804191B1 KR101804191B1 (en) 2017-12-04

Family

ID=59218177

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020150172675A KR101804191B1 (en) 2015-12-04 2015-12-04 Device for diagnosing the combustion state of a gas turbine by using an ultrasonic wave

Country Status (1)

Country Link
KR (1) KR101804191B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101862248B1 (en) * 2017-08-14 2018-05-29 인천대학교 산학협력단 Multipoint temperature sensing device using ultra sonic waves and multipoint temperature sensing system having the same
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

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6350988B1 (en) 1999-02-08 2002-02-26 General Electric Company Optical spectrometer and method for combustion flame temperature determination
JP2009168378A (en) 2008-01-17 2009-07-30 Chugoku Electric Power Co Inc:The Clinker distribution imaging apparatus for piping in coal burning boiler

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101862248B1 (en) * 2017-08-14 2018-05-29 인천대학교 산학협력단 Multipoint temperature sensing device using ultra sonic waves and multipoint temperature sensing system having the same
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

Also Published As

Publication number Publication date
KR101804191B1 (en) 2017-12-04

Similar Documents

Publication Publication Date Title
JP6548388B2 (en) Method of actively measuring gas flow velocity, including in a gas turbine combustor, or simultaneously measuring velocity and temperature
US9709448B2 (en) Active measurement of gas flow temperature, including in gas turbine combustors
JP5259568B2 (en) System and method for direct non-intrusive measurement of corrected air flow
US9746360B2 (en) Nonintrusive performance measurement of a gas turbine engine in real time
US9752959B2 (en) Nonintrusive transceiver and method for characterizing temperature and velocity fields in a gas turbine combustor
US10041859B2 (en) Parameter distribution mapping in a gas turbine engine
EP2738372B1 (en) Gas turbine temperature measurement
US9945737B2 (en) Method for determining waveguide temperature for acoustic transceiver used in a gas turbine engine
US9453784B2 (en) Non-intrusive measurement of hot gas temperature in a gas turbine engine
US9696216B2 (en) Acoustic transducer in system for gas temperature measurement in gas turbine engine
US10145558B2 (en) Method for determining the temperature inside a combustor
EP3056885B1 (en) Measurement system and method for measuring temperature and velocity of a flow of fluid
KR101804191B1 (en) Device for diagnosing the combustion state of a gas turbine by using an ultrasonic wave
GB2207756A (en) Method and apparatus for nonintrusively determining mach number
KR101862248B1 (en) Multipoint temperature sensing device using ultra sonic waves and multipoint temperature sensing system having the same
KR101668842B1 (en) Device for diagnosing the combustion state of a gas turbine by using infrared light
JP2015021949A (en) Sound velocity measuring instrument, gas turbine facility, and sound velocity measurement method
KR20220158483A (en) Apparatus for diagnosing the combustion state of a gas turbine, system for diagnosing the combustion state of a gas turbine and method for diagnosing the combustion state of a gas turbine
Gorny et al. Testing Long-Wavelength Acoustic Flowmeter Concepts for Flue Gas Flows
KR20190063314A (en) Apparatus for combustion diagnosis of gas turbine

Legal Events

Date Code Title Description
A201 Request for examination
E902 Notification of reason for refusal
E701 Decision to grant or registration of patent right
GRNT Written decision to grant