JP2012193978A - Temperature distribution measuring method, measuring device and measuring program - Google Patents

Abstract

PROBLEM TO BE SOLVED: To enable temperature distribution on a two-dimensional section to be measured by catching self-emitted light of non-luminous combustion gas with a simple optical system and measuring system.SOLUTION: A section of an object of measurement is divided in a checkerboard-like grid pattern, the intensity of light emitted by gas in the central position in the arranged direction of cells on each row of the grid is measured, the intensity of light emitted by the gas in the central position in the arranged direction of cells on each column is measured, the band spectral intensities of each row and each column are determined on the basis of these light emission intensities, the average gas temperature of the section of the object of measurement is calculated on the basis of combustion attributes of the gas, and the gas temperature in the central position of each cell in the grid is calculated by using the average gas temperature and the band spectral intensities of each row and each column.

Description

  The present invention relates to a method for measuring a temperature distribution of a gas flow in a cross-section to be measured, a measuring apparatus, and a measuring program. More specifically, the present invention measures the temperature distribution of the gas flow at any cross-section from the combustor outlet to the expansion turbine inlet, for example for high temperature, high pressure, high speed flow and non-flaming combustion gas in a gas turbine. It relates to technology.

  In gas turbine power plants, high efficiency has been achieved by increasing the temperature and pressure of gas at the gas turbine inlet. Along with this, the ratio of the cost of high-temperature components to the entire gas turbine equipment increases due to the application of high-functional materials to high-temperature parts such as gas turbine combustors and expansion turbines and the construction of various coating technologies. At the same time, the ratio of high-temperature parts inspection and repair costs to the total plant operating costs tends to increase.

  On the other hand, gas turbines with excellent environmental conservation take into account that the NOx generation concentration in combustion exhaust gas increases due to higher temperatures for higher efficiency, and lean premixed combustion is used to suppress this. Uniform combustion is adopted. In the homogeneous combustion typified by lean premixed combustion, unlike the conventional diffusion combustion with stoichiometric combustion, the combustion range in the stoichiometric condition is reduced spatially and temporally in the upstream part of the combustor. By reducing the combustion temperature, the concentration of thermal NOx produced by oxidation of nitrogen in the air in a high-temperature gas of 1500 to 1600 ° C. or higher is reduced.

  Here, in the uniform combustion, when the combustion speed is reduced and LNG mainly composed of methane having a narrow combustible range is used as the fuel, the stability of the flame is lowered. For this reason, there is a concern that combustion vibration may occur due to individual differences in gas turbine equipment, increase or decrease in gas turbine load, and the gas temperature at the inlet of the expansion turbine may periodically fluctuate.

  Therefore, a method using a pilot burner in order to increase the flame stability and reduce the NOx emission (Patent Document 1), or a method using a windbox to prevent combustion vibration and stabilize the flame ( Patent Document 2), a technique for absorbing combustion vibration pressure acoustically in order to reduce combustion vibration (Patent Document 3), and the like are employed.

  However, in practice, the periodic fluctuation of gas temperature at the outlet of the combustor and the inlet part of the expansion turbine and the fluctuation range thereof are unknown. Is actually determined using static experimental values obtained by a combustor single unit test using a thermocouple, and an unexpected combustion vibration phenomenon occurs at the time of equipment design during the trial operation of the actual machine.

  For this reason, if the gas temperatures at the combustor outlet and the expansion turbine inlet in the actual machine can be monitored, the combustion vibration suppressing method described in Patent Documents 1, 2, and 3 can be accurately implemented, and the high-temperature turbine component It can contribute to optimization of the cooling method.

  Here, for non-contact gas temperature measurement, a radiation thermometer that detects infrared rays and identifies the temperature from the emissivity and Planck's law has been put into practical use (Patent Document 4).

  Other non-contact temperature measurement methods include a method of obtaining temperature information from the intensity of scattered light by irradiating monochromatic light to generate Raman scattered light (Patent Document 5), or using two laser beams having different wavelengths. Field information by measuring the emission of light generated during the transition to the ground state by exciting a specific substance in the combustion gas with a laser by generating the Raman scattered light and generating high intensity resonance light There is a laser induced fluorescence method to obtain

  As a non-contact temperature measurement method, there is a method in which a position is measured using two ultrasonic waves having different wavelengths, and at the same time, a temperature is measured by using a change in sound speed due to a sound pressure fluctuation caused by the temperature fluctuation. (Patent Document 6).

Further, the distribution of gas temperature at the combustor outlet cross section or the expansion turbine inlet cross section of the gas turbine is generally evaluated by Pattern Factor (hereinafter referred to as PF; unit:%) represented by Formula 1. Is done.
(Equation 1) P.F. = (T _max −T _ex ) / (T _ex −T _air ) × 100
Where T _{max is} the maximum temperature of the gas in the cross section [K]
T _ex : Average gas temperature of cross section [K]
T _air : represents the temperature [K] of the combustion air.

Here, in the design of the combustor, it is generally required that the value of PF is within 15 to 17%. If T _ex = 1773 [K] (= 1500 [° C.]) and T _air = 673 [K] (= 400 [° C.]), the T _max should be set to 17% or less under PF. Must be 1960 [K] or less. In this case, (T _max −T _ex ) is 187 [K]. However, since this only defines a high temperature, a temperature difference ΔT _min from a temperature lower than T _ex is added, and the temperature difference ΔT between the high and low points of the actual gas temperature is (ΔT _min +187 ) [K]. That is, in the design of the expansion turbine blade cascade, in addition to the examination of the heat resistance condition corresponding to the maximum temperature, the examination of the temperature difference based on the temperature distribution in the cross section is also important.

JP-A-2-33419 JP-A-5-187635 Patent No. 39625554 JP 2006-90978 A JP 53-67481 A JP 2003-14555

  However, the combustion gas at the outlet of the low NOx combustor and the inlet of the expansion turbine, which is realizing uniform combustion by lean premixing, is not a bright flame like diffusion combustion, so it becomes translucent because there is little infrared light, and hydrogen In addition, the side wall of the combustor is coated with a refractory material or heat-resistant coating, and the combustion gas and its heat cause large infrared radiation from the refractory material or heat-resistant coating. Therefore, it is difficult to measure the gas temperature with the radiation thermometer of Patent Document 4 that senses infrared light.

  Further, for example, in the measurement method using a laser as in Patent Document 5, there is a problem that the optical system is complicated, and a technical problem as a measurement method remains to be applied to a high temperature field in a gas turbine actual machine. There's a problem. Specifically, a small burner flame is irradiated with a laser to measure the scattered light and emission intensity that would be caused by the flame and temperature, and a certain relationship between the intensity characteristics of the light and the temperature characteristics of the flame. Although it is possible in the laboratory to measure the temperature distribution, it is practically difficult to apply it to an actual gas turbine. Further, although calibration is prescribed for thermocouples and radiation thermometers, there is a problem that the method using a laser is not at a stage where it can be prescribed as a temperature measurement method. Even when using self-luminous light, it cannot be measured if it cannot be calibrated.

  In the measurement method using a laser, there is also a problem that the use of a laser may affect the combustion gas and cause a combustion vibration or the like. Furthermore, there is a problem that the measurement system is complicated and verification is difficult.

  Furthermore, the measurement method using sound waves of Patent Document 6 is intended for room temperature, and there is a problem that a technical problem remains as a measurement method to be applied to measurement under a high temperature / high flow rate condition. is there. Specifically, indoor temperature measurement or boiler temperature measurement methods using sound waves have been proposed, but when sound waves are used, accurate measurement is actually difficult due to the influence of noise inside the boiler, Further, in order to remove the influence of noise inside the boiler, it is necessary to identify the noise characteristics inside the boiler. Further, the combustion gas flow has a flow rate of 100 [m / s], and there is a problem that an error occurs when the temperature is identified by the rate of change in sound speed using sound waves. For example, the sound velocity is 331 [m / s] at 0 [° C] and 843 [m / s] at 1500 [° C], so the combustion gas flow of 100 [m / s] is about 1/8 speed. This is an error.

  In the measurement method using sound waves, there is a problem in that the use of sound waves may affect the combustion gas and cause combustion vibrations. Furthermore, there is a problem that the measurement system is complicated and verification is difficult.

  In addition, in the design of expansion turbine blade rows, in addition to examining the heat resistance conditions corresponding to the maximum temperature, it is important to study the temperature difference based on the temperature distribution in the cross section. There is a problem that measurement is not realized and data for verifying the design is not sufficiently grasped.

  Therefore, the present invention captures the self-luminescence of the combustion gas of the non-luminous flame by a simple optical system and measurement system in a high temperature / high pressure / high flow velocity field such as a gas turbine combustor outlet and an expansion turbine inlet. An object of the present invention is to provide a temperature distribution measuring method, a measuring apparatus, and a measuring program capable of measuring a temperature distribution of a dimensional cross section.

  In order to achieve such an object, the temperature distribution measuring method according to claim 1 divides the cross section of the measurement object into a grid pattern, and determines the emission intensity of the gas at the center position in the arrangement direction of the grid for each stage of the grid pattern. Measure the emission intensity of the gas at the central position of the grid in each column and determine the band spectrum intensity for each stage and each column based on these emission intensities. Based on the average gas temperature of the cross section to be measured based on the average gas temperature and the band spectrum intensity of each stage and each column, the gas temperature at the center position of each grid of the grid is calculated I am doing so.

  The temperature distribution measuring apparatus according to claim 5 is a band based on a gas emission intensity at a central position in the arrangement direction of the grid of each stage of the grid, which is measured by dividing the cross section of the measurement object into a grid. Means for receiving input of spectral intensity and band spectral intensity based on emission intensity of the gas at the center position in the arrangement direction of the grid for each column, and calculating the average gas temperature of the cross section to be measured based on the combustion attribute of the gas And means for calculating the gas temperature at the center position of each square of the grid using the average gas temperature and the band spectrum intensity for each stage and each column.

  A temperature distribution measurement program according to claim 9 is a program for causing a computer to perform a process of calculating a gas temperature in a measurement target section, and is measured by dividing the measurement target section into a grid pattern. Input of the band spectrum intensity based on the emission intensity of the gas at the center position of the grid in each row of the grid and the band spectrum intensity based on the emission intensity of the gas at the center position of the grid in each row The cross-section using the average gas temperature and the band spectrum intensity of each stage and each column, the process of calculating the average gas temperature of the cross section to be measured based on the combustion attribute of the gas, The computer is caused to perform processing for calculating the gas temperature at the central position of each square.

  According to the temperature distribution measuring method, measuring apparatus, and measuring program of the present invention, the combustion temperature of the combustion gas can be obtained by measuring the self-luminescence of the combustion gas of the non-luminous flame according to the principle described below.

In gas turbines, almost 100% of the fuel is combusted at the combustor outlet or expansion turbine inlet, except in the case of aircraft engine high load conditions. That is, a general chemical reaction is the result of a number of elementary reactions that proceed on the order of milliseconds, and the chemical species and concentration depending on the reaction temperature and pressure are determined. In the case of a power plant, the temperature and pressure drop to about 100 ° C. and almost atmospheric pressure at the smoke outlet, and at that time, almost 100% of the fuel is discharged as CO ₂ and H ₂ O.

  Among the intermediate products in the reaction in the combustion gas, those having unpaired electrons are called radicals, and the progress of the combustion reaction can be estimated from the presence of these radicals. The radicals are excited by the heat of combustion, etc., and the excited radicals generate light corresponding to the energy difference in the process of transitioning to a ground state having a low energy level. There is a certain relationship between them. That is, there is a certain relationship between the emission intensity of the combustion gas and the combustion temperature. Therefore, the combustion temperature can be identified by measuring the emission intensity of the combustion gas.

  The invention according to claim 2 is the temperature distribution measuring method according to claim 1, wherein the emission intensity of the gas is measured from both sides of the grid direction of each stage of the grid and for each column. The measurement is made from both sides in the direction of the squares. According to a sixth aspect of the present invention, in the temperature distribution measuring apparatus according to the fifth aspect, the emission intensity of the gas is measured from both sides of the grid direction of each stage of the grid and each column. Each square is measured from both sides in the arrangement direction. The invention according to claim 10 is the temperature distribution measuring program according to claim 9, wherein the emission intensity of the gas is measured from both sides of the grid direction of each stage of the grid and each column. Each square is measured from both sides in the arrangement direction. In this case, even when there is unevenness in the gas temperature distribution in the measurement object cross section, the measurement that reflects the unevenness is performed.

According to a third aspect of the present invention, in the temperature distribution measuring method according to the first aspect, the band spectrum intensity is any one of an OH radical, a CH radical, and a C ₂ radical. According to a seventh aspect of the present invention, in the temperature distribution measuring apparatus according to the fifth aspect, the band spectrum intensity is any one of an OH radical, a CH radical, and a C ₂ radical. The invention according to claim 11 is the temperature distribution measurement program according to claim 9, wherein the band spectrum intensity is one of OH radical, CH radical, or C ₂ radical. In this case, the gas temperature is accurately measured based on the band spectrum intensity.

  According to a fourth aspect of the present invention, in the temperature distribution measuring method according to the first aspect, the measurement object cross section is an arbitrary cross section of a transition piece of a gas turbine. According to an eighth aspect of the present invention, in the temperature distribution measuring apparatus according to the fifth aspect, the measurement object cross section is an arbitrary cross section of the transition piece of the gas turbine. According to a twelfth aspect of the present invention, in the temperature distribution measurement program according to the ninth aspect of the invention, the cross section to be measured is an arbitrary cross section of the transition piece of the gas turbine.

  According to the temperature distribution measuring method, measuring apparatus, and measuring program of the present invention, it becomes possible to measure the temperature of the non-flammable combustion gas in a non-contact manner, which has been considered difficult to measure in an actual machine, and the combustion gas. Since the temperature of the combustion gas can be measured without affecting the flow, it is possible to improve versatility as a temperature distribution measurement of the combustion gas.

  In addition, according to the temperature distribution measuring method, measuring apparatus, and measuring program of the present invention, it is possible to measure the temperature of combustion gas without using anything that affects downstream equipment when it is damaged, for example, a thermocouple. In addition, since the temperature of the combustion gas can be measured by a simple and inexpensive method, it is possible to improve versatility as a temperature distribution measurement of the combustion gas.

  Further, according to the temperature distribution measuring method, measuring apparatus, and measuring program of the present invention, it is possible to measure the temperature of the combustion gas in the actual machine, not the combustion equipment test. Therefore, it is possible to appropriately design and evaluate the combustor and the downstream equipment, and greatly contribute to the improvement of the reliability of the combustion equipment and the downstream equipment.

  In addition, combustion equipment and downstream equipment often apply refractory materials and heat-resistant coatings as the combustion gas temperature of the combustion equipment rises, making infrared radiation more difficult to measure the combustion gas temperature, According to the temperature distribution measuring method, measuring apparatus, and measuring program of the present invention, since visible light or ultraviolet light having a wavelength not related to infrared radiation is measured, the temperature of the combustion gas is measured more accurately. This makes it possible to improve the reliability of the temperature distribution measurement of the combustion gas.

  Further, according to the temperature distribution measuring method, measuring apparatus, and measuring program of the present invention, it is possible to measure a two-dimensional temperature distribution in the cross section of the combustion gas by using a combination of measured values obtained from a plurality of light receiving parts. As a result, the exposure conditions of the combustion device and the downstream device can be grasped in more detail, so that it is possible to further contribute to the optimum design of the combustion device and the downstream device. As a result, it is possible to extend the life of the combustion equipment and the equipment on the downstream side thereof with a cheaper design, and it is possible to contribute to the reduction of equipment costs and repair costs.

  In addition, according to the temperature distribution measuring method of the second aspect, it is possible to measure the temperature distribution that accurately reflects the uneven distribution of the gas temperature in the cross section of the measurement object, thereby improving the accuracy of the gas temperature distribution measurement. Therefore, the reliability of the combustion gas temperature distribution measurement can be improved.

It is a flowchart explaining an example of embodiment of the temperature distribution measuring method of this invention. It is a functional block diagram of the temperature distribution measuring device when the temperature distribution measuring method of this embodiment is implemented using a program. It is a functional block diagram explaining the whole mechanism of the temperature distribution measurement in this embodiment including the temperature distribution measuring apparatus of this invention. It is sectional drawing of the gas turbine which has a measurement object cross section of embodiment. It is a figure explaining the division | segmentation of the measurement object cross section of embodiment, and arrangement | positioning of a light-receiving part.

  Hereinafter, the configuration of the present invention will be described in detail based on the form shown in the drawings.

1 to 5 show an example of embodiments of the temperature distribution measuring method, measuring apparatus and measuring program of the present invention. In the temperature distribution measuring method of the present invention, the cross section 21a to be measured is divided into a grid pattern, and the emission intensity L of the gas at the center position in the arrangement direction of at least each grid of the grid pattern is measured and for each column. The emission intensity L of the gas at the center position in the arrangement direction of the squares is measured, the band spectrum intensity _{L_b} for each stage and each column is obtained based on the emission intensity L, and the cross-section to be measured based on the combustion attribute of the gas The average gas temperature T _ex of 21a is calculated, and the gas temperature T at the center position of each square of the grid is calculated using the average gas temperature T _ex and the band spectrum intensity _{L_b} for each stage and each column. I am doing so.

  In the present embodiment, a gas turbine showing a cross section of the compressor cascade CC, the gas turbine combustor casing 24, and the expansion turbine cascade CT will be described as an example in FIG.

  In the gas turbine combustor casing 24, a combustion gas flow guiding transition piece 21 (also referred to as a combustor tail cylinder) (hereinafter simply referred to as a “trailer”) is provided between the combustor inner cylinder 22 and the expansion turbine blade row CT. (Referred to as a piece 21). In the present embodiment, the temperature of the combustor exhaust gas 23 is measured at the inlet cross section 21a of the transition piece 21 (hereinafter referred to as the TP inlet cross section 21a), which is also the cross section of the outlet of the combustor inner cylinder 22. Will be described. Hereinafter, the TP inlet cross section 21a is also referred to as a measurement target cross section. In the present embodiment, the TP inlet cross section 21a is circular. In FIG. 4, reference numeral 25 denotes compressor discharge air, reference numeral 26 denotes start-up fuel, reference numeral 27 denotes main fuel, and reference numeral 28 denotes a combustor burner (specifically, a fuel injection nozzle and an air swirler). Reference numeral 29 denotes a combustor outer cylinder (also referred to as a flow sleeve), and reference numeral FG denotes exhaust gas after passing through the expansion turbine.

  The light receiving unit 9 receives the self-emission of flame (combustion gas) at the TP inlet cross section 21a, and is specifically a light receiving unit of an optical fiber cable.

  The light receiving unit 9 is disposed on the peripheral edge of the entrance of the transition piece 21 in a direction to receive the self-emission of flame in the TP entrance cross section 21a (that is, toward the inside of the entrance of the transition piece 21).

  The light received by the light receiving unit 9 has a subject depth, and the light emission intensity of the flame (combustion gas) received and measured by the light receiving unit 9 is an integrated value of light emission for the subject depth. In the present invention, an integrated value of light emission in a region (a linear region) corresponding to the subject depth in front of the light receiving unit 9 that is light emitted by the light receiving unit 9 is used. A line extending straight forward in front of the light receiving unit 9 is referred to as a measurement line.

  Here, in the present invention, the cross section to be measured is virtually divided into a grid pattern (indicated by a dotted line in FIG. 5). In addition, when the measurement target cross section is not rectangular as in this embodiment, the inside of the rectangle that fits in the measurement target cross section is divided into a grid pattern. Then, the light receiving portions 9 are arranged in the diagonal direction so that the measurement lines of the light receiving portions 9 intersect each other at approximately the center of each divided grid. In the present invention, the temperature at the point where the measurement lines intersect is determined. Hereinafter, a point at which the measurement lines intersect and is a target of temperature measurement in the present invention is referred to as a temperature measurement point.

  In the present embodiment, a rectangle that fits in the circular TP inlet cross section 21a, which is a cross section to be measured, is divided into a grid of 3 squares × 3 rows in total of 9 squares (displayed by dotted lines in FIG. 5; each square is a square). Then, the temperature of the combustion gas at the center of each square (that is, all nine points) is measured.

  In the present embodiment, six cells arranged oppositely with the center positions of the three cells arranged in each of the three steps as the respective measurement lines, and the center of the three cells arranged in the three columns for each of the three columns. A total of sixteen light receiving portions 9, each of which has six positions arranged opposite to each other with the position as a measurement line and four pieces arranged opposite to each other with the diagonal direction of the rectangle as an individual measurement line, enter the transition piece 21. It is arrange | positioned at the peripheral part.

  Then, the measurement lines of each light receiving unit 9 intersect at the center of each grid having a grid pattern, and the center of each grid becomes a temperature measurement point.

  Here, in the present embodiment, as shown in FIG. 5, the self-light emission of the upper three squares among the three-stage × three-row grid-like squares obtained by dividing the rectangle that fits in the TP inlet cross section 21 a is measured. (In other words, the measurement line penetrates the center of the upper three squares) The identifiers of the two light receiving portions 9 facing each other are A (left side in the figure) and A '(right side), and the middle three squares are measured. Are B and B ′, and C and C ′ are those for measuring the lower three cells. Further, the self-luminous measurement of the three cells in the left column is performed (that is, the measurement line penetrates the center of the three cells in the left column). Upper side) and D ′ (lower side), those that measure 3 squares in the center row are E and E ′, and those that measure 3 squares in the right row are F and F ′. In addition, the identifiers of the two light receiving units 9 facing each other for measuring the self-light emission of three squares in the diagonal direction from the upper left to the lower right as shown in the figure are G (upper left) and G ′ (lower right), and the upper right Let H (upper right side) and H ′ (lower left side) measure 3 squares in the diagonal direction from to the lower left. Also, the temperature measurement points of the upper three cells are a1, a2, and a3 in order from the center of the left cell, the temperature measurement points of the middle three cells are b1, b2, and b3 in order from the center of the left cell, and the lower 3 The cell temperature measurement points are c1, c2, and c3 in order from the center of the left cell.

  Each light receiving unit 9 sends the received self-emission of flame (combustion gas) at the TP inlet cross section 21 a to the signal amplifier 5 through the optical fiber cable 4.

  The signal amplifier 5 amplifies the signal light for each light receiving unit 9 transmitted via the optical fiber cable 4. Then, the signal amplifier 5 sends the amplified signal light for each light receiving unit 9 to the spectral spectrum analyzer 6.

  The spectral spectrum analyzer 6 performs spectral analysis by splitting the signal light sent from the signal amplifier 5 for each wavelength. The spectrum analyzer 6 includes a spectrometer 6a, a camera 6b, a controller 6c such as an A / D converter, and a spectrum analyzer 6d.

  The signal light input from the signal amplifier 5 to the spectral spectrum analyzer 6 is first input to the spectroscope 6a. The spectrometer 6a separates the input signal light for each wavelength.

  Next, the camera 6b selects a specific wavelength by a filter. The camera 6b may be any device that generates an output signal corresponding to the energy of light. For example, a CCD (Charge Coupled Device) element, a CMOS (Complementary Metal Oxide Semiconductor) element, a thermopile, a photomultiplier tube, or the like is used. For example, a CCD camera or a camera equipped with a thermopile is used. It should be noted that the sensitivity characteristics of a camera 6b such as a CCD camera, for example, are matched to the characteristics of the flame (combustion gas) to be measured (in other words, the light is received) (specifically, the emission wavelength of the combustion gas (radical)). (Specifically, as an example, models C7972-03G, C7972-11, and C7164-03 manufactured by Hamamatsu Photonics Co., Ltd. can be applied).

  Next, the controller 6c such as an A / D converter digitizes the intensity of the signal light.

  Next, the spectrum analyzer 6d decomposes the light emission, that is, the wave of light, into intensities for each wavelength.

  Then, the spectrum intensity for each wavelength for each light receiving unit 9 output as a result of the processing of the spectrum analyzer 6 is input to the temperature distribution measuring apparatus 10.

  Here, there is a correlation between the band spectrum intensity of a specific wavelength of flame self-luminescence and the flame temperature, and it is known that the flame temperature can be estimated from the band spectrum intensity of a specific wavelength (Kidoguchi and Takahashi). : Development of simultaneous measurement method of flame temperature and equivalence ratio by flame luminescence measurement-1st report Examination in the open air Bunsen burner flame-Report of Central Research Institute of Electric Power, Research report: W99040, May 2000).

In the present invention, specifically, for example, OH radicals (wavelength: 309.0 nm, etc.) or a CH radical (wavelength: 431.4 nm, etc.) or a C ₂ radical (wavelength: 516.5 nm, etc.) band spectrum, such as Use the relationship between intensity and flame temperature.

In the present embodiment, the spectrum analyzer 6d outputs the band spectrum intensity of the OH radical, CH radical, or C ₂ radical to the temperature distribution measuring apparatus 10.

And the temperature distribution measuring apparatus of this invention divides the measurement object cross section 21a into a grid pattern, and the emission intensity of the gas at the center position in the grid direction in at least each grid of the grid pattern measured by the light receiving unit 9. Means for receiving the band spectrum intensity _{L_b} based on L and the band spectrum intensity _{L_b} based on the emission intensity L of the gas at the center position in the arrangement direction of the _{grids for} each column, and the cross section to be measured based on the combustion characteristics of the gas The center position of each grid of the grid (that is, the temperature measurement point) using the means for calculating the average gas temperature T _ex of 21a and the average gas temperature T _ex and the band spectrum intensity _{L_b} for each stage / column. ) For calculating the gas temperature T.

  The above-described temperature distribution measuring apparatus can also be realized by executing the temperature distribution measuring program of the present invention on a computer. In the present embodiment, a case where the temperature distribution measurement program 17 is executed on a computer will be described as an example.

  FIG. 2 shows an overall configuration of the temperature distribution measuring apparatus 10 of the present embodiment for executing the temperature distribution measuring program 17. The temperature distribution measuring apparatus 10 includes a control unit 11, a storage unit 12, an input unit 13, a display unit 14, and a memory 15, and is connected to each other by a signal line such as a bus.

  The control unit 11 performs an operation related to the control of the entire temperature distribution measuring apparatus 10 and the measurement of the gas temperature distribution using the band spectrum intensity by the temperature distribution measurement program 17 stored in the storage unit 12. Central processing unit). The storage unit 12 is storage means capable of storing at least data and programs, and is, for example, a hard disk. The memory 15 serves as a memory space that is a work area when the control unit 11 executes various controls and operations, and is, for example, a RAM (abbreviation of Random Access Memory).

  The input unit 13 is an interface for giving at least an operator's command to the control unit 11, and is, for example, a keyboard.

  The display unit 14 performs drawing / display of characters, graphics, and the like under the control of the control unit 11 and is, for example, a display.

Then, by executing the temperature distribution measurement program 17, the control unit 11 of the temperature distribution measurement device 10 divides the measurement target cross section 21 a into a grid pattern and measures at least each grid of the grids measured by the light receiving unit 9. receiving an input of a band spectral intensity L _{_b} based on the emission intensity L of the gas in the grid array direction center position of the band spectral intensity L _{_b} and each column based on the emission intensity L of the gas in the arrangement direction center position of the squares Band spectrum intensity input receiving part 11a as means, average gas temperature calculating part 11c as means for calculating average gas temperature T _ex of measurement object cross section 21a based on gas combustion attribute, average gas temperature T _ex , center position of each square of the cross-cut using a band spectral intensity L _{_b} per stage, each column (i.e., the temperature measurement point) hand to calculate the gas temperature T of the And band spectral intensity sum calculating unit 11b and a temperature measurement point the gas temperature calculation unit 11d as is constructed.

In the present embodiment, the temperature distribution measuring program 17 for realizing the temperature distribution measuring method of the present invention in the temperature distribution measuring apparatus 10 includes the band spectrum intensity _{L_b} for each light receiving unit 9 as shown in FIG. A step of receiving an input (S1), a step of calculating a path sum of the band spectrum intensity _{L_b} in the measurement target cross section 21a (S2), a step of calculating an average gas temperature T _ex of the measurement target cross section 21a (S3), A step (S4) of calculating a gas temperature T for each temperature measurement point of the measurement object cross section 21a is executed.

  In executing the temperature distribution measuring method according to the present embodiment, first, the band spectrum intensity of each light receiving unit 9 in the measurement target cross section is input to the band spectrum intensity input receiving unit 11a of the control unit 11 (S1).

  Specifically, the band spectrum intensity of a specific wavelength for each light receiving part 9 as a result of spectral analysis by the spectral spectrum analyzer 6 based on the spontaneous light emission of the flame at the TP inlet cross section 21a received by each light receiving part 9 is the spectral spectrum. The signal is input from the analyzer 6 to the band spectrum intensity input receiving unit 11a.

  In the process of S1, band spectrum intensity of a specific wavelength (hereinafter referred to as a designated band) is used. Specifically, only the band spectrum intensity of the designated band may be input from the spectrum analyzer 6 to the band spectrum intensity input receiving unit 11a, or the band spectrum intensity input receiving unit 11a from the spectrum analyzer 6 may be input. Alternatively, the band spectrum intensity input receiving unit 11a may select and use only the band spectrum of the designated band from the spectrum intensities input by wavelength. Hereinafter, the band spectrum intensity of the designated band is referred to as the designated band intensity.

Here, the light emission intensity received by the light receiving unit 9A in FIG. 5 is expressed as L _{AA ′} , the light emission intensity received by the light receiving unit 9A ′ is expressed as L _A′A, and similarly, the light receiving units 9B, 9B ′, The light emission intensities received by 9C, 9C ′,..., 9H, 9H ′ are _{expressed as} L _{BB ′} , L _B′B , L _{CC ′} , L _C′C ,..., L _{HH ′} , L _H′H , respectively. The light emission intensity L _{AA ′} is specifically an integral value of the light emission intensity on the measurement line connecting the light receiving portions 9A and 9A ′, and the subject depth is measured over the entire depth of the TP entrance cross section 21a. The light emission intensity received by the light receiving unit 9A.

In the band spectrum intensity input receiving unit 11a, the emission intensity L _{AA ′ for} each of the light receiving units 9A, 9A ′, 9B, 9B ′,..., 9H, 9H ′ processed by the signal amplifier 5 and the spectral spectrum analyzer 6 is provided. , L _A′A , L _{BB ′} , L _B′B ,..., L _{HH ′} , L _H′H , the _value of the band spectrum intensity (at least the designated band intensity) is input.

The band spectrum intensity input receiving unit 11a emits light intensity L _{AA ′} , L _A′A , L _{BB ′} , L for each of the received light receiving units 9A, 9A ′, 9B, 9B ′,. _B'B, ..., L _HH ', specified band intensities for L _{H'H (hereinafter, L AA'_b, L A'A_b, L} BB'_b, L B'B_b, ..., L HH'_b, L _{H′H_b} respectively) is stored in the memory 15.

Further, in the present embodiment, the band spectrum intensity input receiving unit 11a further includes a subject depth from each light receiving unit 9 position that is two-thirds of the depth of the TP entrance cross section 21a (that is, 3 for each stage and each column). The value of the band spectrum intensity (at least the designated band intensity) measured by narrowing down to the second square from each light receiving unit 9 side of the square is input. For example, Cassegrain optical systems (for example, P.Kauranen, A.Andersson-Engels, and S.Svanberg, “Spatial mapping of flame radical emission using” a spectroscopic multi-colour imaging system ”, Applied Physics B 53, pp. 260-264, 1991). In the following, for example, the value of the designated band intensity measured by narrowing the subject depth from the light receiving unit 9A side to two-thirds of the depth of the TP entrance cross section 21a is represented as L _{A2 / 3_b,} and the light receiving unit 9A ′ side L _{A′2 / 3 — b} represents the value of the designated band intensity measured by _reducing the subject depth from 2 to 2/3 of the depth of the TP entrance cross section 21a.

The band spectrum intensity input receiving unit 11a emits light intensity L _{AA ′} , L _A′A , L _{BB ′} , L for each of the received light receiving units 9A, 9A ′, 9B, 9B ′,. _{B'B, ..., L HH ',} L H'H specified depth of field two-thirds of the band intensity _{L A2 /} 3_b _{about, L A'2 / 3_b, L B2} / 3_b, L B'2 / 3_b, ..., L _{H2 / 3_b} and L _{H'2 / 3_b} are stored in the memory 15.

  Next, the band spectrum intensity sum calculation unit 11b of the control unit 11 calculates the path sum of the band spectrum intensity in the cross section to be measured (S2).

The band spectrum intensity sum calculation unit 11b specifies designated band intensities L _{AA′_b} , L _{A′A_b} , L _{BB′_b} , L _{B′B_b} ,..., L _HH for the emission intensity stored in the memory 15 in the process of S1. _{' _b} and L _{H'H_b} are read from the memory 15, and the path sums L ₀₁ and L ₀₂ of the designated band intensity are calculated by Equations 2 and 3.
( _Expression 2) L ₀₁ = L _B — _b + L _E — _b + L _G — _b + L _H — _b
(Number _{3) L 02 = L A_b +} L B_b + L C_b + L D_b + L E_b + L F_b

Incidentally, L _{A_b,} L _{B_B} in Equations 2 and 3, ..., as the value of L _{H_b,} an average value of the specified band intensity L _{AA'_b} and L _{A'A_b} for specific example L _{A_b} ( L _{AA′_b} + L _{A′A_b} ) / 2 is used.

The band spectral intensity sum calculating unit 11b, each stage - Each column average value L _{A_b} specified band intensity, L _{B_B,} ..., L _{H_b,} and a path sum L _01, L ₀₂ specified band intensities in the memory 15 Remember.

  Next, the average gas temperature calculation part 11c of the control part 11 calculates the average gas temperature of a measurement object cross section (S3).

The average gas temperature T _ex of the TP inlet cross section 21a, which is the measurement target cross section, is calculated based on, for example, fuel flow rate, air flow rate, fuel temperature, air temperature, pressure, and the like. Since the calculation method of the average gas temperature of the cross section is a well-known technique, details are omitted here (for example, Harker, JH, “The Calculation of Equilibrium Flame Gas Compositions,”, Journal of The Institute of Fuel, Vol.40, No.316, pp.206-213, 1967).

  The average gas temperature calculation unit 11c displays a message on the display unit 14 requesting specification of attributes (values of various variables; hereinafter referred to as gas combustion attributes) necessary for calculating the average gas temperature of the cross section. Then, the combustion attribute of the gas input by the operator via the input unit 13 is read.

Then, the average gas temperature calculation unit 11 c calculates the average gas temperature T _ex of the TP inlet cross section 21 a and stores the calculated value in the memory 15.

  Next, the temperature measurement point gas temperature calculation unit 11d of the control unit 11 calculates the gas temperature for each temperature measurement point of the measurement target cross section (S4).

The gas temperatures at the temperature measurement points a1, a2, a3, b1, b2, b3, c1, c2, c3 for each grid divided in a grid pattern of the TP inlet cross section 21a of this embodiment shown in FIG. _{Let a1} , _Ta2 , _Ta3 , _Tb1 , _Tb2 , _Tb3 , _Tc1 , _Tc2 , and _Tc3 .

When the gas temperature at each temperature measurement point in the TP inlet cross section 21a is used, the average gas temperature T _ex is expressed as Equation 4.
(Expression 4) T _ex = (T _a1 + T _a2 + T _a3 + T _b1 + T _b2 + T _b3 + T _c1 + T _c2 + T _c3 ) / 9

Further, since there is a certain relationship between the band spectrum intensity and the gas temperature, the path sum L ₀₁ of the designated band intensity is expressed as Expression 5 when Expression 4 is substituted into Expression 2.
(Equation 5) L ₀₁ ∝T _ex + T _b2 × 3

Then, using a proportionality constant α for converting the band spectrum intensity into the gas temperature, Formula 5 is expressed as Formula 6.
(Equation 6) −T _b2 = (T _ex −α × L ₀₁ ) / 3

If L _{B — b} is used in Expression 6, Expression 7 is derived.
( _Equation 7) T _b1 + T _b3 = α × L _B — _b + (T _ex −α × L ₀₁ ) / 3

Here, the designated band intensity L _{B2 / 3_b} measured by narrowing the subject depth from the light receiving unit 9B side to two-thirds of the depth of the TP entrance cross section 21a and the subject depth from the light receiving unit 9B ′ side are represented as the TP entrance cross section. Since the difference with the designated band intensity L _{B′2 / 3 — b} measured by _{reducing the depth} to _21/3 of the depth of 21a _corresponds to the difference between the gas temperatures T _b1 and T _b3 , Equation 8 is established.
( _Equation 8) T _b1 −T _b3 = α × (L _{B2 / 3_b} −L _{B′2 / 3_b} )

Temperature measuring point gas temperature calculation unit 11d, each stage - Each column average value L _{A_b} the specified band intensity from the memory 15 in the processing of _{S2, L B_b, ..., L} H_b, and the path the sum of the specified band intensities The average gas temperature T _ex stored in the memory 15 in the process of L ₀₁ and S 3 is read from the memory 15. Then, the temperature measurement point gas temperature calculation unit 11d calculates the gas temperature T _b2 at the temperature measurement point b2 according to Equation 6, and the value T _b1 of T _b1 + T _b3 which is the sum of the gas temperatures at the temperature measurement points b1 and b3. ₊₃ is calculated by Equation 7.

Here, the proportionality constant α for converting the band spectrum intensity into the gas temperature is calculated from the relationship of Equation 9. Note that this proportionality constant α is assumed to be constant at each measurement time point in the measurement object cross section.
(Equation 9) T _ex = α × L _02/2

The temperature measurement point the gas temperature calculating unit 11d reads the specified band intensities of the stored depth of field two-thirds in the memory 15 L _{B2 / 3_B} and L _{B'2 / 3_B} from memory 15 in the processing of S1, temperature measurement A value T _b1-3 of T _b1 −T _b3 , which is the difference between the gas temperatures at the points b 1 and b 3, is calculated by Equation 8.

Then, the temperature measurement point gas temperature calculation unit 11d obtains the gas temperature T _b1 at the temperature measurement point _b1 by Equation 10 and obtains the gas temperature T _b3 at the temperature measurement point _b3 by Equation 11.
( _Equation 10) T _b1 = (T _{b1 + 3} + T _b1-3 ) / 2
( _Equation 11) T _b3 = (T _{b1 + 3} −T _b1-3 ) / 2

The temperature measurement point gas temperature calculation unit 11d obtains gas temperatures T _a1 , T _a2 , T _a3 , T _c1 , T _c2 , T _c3 for each temperature measurement point by the same procedure. Then, the temperature measurement point gas temperature calculation unit 11 d stores the obtained gas temperature value for each temperature measurement point in the memory 15.

Here, since there are nine unknown variables which are gas temperatures T _a1 , T _a2 , T _a3 , T _b1 , T _b2 , T _b3 , T _c1 , T _c2 , T _c3 for each temperature measurement point, these unknown variables If there are similarly nine expressions including known variables, the gas temperatures T _a1 ,..., T _c3 can be calculated. In the present embodiment, Equation 4 is one of the relational expressions, and the average gas temperature T _ex can be calculated and is a known variable. Therefore, there are only eight relational expressions including known variables, specifically, , Eight light receiving parts 9A, 9B, 9C, 9D, 9E, 9F, 9G, 9H (ie, the other eight light receiving parts 9A ′, 9B ′, 9C ′, 9D ′, 9E ′, 9F ′, 9G ′, Designated band intensities L _{AA'_b} , L _{BB'_b} , L _{CC'_b} , L _{DD'_b} , L _{EE'_b} , L _{FF'_b} , L _{GG'_b} , By using only L _{HH′_b} , nine gas temperatures T _a1 ,..., T _c3 can be calculated.

  On the other hand, in this embodiment, since there may be uneven temperature distribution in the measurement object cross section, in addition to the specified band intensity for the light emission intensity received by the eight light receiving portions 9A, 9B, 9C,. Further, the designated band intensity for the light emission intensity received by the eight light receiving units 9A ′, 9B ′, 9C ′,..., 9H ′ is further used, or the designated band intensity at the two thirds of the subject depth is further used. It is. Thereby, the measurement accuracy of gas temperature distribution can be improved.

Further, although not incorporated as a procedure in the present embodiment, since there is a certain relationship between the band spectrum intensity and the gas temperature, if Equation 4 is substituted into Equation 3, the luminous intensity path sum L ₀₂ is given by Equation 12. It is expressed as follows.
(Equation 12) L ₀₂ ∝T _ex × 18

When the proportional constant α ′ is used, Expression 12 is expressed as Expression 13.
(Expression 13) L ₀₂ = 1 / α ′ × T _ex × 18

  Furthermore, the measurement accuracy of the gas temperature distribution can be improved by obtaining the error due to the path length from Equation 6 and Equation 13.

Further, L ₀₃ and L ₀₄ are defined as Equation 14 and Equation 15, and by comparing these, the light intensity difference depending on the difference in the direction of light emission and reception and the proportional multiplier with the gas temperature in the gas temperature information are obtained. Thus, by obtaining the temperature difference, the measurement accuracy of the gas temperature distribution can be improved.
(Number _{14) L 03 = L _A +} L _B + L _C
(Number _{15) L 04 = L _D +} L _E + L _F

  In addition, although the above-mentioned form is an example of the suitable form of this invention, it is not limited to this, A various deformation | transformation implementation is possible in the range which does not deviate from the summary of this invention. For example, in the above-described embodiment, the case of measuring the temperature of the combustor exhaust gas 23 in the cross section 21a of the inlet of the transition piece 21 of the gas turbine has been described as an example, but the measurement is performed by the temperature distribution measuring method of the present invention. The object is not limited to this. For example, the temperature of the combustor exhaust gas 23 at the exit cross section of the transition piece 21 which is also the cross section of the inlet of the expansion turbine blade row CT may be measured. You may make it measure the temperature of the combustor exhaust gas 23 in the arbitrary cross sections from the entrance of the transition piece 21 to an exit. Furthermore, the measurement object in the present invention is not limited to the combustion gas in the gas turbine, and for example, the temperature of the combustion gas in the boiler may be measured.

In the above-described embodiment, in addition to the eight light receiving portions 9A, 9B, 9C,..., 9H, further eight light receiving portions 9A ′, 9B ′, 9C ′,. 9A, 9B, 9C,..., 9H, in addition to the designated band intensity for the light emission intensity received by the light receiving units 9A ′, 9B ′, 9C ′,. And a specified band intensity of 2/3 of the subject depth is used, but since there are nine unknown variables of gas temperatures T _a1 ,..., T _c3 at each temperature measurement point, between these unknown variables The gas temperatures T _a1 ,..., T _c3 can be calculated as long as there are at least nine equations including known variables. Further, the average gas temperature T _ex with established relationship such as Equation 4 between the average gas temperature T _ex measurement target section as the gas temperature of the temperature for each measurement point may be calculated by known methods. Therefore, when the cross section to be measured is divided into [m stages × n columns] grids and the number of temperature measurement points is [m × n] (however, both m and n are 3 or more) Integer), the measurement line penetrates the center of n cells in each stage to measure self-emission, and the measurement line penetrates the center of m cells in each row to measure self-emission. In addition, [m × n] light receiving units are installed (and the entire depth of the measurement target cross section is measured as the subject depth), and the separately calculated average gas temperature T _ex of the measurement target cross section is used. Then, the gas temperature can be calculated. Further, in order to improve the temperature measurement accuracy even when the temperature distribution of the cross section to be measured is uneven as in the present embodiment, a light receiving unit facing the [m × n] light receiving units is further installed as necessary. Then, the emission intensity may be measured, or the depth of the measurement object cross section, for example, 2 / m or 2 / n may be further measured as the subject depth.

  Further, in the above-described embodiment, the gas temperature is calculated from the designated band intensity with respect to the emission intensity using Equations 2 to 11, but in the present invention, the method / procedure for calculating the gas temperature from the designated band intensity is used. Is not limited to this. In the above-described embodiment, if at least the relational expression between the total gas temperature and the average gas temperature at each temperature measurement point of the measurement object cross section expressed as Expression 4 is used, another relational expression different from the remaining expression is used. It may be used. Note that the proportionality constant α is calculated using Equation 9 in the above-described embodiment if it is not obtained by experiment as described below.

  In the above-described embodiment, the band spectrum intensity of a single designated band is used. However, the present invention is not limited to this, and the plurality of kinds of band spectrum intensities of a plurality of kinds of designated bands are used according to the fuel composition. The gas temperature at the temperature measurement point may be obtained for each designated band, and for example, the average value of these may be used as the measurement temperature. Thereby, gas temperature can be evaluated more correctly.

In the above-described embodiment, specific examples of the specific wavelength of the band spectrum intensity used in the relationship between the band spectrum intensity and the flame temperature include OH radical, CH radical, and C ₂ radical. The specific wavelength of the band spectrum intensity used is not limited to these, and band spectrum intensity of other wavelengths may be used.

  In the above-described embodiment, the proportionality constant α for converting the band spectrum intensity into the temperature is calculated from the relationship of Equation 9, but the proportionality constant α may be obtained by experiment.

  In the above-described embodiment, the light receiving unit 9 of the optical fiber cable 4 is arranged at the peripheral edge of the entrance of the transition piece 21, and the light received by the light receiving unit 9 is transmitted by the optical fiber cable 4 to the spectral spectrum analyzer 6. To the camera 6b. This is because the vicinity of the entrance of the transition piece 21 is a high temperature field, and it is not preferable to directly arrange the cameras. Therefore, if there is no problem even at high temperatures due to heat resistance specifications, the optical fiber cable 4 is not used, and the output corresponding to the energy of light such as a camera is provided at the periphery of the entrance of the transition piece 21. A device for generating a signal may be directly arranged.

DESCRIPTION OF SYMBOLS 10 Temperature distribution measuring apparatus 11 Control part 12 Storage part 13 Input part 14 Display part 15 Memory 17 Temperature distribution measurement program

Claims (12)

  The cross section to be measured is divided into a grid pattern, and the emission intensity of the gas at the center position of the grid in each row of the grid is measured, and the gas at the center position of the grid in each column is measured. Measure the emission intensity, obtain the band spectrum intensity for each stage and each column based on these emission intensity, calculate the average gas temperature of the cross section to be measured based on the combustion attribute of the gas, the average gas temperature And calculating the gas temperature at the center position of each square of the grid by using the band spectrum intensity for each stage and each column.   The emission intensity of the gas is measured from both sides of the grid in each row of the grid and from both sides of the grid in each row. Temperature distribution measurement method. _2. The temperature distribution measuring method according to claim 1, wherein the band spectrum intensity is any one of an OH radical, a CH radical, and a C2 radical.   The temperature distribution measuring method according to claim 1, wherein the cross section to be measured is an arbitrary cross section of a transition piece of a gas turbine.   The band spectrum intensity based on the emission intensity of the gas at the center position of the grid in each row of the grid and the center of the grid in each row measured by dividing the cross section of the measurement object into a grid. Means for receiving an input of a band spectrum intensity based on the emission intensity of the gas at a position; means for calculating an average gas temperature of the cross section to be measured based on a combustion attribute of the gas; A temperature distribution measuring apparatus comprising: means for calculating a gas temperature at a central position of each grid of the grid using the band spectrum intensity for each column.   The emission intensity of the gas is measured from both sides of the grid in each row of the grid and is measured from both sides of the grid in each row. The temperature distribution measuring apparatus according to claim 5. 6. The temperature distribution measuring apparatus according to claim 5, wherein the band spectrum intensity is any one of OH radical, CH radical, and C ₂ radical.   The temperature distribution measuring device according to claim 5, wherein the cross section to be measured is an arbitrary cross section of a transition piece of a gas turbine.   A program for causing a computer to calculate a gas temperature in a cross section to be measured, the grid being arranged in a grid pattern for each stage of the grid, which is measured by dividing the cross section to be measured into a grid pattern Based on the process of receiving the input of the band spectrum intensity based on the emission intensity of the gas at the center position and the band spectrum intensity based on the emission intensity of the gas at the center position in the arrangement direction of the cells for each column, and the combustion attribute of the gas The gas temperature at the center position of each grid of the grid is calculated using the process of calculating the average gas temperature of the cross section to be measured, and the average gas temperature and the band spectrum intensity for each stage / column. A temperature distribution measuring program for causing a computer to perform processing.   The emission intensity of the gas is measured from both sides of the grid in each row of the grid and is measured from both sides of the grid in each row. The temperature distribution measuring program according to claim 9. The temperature distribution measurement program according to claim 9, wherein the band spectrum intensity is any one of OH radical, CH radical, or C ₂ radical.   The temperature distribution measurement program according to claim 9, wherein the cross section to be measured is an arbitrary cross section of a transition piece of a gas turbine.

Images