CN102445283B - The hot gas temperature using tunable diode laser in combustion gas turbine is measured - Google Patents

Abstract

The hot gas temperature that the present invention relates to use in combustion gas turbine tunable diode laser is measured, specifically, relate to a kind of burning gases measurement apparatus being arranged in combustion gas turbine, this measurement apparatus includes: tunable laser, and it generates the radiant flux of the burning gases path in combustion gas turbine；Controller, it is for tunable laser and is tuned laser instrument at least having first and select wavelength and second to launch and select the radiation of wavelength, both of which, corresponding to the transformation varied with temperature of combustible substance of gas, wherein first is selected wavelength and second and is selected wavelength not near the absworption peak of adjacent wavelength；Detector, its sensing is through the radiant flux of burning gases and generates instruction each in first wave length and second wave length of burning gases absorption signal to the absorption of this bundle；And controller, it performs ratio based on the absorption signal to first wave length and second wave length and determines the program being stored on non-transitory storage medium of burning gas temperature.

Description

The hot gas temperature using tunable diode laser in combustion gas turbine is measured

Technical field

The present invention relates to use tunable laser to determine hot gas temperature, and particularly relate to determine in combustion gas turbine High-pressure combustion gas temperature.

Background technology

Burning gas temperature in combustion gas turbine is difficult to be accurately determined.Burning gases are very hot, be corrosive, disturbance and Under high pressure.Burning gas temperature such as turbine firing temperature (Tfire) is typically based on such as delivery temperature and compressor row Atmospheric pressure etc because usually estimating.This estimation of burning gas temperature has a certain degree of uncertainty.In order to compensate This uncertainty, if be set below by burning gas temperature, ignition temperature is known has bigger uncertainty, can need The temperature wanted.

Burning gas temperature affects the power output of combustion gas turbine.Power increases along with burning gas temperature and increases. Such as, for the combustion gas turbine of 200 megawatts (200MW), making burning gas temperature (Tfire) raise 10 degrees Fahrenheits can Increase power one megawatt (1MW) of output.Reducing uncertainty degree can allow burning gas temperature raise and cause combustion gas turbine The corresponding increase of power output.

Have pointed out spectral measurement such as laser measurement to the gas temperature being accurately determined in combustion gas turbine.International monopoly Application WO 2007/014960 describes a kind of temperature measuring equipment, its measure be in in the combustion-gas flow of combustion gas turbine The absorption of the laser under the wavelength that oxygen is corresponding.U.S. Patent Application Publication 2008/0289342 describe by measure with The absorption of the laser of the wavelength that oxygen in the air-flow of combustion gas turbine is corresponding determines ignition temperature.

Measure the optical maser wavelength residing for absorbing due to burning gases and should be chosen to the computational accuracy of optimization gas temperature.Survey Wavelength residing for amount absorption is generally selected to corresponding with the transformation varied with temperature of the material in gas.Exist some available Wavelength, absorbs due to the transformation varied with temperature of burning gases material at these wavelength.A kind of method is needed to select Select a pair wavelength, at this, wavelength measurement laser absorption is used for accurately calculating the burning gas temperature in combustion gas turbine to obtain Absorption line strengths data.

Summary of the invention

Have been developed for a kind of firing temperature for accurately measuring in combustion gas turbine or other hot gas temperature is System and method.Tunable diode laser guided laser bundle is by flowing through the burning gases of combustion gas turbine.Radiation sensor Measure and changing the radiation suction occurred at corresponding wavelength with a pair steam harmonic wave (overtone) near infrared band Receive.The temperature of ratio calculation burning gases based on the absorption measured at the two wavelength.This wavelength is relatively isolated and Nigh wavelength does not have adjacent strong absorption line.Isolation and the shortage of adjacent absorption intensity spectral line avoid in combustion gas The merging of the adjacent strong absorption intensity spectral line occurred under the high pressure in turbine.

Disclosing a kind of burning gases measurement apparatus being arranged in combustion gas turbine, this measurement apparatus includes: tunable Laser instrument, it generates the radiant flux of the burning gases path in combustion gas turbine；Controller, it is used for tunable laser And tuned laser at least has first and selectes wavelength and second to launch and select the radiation of wavelength, first selectes wavelength and second The transformation that selected wavelength both of which varies with temperature corresponding to the combustible substance of gas, wherein first selectes wavelength and second and selectes Wavelength is not near the absworption peak of adjacent wavelength；Detector, its sensing is through the radiant flux of burning gases and generates instruction burning The absorption signal of the absorption of halved tie at each in first wave length and second wave length of gas；And processor, it performs base What the ratio in the absorption signal to first wave length and second wave length determined burning gas temperature is stored in non-transitory storage medium On program.

Disclosing a kind of burning gases measurement apparatus being arranged in combustion gas turbine, this measurement apparatus includes: tunable Diode laser, it launches the laser beam of the burning gases path in combustion gas turbine；Controller, it is used for being tuned Tunable diode laser with the first laser beam of a length of 1334 nanometers of transmitted wave (nm) and wavelength as 1380nm or Second laser beam of 1391nm；The laser beam of the laser beam of transmitted wave a length of 1334nm and 1380nm or 1391nm；Laser Sensor, its sensing is through each radiant flux of burning gases and generates the suction to the absorption of this bundle at each wavelength of the instruction burning gases The collection of letters number；And processor, it performs ratio based on the first laser beam and the absorption signal of the second laser beam and determines combustion gas The program being stored on non-transitory storage medium of temperature.

A kind of method disclosing burning gas temperature for calculating in environment under high pressure, the method includes: identifies and fires Burn the intensity spectral line that the temperature relevant transition of the material in gas is associated；Identify with the combustible substance of burning gases with temperature The intensity spectral line that the transformation of degree change is correlated with；Selected as the last the first and second intensity spectrum identified relatively with combustible substance Line, wherein selected in strong intensity spectral line two do not have adjacent intensity spectral line；Identify each respectively with first and second First wave length that intense line is associated and second wave length；By be in the first and second wavelength of identifying each under laser Bundle is projected through burning gases path, and collect with burning gases under each of the first and second wavelength identified to this That restraints absorbs relevant data；And use the data collected to calculate burning gas temperature.

Accompanying drawing explanation

Fig. 1 is the schematic diagram of combustion gas turbine.

Fig. 2 is the cross section of the joint between burner and the turbine of the combustion gas turbine shown in Fig. 1.

Fig. 3 and 4 shows the burning gases laser spoke to the radiative frequency span from 7200/cm to 7207/cm wavelength Penetrate the chart of absorption.

Fig. 5 and 6 shows burning gases in the various wavelength example chart to the intensity of spectral line of laser absorption.

Fig. 7 and 8 shows burning gases in the various wavelength example chart to the intensity of spectral line of laser absorption.

Fig. 9 and 10 shows for using tunable diode laser to determine the mistake of illustrative methods of ignition temperature Journey chart.

Parts list

10 combustion gas turbines

12 compressors

14 burners

16 combustion tubes

18 turbines

20 controllers

22 laser instrument and sensor cluster

23 fuel-control units

The shell of 24 combustion gas turbines

Port on 26 shells

The axle of 28 assemblies

30 gas flow paths

32 thes tip of the axis

34 laser

38 first stators

40 first turbine vanes

100 test burning gases

102 identify the intensity spectral line relevant to the temperature relevant transition of the material of burning gases

104 find out the intensity spectrum line-group group relevant to same substance

106 identify the intensity spectral line pair in the group without adjacent intensity spectral line

108 identify the wavelength without intensity spectral line

Laser instrument and sensor cluster are arranged in combustion gas turbine by 110

112 service datas collecting combustion gas turbine

114 calculate gas temperature

Detailed description of the invention

Fig. 1 is to have compressor 12, start with the burner 14 of combustion tube 16 and the industrial gas turbine of turbine 18 The schematic diagram of machine 10.Air enters axial compressor 12, and this axial compressor 12 is to air pressurized and is discharged to form combustion The annular array of the combustion tube 16 of burner.The heat that air and fuel mixture are ignited in combustion tube and are formed by burning Gas flows into turbine 18.Hot combustion gas 15 enters turbine 16 annular array flowing through first order stator vane and first order whirlpool The annular array of wheel wheel blade.Hot burning gas stream flows through multiple rows of annular array turbine vane, revolving wormgear wheel blade and be also connected to pressure The axle being associated on contracting machine.Turbine rotary compressor causes compressor to the air pressurized for burner.

The temperature of the hot combustion gas entering turbine is commonly referred to firing temperature (Tfire).This firing temperature may be defined as Such as in the burning gases stream of the trailing edge of the first stator and the edge of the first turbine vane, turbine is started working the gas at place Temperature.

Controller 20, such as, with non-transitory storage medium and the computer of processor, receive from laser instrument and sensing The wavelength absorption data of device assembly 22, these data are used for calculating burning gas temperature.Controller uses the combustion gas body temperature calculated Degree controls combustion gas turbine, such as by regulation fuel control unit 23 and the entry guide vane leading to compressor 12.Controller Also use the data that the burning gas temperature output calculated is relevant with the performance of combustion gas turbine.

Fig. 2 corresponds to lead to the sectional view amplifying section of the combustion gas turbine 10 of the import of turbine 16, this amplification region Section is close to the trailing edge of first row stator and the leading edge of first row turbine vane.The shell 24 of combustion gas turbine 10 has and is generally used for Insert inspection Kong Yi to check the port 26 of the internals such as turbine vane and stator of combustion gas turbine.

Port 26 provide monitor from combustor flow to and flow through the laser instrument of burning gases and the sensor cluster 22 of turbine Entrance.Laser instrument and sensor cluster 22 are arranged on the shell 24 of combustion gas turbine or wherein and extend through borehole port 26.The axle 28 of laser instrument and sensor cluster 22 extends through one of them port 26 on shell and extends to gas flow path 30 Periphery.

Light path such as optical fiber or electric wire is had with in the inner 32 of axle and relevant to laser instrument and sensor cluster 22 in axle 28 Laser or the signal of telecommunication is transmitted between electronic-controlled installation and the sensing circuit of connection.End 32 can include being connected respectively to electrical signal line On laser diode and diode-transducer.Laser diode projection is through a branch of radiation 34 of burning gases stream 30.Two Pole tube sensor receives bundle 34 after gas flow path at bundle 34 and generates the intensity such as brightness of this bundle of instruction (intensity) signal.

End 32 can be directed at the close clearance between the first stator 38 and the first turbine vane 40 and be positioned at by this At the periphery of the stream 30 in gap.Laser 34 is radially-inwardly projected through this stream and adjacent with this stream radially inner The radiation detector being positioned at end 32, such as optical pickocff or optical fiber is reflected back on surface.Laser 34 can be from turbine Axle reflects.

Replacing reflection laser, one countershaft 28 can insert at different inspection hole instrument ports 26, and this port 26 can be in combustion gas whirlpool Axially align on the shell 24 of turbine, and be located so that each the tip of the axis 32 is along extending through regarding of this gas passage Line.Laser 34 is positioned at another end from the first end projection and photo-detector or light acquisition equipment such as optical fiber.Additionally, it is many Individual axle 28 (or how countershaft) can extend across inspection hole instrument ports different in the shell of combustion gas turbine or other opening, with at gas Various positions in body stream monitor gas temperature.

Tunable diode laser and sensor cluster 22 can be conventional system, and it has tunable diode laser light Source, the transmission optics of such as beam shaping, the optics receiving laser beam and the detector of such as photodiode etc. Laser diode is tuned by the electronic circuit being associated with assembly 22 and computer control, with by laser in wavelength characteristic Radiation emission wavelength via changes into the absorbing wavelength of some combustible substance of the burning gases of such as steam etc.

The absorption of radiation launched from laser instrument reduces the brightness of laser beam and this brightness reduces by detector measurement. Detector generates the line strength signal of the absorbtivity of the wavelength indicating this radiation to be launched at laser instrument.Line strength signal is defeated Going out to computer 20 or other processing unit, it uses this signal to determine burning gas temperature.Computer 20 can with to laser instrument The computer that laser instrument in assembly 22 is tuned separates or combines.

Tunable diode laser be wherein can the ultraviolet of spectrum, visible and region of ultra-red part or all On laser instrument that the frequency of output radiation is tuned.Can select tunable based on the wave-length coverage performing tuning thereon Diode laser.The representative instance of diode laser is that InGaAsP/InP (can adjust in the scope of 900nm to 1.6 μm Humorous) and InGaAsP/InAsP (can be tuned to the scope of 2.2 μm in 1.6 μm).Can be by regulating the temperature of diode laser Diode laser is tuned by the injected current density in the gain media of degree or injection laser.

Optical sensor for laser instrument and sensor cluster 22 uses conventional absorption spectroscopy techniques to measure to laser Radiation absorption under the various wavelength launched when device is tuned.Along with laser radiation such as light is through burning gases, gas In combustible substance absorb radiation some wavelength.Additionally, the absorbtivity that the temperature impact of gas occurs.

Under selected wavelength, Laser Measurement device radiation absorption provides the data that can be used for calculating the temperature of burning gases. Particularly, it is possible to from the temperature of the ratio derivation gas of the absorption of the laser radiation measured under two wavelength, each wavelength The transformation varied with temperature corresponding to the composition (material) of gas.

The wavelength that the selected wavelength of laser radiation changes corresponding to the steam occurred in burning gases.Based on through stream Laser emission measurement the intensity of spectral line under the wavelength that the two is selected through the compressed burning gases of combustion gas turbine.When right Laser diode be tuned with each selected wavelength radial time base alternatively on this simultaneously at two selected ripples Absorption line strengths is measured under length.

The ratio of two absorption line strengths is in a usual manner for calculating the temperature of burning gases.Tunable two can be used Pole pipe laser absorption spectrum (TDLAS) commercial measurement absorption line strengths also calculates burning gas temperature.Especially, by wavelength It is chosen to corresponding to two kinds of water vapor overtone in near-infrared section.Can be based on corresponding to two kinds of water vapor overtone The ratio absorbed that measures of wavelength calculates the temperature of burning gases.

Measure and absorb to determine that the wavelength residing for burning gas temperature is chosen such that i.e. so that they correspond to water Steam carry out absorb and do not have absorb its reach peak value near wavelength.Select the ripple away from other absworption peak wavelength Length ensure that selected wavelength will not raise along with gas pressure and merge with adjacent absworption peak.

For the application in internal combustion (IC) electromotor of such as combustion gas turbine etc, (the collision exhibition of variable pressure broadening Wide) make absorptiometry become complicated and cause to absorb to change and adjacent transformation in various degree overlapping.Typical water steam changes Collision broadening be γ_air, it is about 0.05cm-1/atm at 300k.If candidate's optical maser wavelength has phase in 2.5cm-1 Adjacent transformation, then will exist the most overlapping in IC under high combustion pressure.Overlapping (interference) degree depends at electromotor Relative line intensities during P/T circulation.Simplest choice of spectrum method will not have closest in being only remained in 2.5cm-1 The spectral line of adjacent line.

Fig. 3 and 4 show burning gases from the radiative frequency span of 7200/cm to 7207/cm wavelength to laser spoke The chart of the absorption penetrated.As shown in Figure 3, when gas pressure is 10 atmospheric pressure (ATM), strong absorption line (peak) occurs in 7204/cm (corresponding to the wavelength of 1388 nanometers (nm)) and neighbouring less spectral line occur at 7205/cm.Fig. 4 shows Along with gas pressure rises to 30ATM, two absorption lines launch and merge.Absorption line raises along with gas pressure and merges Due to absorption line wherein one and make the certainty of measurement of absorption decline.

Measuring for the typical Tfire in combustion gas turbine, combustion pressure is about 15 atmospheric pressure (15atm).Typical case The collision broadening that steam changes is γ_air, it is of about 0.05cm-1/atm at 300k.At 15atm, steam changes Halfwidth (FWHM) will change 0.75cm-1.This will not cause spectral line in any merging of high pressure.

Fig. 5 and 6 shows the burning gases example chart to the intensity of spectral line of the absorption of laser under various wavelength. The pressure of gas is in the example shown in Fig. 5 and 6 being 1 atmospheric pressure (atm).Fig. 5 shows at 7495/cm (1334nm) With the strong absorption line at a temperature of 2000 degree Kelvins (K) (1727 DEG C and 3140.6 °F).Model at 7490/cm to 7515/cm The adjacent wavelength with absorption line is there is not in enclosing.Fig. 6 shows the strong absorption line under 7243/cm (1380nm).

Wavelength is to (i) 7495/cm (1334nm) and 7243/cm (1380nm) and (ii) 7495/cm and 7185/cm (1391nm) correspond to the water vapor overtone in near-infrared and not there is the adjacent absorbent spectral line caused interference with.

Fig. 5 shows insignificant the intensity of spectral line under ambient temperature (296K), and it represents that ambient temperature will not produce shadow Ring interference or the noise of the temperature computation of burning gases.As shown in Figure 7, the absorption line strengths under 133nm wavelength is with temperature Degree increases.

Fig. 6 shows the strong absorption line strengths under the wavelength, ambient temperature (296K) of 7243/cm and 2000K's At a temperature of nominal the intensity of spectral line.Absorption at 7243/cm (1380nm) wavelength changes on the contrary with temperature.

The intensity of spectral line [cm-2atm-1] varied with temperature can carry out table according to the known the intensity of spectral line under fiducial temperature T0 Reach:

$S\left(T\right)=S\left(T_0\right)\frac{Q\left(T_0\right)}{Q\left(T\right)}\left(\frac{T_0}{T}\right)\exp [-\frac{{\mathrm{hcE}}^{\′\′}}{k}(\frac{1}{T}-\frac{1}{T_0})][1-\exp \left(\frac{-{\mathrm{hcv}}_0}{\mathrm{kT}}\right)]{[1-\exp \left(\frac{-{\mathrm{hcv}}_0}{k{T}_0}\right)]}^{-1}$

Wherein Q (T) is molecular partition function, and h [Jsec] is Planck's constant, and c [cm/s] is the light velocity, and k [J/K] is bohr The most graceful constant, and E " [cm-1] be relatively low-energy state.

Temperature can be derived from the ratio that the integration that the transformation varied with temperature different to two is measured absorbs.

$R=\frac{\∫P_{\mathrm{abs}}L{\mathrm{\Φ}}_{v1}{S}_1\left(T\right)\mathrm{dv}}{\∫P_{\mathrm{abs}}L{\mathrm{\Φ}}_{v2}{S}_2\left(T\right)\mathrm{dv}}=\frac{S_1\left(T\right)}{S_2\left(T\right)}=\frac{S(T_0,v_1)}{S(T_0,v_2)}\exp [-\left(\frac{\mathrm{hc}}{k}\right)(E_1^{\′\′}-E_2^{\′\′})(\frac{1}{T}-\frac{1}{T_0})]$

Wherein Pabs [atm] is the local pressure of absorbing material, and φ v [cm] is the linear function of special transition, S (T0, Vi) it is at the intensity of spectral line of the transformation at vi [cm-1] place, E for fiducial temperature T0 center " it is relatively low state energy [cm-1] and T For gas temperature [K].

The relative sensitivity of temperature is obtained by above ratio by following formula:

$\mathrm{\σ}=\left|\frac{\mathrm{dR}/R}{\mathrm{dT}/T}\right|=\left(\frac{\mathrm{hc}}{k}\right)\frac{\left|(E_1^{\′\′}-E_2^{\′\′})\right|}{T}$

Can be seen that from above formula, it is desirable to the high spectral line of relatively low state difference is to having high temperature sensitivity.

In the example illustrated in figs. 5 and 6, the temperature range for 1500K to 2000K (2240 °F to 3140 °F) is sensitive Degree (6) is 5.71.

High sensitive level represents that the thermometric precision that a pair wavelength 1334nm and 1380nm of use is carried out should be big About 0.35%, it is corresponding to the error of only 9 degrees Fahrenheits under 2500 degrees Fahrenheits.

Fig. 7 (it is identical with Fig. 5) and 8 shows the intensity of spectral line of burning gases laser absorption under various wavelength Example chart.Fig. 7 shows in 7495/cm (1334nm) and the temperature of 2000 degree Kelvins (K) (1727 DEG C and 3140.6 °F) Under strong absorption line.The adjacent wavelength with absorption line is there is not in the range of 7490/cm to 7515/cm.Fig. 8 illustrates Strong absorption line at 7185/cm (1391nm).

Although Fig. 8 existing near 7185cm-1 another absorption line, but the intensity of spectral line of this another spectral line being little. Guarantee that thermometric standard is that Two change has similar signal to noise ratio (SNR).Assume that minimum detectable absorbance is 2E- 4 and SNR is 10, then peak absorbance have to be larger than 2E-3.Assume that pressure is 15atm and path-length is 1cm, then in Fig. 8 The spectral line (band pressure broadening) of 7185cm-1 will not significantly affect thermometric precision.

Fig. 8 shows the strong absorption line strengths under 7185/cm (1391nm), ambient temperature (296K) and at 2000K At a temperature of nominal the intensity of spectral line.Absorption at 7185/cm (1391nm) wavelength changes on the contrary with temperature.

In the example illustrated in figures 7 and 8, the temperature range for 1500K to 2000K (2240 °F to 3140 °F) is sensitive Degree (6) is 3.91.This high sensitive level represents the thermometric precision that a pair wavelength 1334nm and 1391nm of use is carried out Should be within 15 degrees Fahrenheits under 2500 degrees Fahrenheits.

Can by the diode laser in laser instrument and sensor cluster 22 be tuned to the 3rd wavelength, such as 635nm, it is not Corresponding to the wavelength absorbed by burning gases.Be usable in the line strength signal of the 3rd wavelength detection as indication laser and The transparency of the optics in sensor cluster 22 and the detection in the end 32 that laser beam is reflected back into assembly 22 The benchmark of the reflectance on the turbine wheel shaft of device or other surface.

Fig. 9 and 10 is for arranging tunable laser system to measure ignition temperature and to measure the exemplary of ignition temperature The flow chart of method.Can be presented as and be stored in, for measuring the part of the method for ignition temperature, the non-provisional that can be accessed by processor The instruction in the computer program in computer 27 on storage medium or shown in Fig. 2.

In step 100, identical or substantially similar burning gases are tested to identify by burning gases such as combustible substance The wavelength of the radiation absorbed.Can be such as one atmospheric pressure (ATM) of low-pressure or be similar to the pressure of Compressor Discharge Pressure Such as test burning gases under 20ATM to 30ATM.Test avoids the absorption tending to occur at elevated pressures at low pressures The merging of intensity spectral line.Absorption line can be identified in the combustor of laboratory.Tunable diode laser can be used to scan The wavelength of proper range with obtain with by the material in burning gases in the relevant data of its lower wavelength that absorption occurs.

In a step 102, evaluate data relevant with the absorption intensity spectral line obtained in a step 101 with identification corresponding to The intensity spectral line of the material in the burning gases of experience temperature relevant transition.Such as, steam is that experience temperature is relevant with oxygen The material of the burning gases changed.The ordinary skill people in burning gases field in combustion field, especially combustion gas turbine Member will have sufficient knowledge and training with which absorption intensity spectral line of determining in data corresponding to the material of burning gases The transformation varied with temperature.

From the intensity spectral line identified in a step 102, find out at step 104 and be associated with identical burning gases material The group of intensity spectral line, such as, intensity spectral line pair.Evaluate the intensity spectral line in a group in step 106, to identify it In every spectral line the most not there is a pair spectral line of adjacent intensity spectral line.Such as, a pair 1334nm and 1380nm and 1334nm With the wavelength of 1391nm, there is due to the transformation varied with temperature of steam the strong absorption line being associated and do not exist Adjacent strong absorption line.

At step 104, determine in the intensity spectral line identified in a step 102, which is away from adjacent intensity spectral line.Choosing The wavelength selecting the intensity spectral line without adjacent intensity spectral line corresponding to identifying at step 104 is measured as under it Absorption is to calculate the wavelength pair of the temperature of burning gases.In step 108, identify with intensity spectral line, particularly vary with temperature The incoherent wavelength of intensity spectral line.

In step 110, laser instrument and sensor cluster are arranged in combustion gas turbine make tunable laser two Pole pipe gas passage radiation laser beam in combustion gas turbine.Between this laser beam can be between the first stator and the first turbine Gap, directly to collect absorption data from the position of Tfire temperature.

In step 112 and during combustion gas turbine operating, laser instrument and sensor cluster are by through combustion gas turbine Project laser beam and collect absorption data, wherein by laser tuning to the wavelength selected in step 106.The tuning of laser instrument Can be making wavelength periodically and being quickly changed in step 106 and 108 wavelength selected of circulation.Data collection will be absorbed And be stored in the storage medium relevant to the controller in laser instrument and detector assembly.In step 114, at laser instrument and Detector assembly or for combustion gas turbine controller in process absorb data, with based on be in step 106 identify two The ratio (absorption data) of the intensity of spectral line that individual wavelength obtains calculates burning gas temperature.Additionally, laser instrument and detector assembly The absorption data using the wavelength identified in step 108 to collect do not have, as instruction, the absorption that the material of burning gases is carried out The benchmark of intensity spectral line signal.Controller for combustion gas turbine uses the burning gas temperature calculated to control combustion gas whirlpool Turbine also generates the report relevant with the performance of combustion gas turbine.

It is presently considered to the most practical also most preferred embodiment although having combined invention has been described, but should manage Solving, the present invention is not limited to the disclosed embodiments, but is intended instead to contain and is included in claims Various modification in scope and equivalence are arranged.

Claims (15)

1. being arranged on the burning gases measurement apparatus in combustion gas turbine (10), this measurement apparatus includes:

Tunable laser, it generates the radiant flux (34) of the burning gases path in described combustion gas turbine (10)；

Controller, it is for described tunable laser and described laser instrument is tuned (100) at least has the to launch One selectes wavelength and second selectes the radiation of wavelength, and described first selectes wavelength and described second selectes wavelength both of which and correspond to The transformation (102) varied with temperature of the combustible substance of described burning gases, wherein said first selectes wavelength and described second Selected wavelength does not have the adjacent wavelength (104) corresponding to absorption intensity line；

Detector, it senses (100,112) and through the described radiant flux of described burning gases and generates instruction by described combustion gas Body selectes wavelength and the absorption signal of absorption that described second each halved tie selecting in wavelength is carried out described first, and

Processor, its execution is stored on non-transitory storage medium and selectes wavelength and described second based on to described first The ratio of the absorption signal of selected wavelength determines the program of (114) burning gas temperature.

Burning gases measurement apparatus the most according to claim 1, it is characterised in that described first to select wavelength be 1334 to receive Wavelength selected by rice (nm) and described second is 1380nm or 1391nm.

Burning gases measurement apparatus the most according to claim 1, it is characterised in that described combustible substance is steam.

Burning gases measurement apparatus the most according to claim 1, it is characterised in that described tunable laser (22) is installed In described combustion gas turbine (10) so that described radiant flux is through first turbine stator (38) and of described combustion gas turbine Gas passage (30) between one turbine vane (40).

Burning gases measurement apparatus the most according to claim 1, it is characterised in that described tunable laser (22) is can Tuning diode laser instrument.

Burning gases measurement apparatus the most according to claim 1, it is characterised in that described radiant flux is from described gas turbine The surface reflection of the turbine of machine.

7. being arranged on the burning gases measurement apparatus in combustion gas turbine (10), this measurement apparatus includes:

Tunable diode laser (22), swashing of its transmitting burning gases path in (110) described combustion gas turbine Light beam, described tunable diode laser tuned (100,102) with transmitted wave length be in 1334 nanometers (nm) first swash Light beam and wavelength are in second laser beam of 1380nm or 1391nm；

Laser sensor (22), its sensing (100) described first laser beam and second laser beam, each laser beam is through described combustion Burning gas, described laser sensor generates instruction to be believed the first absorption of the absorption that the first laser beam is carried out by described burning gases Number (112) and the second absorption signal to the absorption that the second laser beam is carried out, and

Controller (20), it performs to be stored on non-transitory storage medium and based on described first laser beam and described second The ratio of the first and second absorption signals of laser beam determines the program of (114) burning gas temperature.

Burning gases measurement apparatus the most according to claim 7, it is characterised in that described tunable diode laser (22) the first turbine stator (38) making described laser beam through described combustion gas turbine it is arranged in described combustion gas turbine And the gas passage (30) that first between turbine vane (40).

Burning gases measurement apparatus the most according to claim 7, it is characterised in that radiant flux is from described combustion gas turbine The surface reflection of turbine.

10., for the method calculating the burning gas temperature in environment under high pressure, described method includes:

Identify the intensity spectral line relevant to the temperature relevant transition of the material in burning gases；

Identify the intensity spectral line relevant to the transformation varied with temperature of the combustible substance of described burning gases；

Selecting to be identified as the first and second intensity spectral lines relevant to described combustible substance, two wherein selected intensity spectral lines are not There is adjacent intensity spectral line；

Identify each the most respectively with first wave length and the second wave length of described first and second intensity spectral line correlations；

First and the is projected respectively through burning gases path under each wavelength in the first wave length identified and second wave length Dual-laser bundle, and collect and by described burning gases under each wavelength in the first wave length and second wave length of described identification Carry out described first and second laser beams absorbs relevant absorption signal data, and

The ratio calculation of described absorption signal data based on described first and second laser beams determines burning gas temperature.

11. methods according to claim 10, it is characterised in that described first wave length is 1334 nanometers (nm) and described Two wavelength are 1380nm or 1391nm.

12. methods according to claim 10, it is characterised in that use the data collected to calculate burning gas temperature and include Determine the ratio to the absorption of described bundle in described first wave length and second wave length.

13. methods according to claim 10, it is characterised in that described combustible substance is steam.

14. methods according to claim 10, it is characterised in that non-conterminous intensity spectral line (106) is described first wave At least two wavelength between length or second wave length and another intensity spectral line.

15. methods according to claim 10, it is characterised in that the laser instrument that described method is used is tunable two poles Pipe laser instrument.