• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a combustion gas measuring device arranged in a gas turbine, the measuring device comprising: a tunable laser (22) which generates a beam (34) passing through a combustion gas path in the gas turbine; a tunable laser controller (20), the laser (22) being tuned to emit radiation having at least one selected first wavelength and a selected second wavelength, each corresponding to respective temperature dependent transitions of a combustion species of the gas, wherein the first selected wavelength and the second selected wavelength do not have adjacent distinct absorption lines; a detector that detects the beam passing through the combustion gas and generates an absorption signal indicative of the absorption of the beam by the combustion gas at each of the first wavelength and the second length, and the controller (20) stores a program stored on a non-volatile storage medium to determine a combustion gas temperature based on a ratio of the absorption signals for the first wavelength and the second wavelength.
    公开号:CH703759B1
    申请号:CH01482/11
    申请日:2011-09-08
    公开日:2016-08-31
    发明作者:Venugopal Badami Vivek；Mordin Hoyte Scott；Mitra Chayan；Banerjee Ayan
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background of the invention
    The invention relates to the determination of hot gas temperatures using a tunable laser and, in particular, to the determination of high pressure combustion gas temperatures in a gas turbine.
    It is difficult to accurately determine the combustion gas temperature in a turbine. The combustion gas is extremely hot, corrosive, turbulent and is under high pressure. The combustion gas temperature, e.g. the turbine combustion temperature (TBrenn) is usually estimated using factors such as exhaust gas, temperature and pressure of the gas emitted by the compressor. This estimate of the combustion gas temperature contains a certain amount of uncertainty. In order to take this uncertainty into account, the combustion gas temperature is set to a temperature which is lower than it would be required if the combustion gas temperature were known with greater certainty.
    The combustion gas temperature affects the power output of a gas turbine. The output increases with increasing combustion gas temperature. For example, increasing the combustion gas (Tburn) temperature by 10 ° F (5.5556 ° C) can increase the output power by one megawatt (1 MW) for a two hundred megawatt (200 MW) gas turbine. Reducing the level of uncertainty would allow the combustion gas temperature to be increased and would result in a corresponding increase in the output of a gas turbine.
    Spectroscopic measurements, e.g. Laser measurements have been proposed to accurately determine gas temperatures in a gas turbine. The international patent application WO 2007/014 960 describes a temperature measuring device which measures the absorption of laser light at wavelengths which correspond to oxygen in a flow of combustion gas from a gas turbine. US patent application 2008/0 289 342 describes the determination of combustion temperatures by measuring the absorption of laser light wavelengths which correspond to oxygen in the gas flow of a gas turbine.
    The laser wavelengths at which the absorption originating from the combustion gas is measured must be chosen so that the accuracy of the calculation of the gas temperature is optimized. The wavelengths at which the absorption is measured are usually selected to correspond to temperature-dependent transitions of a species in the gas. There are several available wavelengths at which absorption occurs that result from temperature-dependent transitions of a combustion gas species. What is needed is a method of selecting a pair of wavelengths at which to measure laser absorption in order to obtain absorption line strength data for accurately calculating combustion gas temperature in a gas turbine.
    Brief description of the invention
    [0006] A system and method for accurately measuring the combustion temperature or other hot gas temperatures in a gas turbine have been developed. A tunable diode laser directs a laser beam through the combustion gases flowing through a gas turbine. Radiometers measure the radiation absorption that occurs at wavelengths corresponding to a pair of water vapor harmonic transitions in the near-infrared wavelength band. The temperature of the combustion gas is calculated based on a ratio of the absorptions measured at these two wavelengths. The pair of wavelengths is relatively isolated and has no neighboring strong absorption lines of nearby wavelengths. This isolation and the absence of adjacent absorption strength lines prevents the merging of adjacent distinct absorption strength lines which occurs at high pressures in a gas turbine.
    According to the invention, a combustion gas measuring device is arranged in a gas turbine, the measuring device comprising: a tunable laser which generates a beam of radiation that passes through a combustion gas path in the gas turbine; a control device for the tunable laser, wherein the laser is tuned to emit radiation having a first selected wavelength and a second selected wavelength, both of which correspond to temperature-dependent transitions of a combustion species of the gas, the first selected wavelength and the second selected wavelength have no adjacent pronounced absorption lines; a detector that detects the beam of rays passing through the combustion gas and generates an absorption signal that indicates the absorption of the beam by the combustion gas at both the first wavelength and the second length, and a processor that executes a program stored on a non-volatile storage medium which , based on a ratio of the absorption signals for the first wavelength and for the second wavelength, calculates the combustion gas temperature.
    According to an advantageous embodiment of the invention, a combustion gas measuring device is arranged in a gas turbine, the measuring device having: a tunable diode laser which emits a laser beam that passes through a combustion gas path in the gas turbine; a tunable diode laser controller that is tuned to emit a first laser beam having a wavelength of 1334 nanometers (nm) and a second laser beam having a wavelength of 1380 nm or 1391 nm; a laser sensor that detects each of the radiation beams passing through the combustion gas and generates an absorption signal indicating the absorption of the radiation beam by the combustion gas at each of the wavelengths; and a processor that executes a program stored on a non-volatile storage medium to determine the combustion gas temperature based on a ratio of the absorption signals in the first laser beam and the second laser beam.
    The invention also relates to a method which is used to calculate the combustion gas temperature in a high pressure environment with the aid of a combustion gas measuring device according to the invention, the method comprising: identifying pronounced absorptions which are associated with temperature-dependent transitions of gas species in the combustion gas; Identifying the pronounced absorptions associated with a temperature-dependent transition of combustion gas species of the combustion gas; Selecting first and second lines of the distinct absorption lines identified as being associated with the combustion gas types, the two selected distinct absorption lines having no adjacent absorption lines; Identifying a first wavelength and a second wavelength associated with the first and second salient lines, respectively; Projecting a laser beam through a combustion gas path at each of the identified first and second wavelengths and collecting data relating to the absorption of the beam by the combustion gas at each of the identified first and second wavelengths and calculating a combustion gas temperature using the collected data.
    Brief description of the drawing
    [0010] FIG. 1 is a schematic illustration of the principle of a gas turbine; FIG. 2 is a cross-sectional view of the connection between the combustor and turbine of the gas turbine shown in FIG. 1; Figures 3 and 4 are graphs illustrating laser beam absorption by combustion gas over a radiation frequency range of 7200 / cm to 7207 / cm; FIGS. 5 and 6 are exemplary diagrams for illustrating the line thickness in the case of laser absorption by combustion gases at different wavelengths; FIGS. 7 and 8 are exemplary diagrams for illustrating the line thickness in the case of laser absorption by combustion gases at different wavelengths. 9, 10 are flow charts illustrating an exemplary method for determining the combustion temperature using a tunable diode laser.
    Detailed description of the invention
    1 is a schematic representation of an industrial gas turbine engine 10 with a compressor 12, a combustion chamber 14 with combustion tubes 16 and a turbine 18. Air enters the axial compressor, which compresses the air and releases it into an annular arrangement of combustion tubes 16 that form the combustion chamber. The air / fuel mixture is ignited in the combustion tubes. Hot gases resulting from the combustion flow into the turbine 18. The hot combustion gases 15 enter the turbine 18 and flow over an annular array of first stage guide vanes and an annular array of first stage turbine blades. The stream of hot combustion gases, which flows over the rows of annular arrangement of turbine rotor blades, sets the turbine rotor blades and the shaft associated with them in rotation, which shaft is also connected to the compressor. The drive of the compressor by the turbine causes the compressor to compress the air for the combustion chamber.
    [0012] The temperature of the hot combustion gases entering the turbine is usually referred to as the combustion temperature (TBrenn). The combustion temperature can be defined as the gas temperature at which turbine work begins, in the combustion gas flow path at about the trailing edge of the first guide vanes and the leading edge of the first turbine blades.
    A control device 20, e.g. a computer having a non-volatile storage medium and a processor, receives wavelength absorption data from a laser and sensor assembly 22 which is used to calculate a combustion gas temperature. The control device uses the calculated combustion gas temperature to control the gas turbine, for example by adapting the fuel control 23 and the inlet guide vanes in the compressor 12. The control device also outputs data relating to the operating behavior of the gas turbine using the calculated combustion gas temperature.
    Figure 2 is a schematic cross-sectional view of an enlarged portion of the gas turbine 10 corresponding to the inlet to the turbine 16 which is proximate the trailing edge of the first row of vanes and the leading edge of the first row of turbine blades. The housing 24 of the gas turbine 10 has accesses 26 which are usually used for inserting endoscopes in order to inspect internal components, for example rotor blades and guide vanes, of the gas turbine.
    The entrances 26 give the laser and laser sensor assembly 22 access, which monitors the combustion gases flowing from the combustion chamber to and through the turbine. The laser and sensor arrangement 22 is mounted on or in the housing 24 of the gas turbine and extends through a bore-shaped access 26. A shaft 28 of the laser and sensor arrangement 22 extends through one of the accesses 26 on the housing and up to the outer circumference of the Gas flow path 30.
    In the shaft 28 light paths, for example fiber optics or electrical wires, are arranged to transmit laser light or electrical signals between the inner tip 32 of the shaft and electronic control and detection circuits associated with the laser and sensor assembly 22. Tip 32 may contain a laser diode and a diode sensor, each of which is connected to electrical leads. The laser diode projects a radiation beam 34 that passes through the combustion gas flow path 30. The diode sensor receives the beam 34 after passage through the gas flow path and generates a signal indicative of the strength, i. Indicating the intensity of the beam.
    The tip 32 can be aligned with a narrow gap between the first guide vane 38 and the first turbine rotor blade 40 and lie on the outer circumference of the flow path 30 through this gap. Laser light 34 is projected radially inward through the flow path and reflected on a radially inward surface adjacent the flow path to a radiation detector, e.g. an optical sensor or a fiber optic at the tip 32. The laser light 34 can also be reflected from the shaft of the turbine.
    Instead of reflecting the laser light, two shafts 28 can be introduced at different endoscope accesses 26, which are axially aligned on the housing 24 of the gas turbine and positioned so that the tip 32 of each shaft lies on an alignment line that extends through the Gas path extends. Laser light 34 is projected from a first tip while a light detector or light intercepting device, e.g. a fiber optic, in the other tip is provided. In addition, several shafts (or shaft pairs) can also extend through different endoscope access points or other openings in the housing of the gas turbine in order to monitor the gas temperature at different locations in the gas flow path.
    A tunable diode laser and sensor assembly 22 can be a common system that includes a laser light source with a tunable diode, optics for transmission, such as beam shaping, laser beam receiving optics and one or more detectors, such as a photodiode. The laser diode is tuned by electronic circuits and a computer control unit assigned to the arrangement 22 in such a way that the radiation emission wavelength of the laser is varied over wavelengths which are characteristic of the absorption wavelengths of certain combustion gas components (species) of the combustion gas, such as water vapor.
    The absorption of the radiation emission from the laser reduces the intensity of the laser beam and this reduction in intensity is measured by the detector. The detector generates a line width signal that indicates the amount of absorption of the radiation at the wavelength emitted by the laser. The line width signal is provided to a computer 20 or other processing unit which uses the signal to determine the combustion gas temperature. The computer 20 can be separate from or combined with the computer tuning the laser in the laser assembly 22.
    A tunable diode laser is a laser in which the frequency of the emitted radiation can be tuned over part or all of the ultraviolet, the visible and the infrared region of the spectrum. The tunable diode laser can be selected depending on the wavelength of the region over which the tuning is to take place. Typical examples of diode lasers are InGaAsP / InP (tunable from 900 nm to 1.6 µm) and InGaAsP / InAsP (tunable from 1.6 µm to 2.2 µm). Diode lasers can be tuned by tuning their temperature or the injection current density that is injected into the gain medium of the laser.
    The light sensor or light sensors of the laser and sensor arrangement 22 measures the radiation absorption at the various wavelengths that are emitted depending on the tuning of the laser, using conventional absorption spectroscopic techniques. When the laser radiation passes through, e.g. of light, through the combustion gas, the combustion species in the gas absorb certain wavelengths of radiation. In addition, the temperature of the gas influences the amount of absorption that occurs.
    Measuring the laser beam absorption at selected wavelengths provides data useful in calculating the temperature of the combustion gas. In particular, the temperature of a gas can be derived from the ratio of the laser beam absorption, which is measured at two wavelengths, each of which corresponds to a temperature-dependent transition of a component (species) of the gas.
    The selected wavelengths of the laser radiation correspond to wavelengths of water vapor transitions that occur in the combustion gas. The line widths are measured at these two selected wavelengths on the basis of the laser radiation passing through the compressed combustion gas flowing through the gas turbine. The absorption line strengths are measured essentially simultaneously at the two selected wavelengths, because the laser diode is tuned in such a way that it emits alternately at each of the selected wavelengths.
    The ratio of the two absorption line strengths is commonly used to calculate the temperature of the combustion gas. Tunable diode laser absorption spectroscopy (TDLAS) techniques can be used to measure absorption line strengths and calculate combustion gas temperature. The wavelengths are specifically chosen to correspond to two water vapor harmonic transitions in the near infrared band. The temperature of the combustion gas can be calculated based on a ratio of the measured absorption of the wavelengths corresponding to the two water vapor harmonic transitions.
    The wavelengths at which the absorption is measured to determine the combustion gas temperature are selected so that they correspond to the absorption by water vapor and have no nearby wavelengths at which absorption peaks occur. The choice of wavelengths which are removed from other wavelengths with an absorption peak ensures that the selected wavelength does not unite with an adjacent absorption peak as the gas pressure increases.
    When used in internal combustion engines, such as gas turbines, a variable pressure broadening (collision broadening) complicates the absorption measurement and introduces a varying degree of overlap of absorption transitions with adjacent transitions. The collision broadening of a typical water vapor, γair, is about 0.05 cm-1; Atmosphere at 300 ° K. If the laser wavelength under consideration has an adjacent transition within 2.5 cm-1, there is a considerable overlap at the high combustion pressures in an internal combustion engine. The amount of overlap (interference) depends on the line thicknesses during the machine's performance / time cycles. The simplest line selection process would only keep lines that have no nearest neighbors within 2.5 cm-1.
    Figures 3, 4 are diagrams illustrating laser radiation absorption by a combustion gas over a range of wavelengths with radiation frequencies of 7200 / cm to 7207 / cm. As shown in Fig. 3, a strong absorption line (peak) occurs at 2704 / cm (corresponding to a wavelength of 1388 nanometers (nm)), with a weaker line at 7205 / cm when the gas pressure is 10 atmospheres (ATM) (10.1325 bar). 4 shows that when the gas pressure rises to 30 ATM, the two absorption lines broaden and merge into one another. The merging of absorption lines with increasing gas pressure impairs the measurement accuracy of the absorption associated with one of the absorption lines.
    In a typical Tburn measurement in a gas turbine, the combustion pressure is about 15 atmospheres (15 ATM). The collision broadening of a typical water vapor transfer is γ air with approximately 0.05 cm – 1 / atm at 300 K. At 15 atm the full-width (half maximum FWHM) for a water vapor transfer changes by 0.75 cm – 1. This will not cause lines to collapse at high pressure.
    Figures 5, 6 are exemplary diagrams illustrating the line thickness in laser absorption by combustion gases at different wavelengths. In the examples given in FIGS. 5 and 6, the gas pressure is one atmosphere (ATM). Figure 5 shows a strong absorption line at a wavelength of 7495 / cm (1334 nm) and a temperature of 2000 Kelvin (K) (1727 ° C and 3140.6 ° F). There are no adjacent wavelengths that have an absorption line in the range of 7490 / cm to 7515 / cm. Fig. 6 shows a strong absorption line at a wavelength of 7243 / cm (1380 nm).
    The wavelength pairs (i) 7495 / cm (1334 nm) and 7243 / cm (1380 nm) and (ii) 7495 / cm and 7185 / cm (1391 nm) correspond to water vapor harmonic transitions in the near-infrared and have no adjacent absorption lines that represent a Would generate interference.
    Fig. 5 shows a negligible line width at ambient temperature (296 K), which indicates that ambient temperatures do not generate interference or noise that affects the temperature calculation of the combustion gases. As shown in Fig. 7, the line width of the absorption at the 1334 nm wavelength increases with temperature.
    6 shows a strong absorption line strength at a wavelength of 7243 / cm at ambient temperature (296 K) and a nominal line strength at a temperature of 2000 K. The absorption at the 7243 / cm (1380 nm) wavelength changes inversely with temperature.
    The temperature-dependent line thickness [cm-2atm-1] can be specified in relation to the known line thickness at a reference temperature T0:
    where Q (T) is the molecular partition function, h [Jsec] is Planck's constant; c [cm / s] is the speed of light, k [J / K] is Boltzmann's constant and E ́ ́ [cm – 1] the lower energy state.
    The temperature can be derived from the measured ratio of the integrated absorptivity at two different temperature-dependent transitions.
    where Pabs [atm] is the partial pressure of the absorbing species, Φνγ [cm] is the line shape function of a particulate transition; S (T0, vi) is the line width of the transition centered at vi [cm – 1] at the reference temperature T0, E ́ ́ the lower energy state [cm – 1] and T is the gas temperature [K].
    The relative temperature sensitivity of the above ratio is obtained by:
    It can be seen from the above equation that a line pair with a large difference between the lower states is sought in order to achieve a high temperature sensitivity.
    In the example shown in FIGS. 5, 6, the sensitivity (σ) is 5.71 at a temperature range of 1500 K to 2000 K (2240 ° F to 3140 ° F)
    A high level of sensitivity indicates that the accuracy of temperature measurements using the wavelength pair of 1334 nm and 1380 nm should be about 0.35%, which is an error of only 9 ° F at 2500 ° F (5 ° C at 1371.1 ° C).
    FIGS. 7 (which is identical to FIG. 5) and 8 are exemplary diagrams showing the line widths for laser absorption by combustion gases at different wavelengths. Figure 7 shows a strong absorption line at a wavelength of 7495 / cm (1334 nm) and a temperature of 2000 K (1727 ° C and 3140.6 ° F). There are no adjacent wavelengths that have an absorption line in the range of 7490 / cm to 7515 / cm. Fig. 8 shows a strong absorption line at a wavelength of 7185 / cm (1391 nm).
    Although there is a further absorption line near 7185 / cm-1 in FIG. 8, the line width of this further line is small. One criterion for ensuring the temperature measurement is that the two transitions have a similar signal-to-noise ratio (SNR). Assuming a minimum detectable absorbance of 2E-4 and an SNR of 10, the peak absorbance must be greater than 2E-3. Assuming a pressure of 15 ATM and a path length of 1 cm, the line at 7185 cm-1 (with pressure broadening) in FIG. 8 should not significantly affect the accuracy of the temperature measurement.
    8 shows a large absorption line strength at a wavelength of 7185 / cm (1391 nm) at ambient temperature (296K) and a nominal line strength at a temperature of 2000 K. The absorption at the 7185 / cm (1391 nm) wavelength changes inversely with temperature.
    In the embodiment illustrated in Figures 7, 8, the sensitivity (σ) is 3.91 in a temperature range of 1500 K to 2000 K (2240 ° F to 3140 ° F). This high level of sensitivity indicates that the accuracy of temperature measurements made using the 1334 nm and 1391 nm wavelength pair should be within 15 ° F at 2500 ° F (8.3 ° C at 1371.1 ° C).
    The diode laser in laser and sensor assembly 22 can be tuned to a third wavelength, e.g. of 635 nm which does not correspond to a wavelength that is absorbed by the combustion gas. The line width signal detected at the third wavelength can be used as a reference value indicating the transparency of the optics in the laser and sensor assembly 22 and the reflectivity of the turbine shaft or other surface used to deliver the laser beam to the detector in the tip 32 of the arrangement 22 to reflect.
    Figures 9 and 10 are flow charts of an exemplary method of establishing a tunable laser system for measuring combustion temperature and combustion gas temperature. The part of the method for measuring the combustion temperature can be embodied in the form of commands in a computer program which is stored on a non-volatile storage medium which can be accessed by the processor or the computer 27 shown in FIG.
    In a step 100, combustion gases that are the same or substantially similar are tested to determine radiation wavelengths emitted by the combustion gas, e.g. to identify species of combustion being absorbed. The combustion gases can be at a low pressure e.g. an atmosphere (ATM) or at a pressure corresponding to the compressor outlet pressure, e.g. 20 ATM to 30 ATM (20.265 bar to 30.398 bar), which is similar, can be tested. Testing at low pressure avoids the merging of lines of absorbent strength which, at high pressure, tends to occur. The absorption lines can be identified in a laboratory combustion chamber. A tunable diode laser can be used to scan an appropriate range of wavelengths to obtain the data regarding the wavelengths at which absorption by species in the combustion gases occurs.
    In a step 102, the absorption line strengths obtained in step 101 are evaluated in order to identify strength lines which correspond to species in the combustion gas which have temperature-dependent transitions. For example, water vapor and oxygen are species of combustion gas that experience temperature-dependent transitions. A person skilled in the art of combustion, particularly that of combustion gases in a gas turbine, has sufficient knowledge and experience to determine which absorption line strengths correspond to the data of temperature-dependent transitions of species of the combustion gas.
    Of the strength lines identified in step 102, groups, e.g. Find pairs of strength lines associated with the same combustion gas species in step 104. The strength lines in a group are evaluated in a step 106 to identify a pair of lines, each line having no adjacent strength lines. For example, a pair of wavelengths of 1334 nm and 1380 nm as well as 1334 nm and 1391 nm has each assigned strong absorption lines because of a temperature-dependent transition of water vapor and the lack of adjacent strong absorption lines.
    In a step 104 it is determined which of the strength lines identified in the step 102 are removed from adjacent strength lines. The wavelength pairs which correspond to the strength lines identified in step 104 with no adjacent strength lines are selected as the wavelength pair at which the absorption is measured in order to calculate the temperature of the combustion gas. In a step 108, a wavelength is identified that is not assigned to any strength line, in particular a temperature-dependent strength line.
    In a step 110, the laser and sensor arrangement is installed in a gas turbine in such a way that the tunable laser diode allows a beam to pass through the gas path in the turbine. The laser beam can pass through a gap between the first vane and the first blade to acquire absorption data directly from the location of the Tburn temperature.
    In a step 112 and during the operation of the gas turbine, the laser and sensor arrangement acquires absorption data by projecting a laser beam through the gas turbine, the laser being tuned to the wavelengths selected in step 106. The tuning of the laser can be cyclical, such that the wavelengths are changed periodically and rapidly to the wavelengths selected in steps 106, 108. The absorption data are collected and stored on a storage medium assigned to the control device in the laser and detector arrangement. In a step 114, the absorption data are processed in the laser and detector arrangement or in the control device for the gas turbine in order to calculate a combustion gas temperature based on the ratio of the line widths (absorption data) obtained at the two wavelengths identified in step 106 had been. In addition, the laser and detector arrangement uses the absorption data acquired at the wavelength identified in step 118 as a reference value which indicates a line strength signal which has no absorption by species of the combustion gas. The gas turbine controller uses the calculated combustion gas temperature to control the gas turbine and to generate reports on the performance of the gas turbine.
    Although the invention has been described in connection with what is currently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the embodiment illustrated, but on the contrary, numerous modifications and equivalent arrangements which are within the scope of the appended claims.
    A combustion gas measuring device arranged in a gas turbine 10, the measuring device comprising: a tunable laser 22 that generates a beam 34 passing through a combustion gas path in the gas turbine 110; a control device 20 for the tunable laser, wherein the laser 22 is tuned such that it emits radiation having at least a selected first wavelength and a selected second wavelength, both of which correspond to temperature-dependent transitions 102 of a combustion species of the gas, the first the selected wavelength and the second selected wavelength do not have adjacent distinct absorption lines 104; a detector which detects the beam passing through the combustion gas (100, 112) and generates an absorption signal indicative of the absorption of the beam by the combustion gas at each of the first wavelength and the second wavelength, and the control device 20 on a non-volatile Executes a program stored in the storage medium to determine a combustion gas temperature based on a ratio of the absorption signals for the first wavelength and the second wavelength.
    List of reference symbols
    10 gas turbine 12 compressor 14 combustion chamber 16 combustion tubes 18 turbine 20 control device 22 laser and laser sensor arrangement 23 fuel control device 24 housing of the gas turbine 26 accesses to the housing 28 shaft of the assembly 30 gas flow path 32 tip of the shaft 34 laser light 38 first guide vane 40 first turbine blade 100 combustion gases testing 102 identifying strong lines associated with temperature-dependent transitions of species of the combustion gas 104 finding groups of strong lines associated with the same species 106 identifying a group of strong lines that have no adjacent strong line 108 identifying a wavelength that is not a strong line Line includes 110 positioning the laser and sensor assembly in the gas turbine 112 collecting data from the operation of the gas turbine 114 calculating gas temperature
    权利要求:
    Claims (15)
    [1]
    A combustion gas meter disposed in a gas turbine (10), the meter comprising:a tunable laser (22) that generates a radiation beam (34) that passes through a combustion gas path in the gas turbine (10);a tunable laser controller (20), wherein the laser (22) is tuned to emit radiation having at least a first selected wavelength and a second selected wavelength, which two temperature dependent transitions (102) of a combustion species of the gas wherein the first selected wavelength and the second selected wavelength do not have adjacent distinct absorption lines (104);a detector detecting the beam passing through the combustion gas and generating an absorption signal indicative of absorption of the bundle by the combustion gas at each of the first wavelength and the second wavelength, andwherein the controller (20) is configured to execute a program (114) of a combustion gas temperature stored on a non-volatile storage medium based on a ratio of the absorption signals for the first wavelength and for the second wavelength.
    [2]
    2. The combustion gas meter of claim 1, wherein the first selected wavelength is 1334 nm and the second selected wavelength is 1380 nm or 1391 nm.
    [3]
    3. A combustion gas meter according to claim 1, wherein the combustion species is water vapor.
    [4]
    The combustion gas meter of claim 1, wherein the tunable laser (22) is disposed in the gas turbine (10) such that the beam passes through the gas path (30) between a first turbine vane (38) and a first turbine vane (40) of the gas turbine passes.
    [5]
    The combustion gas meter of claim 1, wherein the tunable laser (22) is a tunable diode laser.
    [6]
    6. A combustion gas meter according to claim 1, wherein the tunable laser (22) in the gas turbine (10) is arranged such that the beam is reflected by a surface of a turbine of the gas turbine.
    [7]
    The combustion gas meter of claim 2, wherein the tunable laser (22) is a tunable diode laser (22).
    [8]
    The combustion gas meter of claim 7, wherein the tunable laser (22) is disposed in a gas turbine such that the laser beams pass through the gas path (30) between a first turbine vane (38) and a first turbine vane (40) of the gas turbine.
    [9]
    9. A combustion gas meter according to claim 7, wherein the tunable laser (22) in the gas turbine (10) is arranged such that the beam is reflected from a surface of a turbine of the gas turbine.
    [10]
    10. A method for calculating a combustion gas temperature in a high pressure environment using a combustion gas meter according to claim 1, the method including:Identifying (102) distinct absorption lines associated with temperature dependent transitions of species in the combustion gas (30);Identifying (104) the distinct absorption lines associated with a temperature-dependent transition of a combustion species of the combustion gas;Selecting (106) first and second distinct absorption lines identified as being associated with the combustion species, the selected two distinct absorption lines having no adjacent distinct absorption lines;Identifying (108) a first wavelength and a second wavelength respectively associated with the first and second distinct absorption lines;Projecting (110) a laser beam through a combustion gas path (30) at each of the first and second identified wavelengths and collecting data (112) related to the absorption of the beam by the combustion gas at each of the identified first and second wavelengths, respectively, andCalculating (114) a combustion gas temperature using the collected data.
    [11]
    The method of claim 10, wherein the first wavelength is 1334 nanometers (nm) and the second selected wavelength is 1380 nm or 1391 nm.
    [12]
    12. The method of claim 10, wherein calculating the combustion gas temperature using the collected data includes determining a ratio of the respective absorption of the radiation beam at the first and second wavelengths.
    [13]
    13. The method of claim 10, wherein the combustion species is water vapor.
    [14]
    The method of claim 10, wherein no adjacent distinct absorption lines (106) means at least two wavelengths between the first and second selected wavelengths and another distinct absorption line.
    [15]
    15. The method of claim 10, wherein the laser is a tunable diode laser.
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    JP2012057623A|2012-03-22|
    US8702302B2|2014-04-22|
    CN102445283A|2012-05-09|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-04-30| PL| Patent ceased|
    优先权:
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    US12/880,681|US8702302B2|2010-09-13|2010-09-13|Hot gas temperature measurement in gas turbine using tunable diode laser|
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