Abstract:
A system includes an optical sensor that optically measures and spatially resolves in three dimensions at least one chemical species within a flame produced by a device and a component that correlates the three dimensionally measured at least one chemical species to at least one parameter of the device.

Description:
BACKGROUND OF THE INVENTION 
     The subject matter disclosed herein relates to the optical measurement of light and, more particularly, to an optical sensor that performs three-dimensional, spatially-resolved optical measurements of the flame of a combustor of a gas turbine engine and to a system that utilizes the optical measurements to better control the combustion process. 
     Optical measurements of flame chemiluminescent light emission are routinely used in premixed gas combustors in gas turbine engines to determine various parameters such as energy or heat release rates and fuel-to-air ratios in such combustors. Placing wavelength filters in front of optical detectors is typically used to identify the partial contribution of the total light emission from each of specific excited-state species, such as OH*, CH*, C2* and CO2*. Ratios of the signals of one or more of these species can then be correlated in a known manner to various combustor parameters such as the fuel-to-air ratio, heat release rate and gas temperature. Previous applications of this measurement technique have used simple optical sensor arrangements and camera systems. A problem with these techniques and systems is their inherent limited spatial resolution. In complex combustion flows, the ability to make spatially resolved measurements in three dimensions is critical to optimizing system performance through improved control of the combustion process. 
     The use of exhaust temperature spread as a surrogate for combustor chamber-to-chamber variation in fuel-to-air ratio, heat release rate and gas temperature is adequate. However, results can be improved by using optical techniques to observe the flame in each combustor can. A primary issue with using optical methods in these situations has been that they typically provide limited line-of-sight information when what is preferably needed is three-dimensional, spatially-resolved information about the entire flame in each combustor can. 
     BRIEF DESCRIPTION OF THE INVENTION 
     According to one aspect of the invention, a system includes an optical sensor that optically measures and spatially resolves in three dimensions at least one chemical species within a flame produced by a device and a component that correlates the three dimensionally measured at least one chemical species to at least one parameter of the device. 
     According to another aspect of the invention, a method includes optically measuring and spatially resolving in three dimensions at least one chemical species within a flame produced by a device, and correlating the three dimensionally measured at least one chemical species to at least one parameter of the device. 
     According to yet another aspect of the invention, a system includes an optical sensor that optically measures and spatially resolves in three dimensions at least one chemical species within a flame produced by a combustor, and a device that correlates the three dimensionally measured at least one chemical species to at least one parameter of the combustor. 
     These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWING 
       The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which: 
         FIG. 1  illustrates an optical sensor and accompanying optics according to an embodiment of the present invention for measuring the combustion flame in three dimensions in a combustor portion of a gas turbine engine; 
         FIG. 2 , including  FIGS. 2A and 2B , are side and top views, respectively, of another embodiment of the present invention for measuring the combustion flame in three dimensions in a combustor portion of a gas turbine engine; 
         FIG. 3  is a side view, partially cutaway, of the sensors of  FIGS. 1  or  2  located in the combustor of a gas turbine engine; and 
         FIG. 4  is side view, partially cutaway, of the sensors of  FIGS. 1  or  2  located in the combustor of a gas turbine engine, together with an associated controller and fuel control valves. 
     
    
    
     The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings. 
     DETAILED DESCRIPTION OF THE INVENTION 
     Referring to  FIG. 1 , an image sensor  100  according to an embodiment of the invention includes a single sensor array  102  having a plurality of apertures  104  for sensing emitted light at a particular wavelength. The image sensor  100  may be a single wavelength color sensor that provides a three-dimensional mapping of the flame chemiluninescence intensity emitted by a single chemical species from among a number of different such species (e.g., OH*, CH*, C2*, CO2*, wherein the asterisk “*” following the molecule name denotes the molecule in an excited state) of the flame within the combustion zone  106  of a combustor ( FIGS. 3-4 ) of a gas turbine engine. The optical image of the flame within the combustion zone  106  is focused not directly onto the apertures  104  in the sensor array  102 , but instead is focused by an imaging lens  108  to a focal plane  110  located above the apertures  104 . The image is then re-imaged by an optical filter  112  having a single wavelength onto the apertures  104  to form partially overlapping images or fields of view of the combustion zone  106  between the apertures  104 . The optical filter  112  (i.e., local optics) may be implemented in a dielectric stack of an integrated circuit using refractive microlenses or diffractive gratings patterned in metal layers. The sensed images of the chemical species may then be combined to form a three-dimensional, spatially-resolved representation of the flame within the combustion zone  106 . The multiple perspective views of the image of the flame in the combustion zone  106  allow for the synthesis of a three-dimensional image at a greater spatial resolution that the number of apertures  104  themselves. 
     In an alternative embodiment of the invention, more than one sensor array  102  may be utilized, with different wavelength filtering capability provided on each array  102 . This allows for simultaneous measurement of several different chemical species (e.g., OH*, CH*, C2*, CO2*) of the flame within the combustion zone  106 , wherein these different chemical species are at different wavelengths. This allows for performing ratiometric measurements between the multiple species. The ratios of at least two different ones of these species can then be correlated in a known manner to arrive at or to derive various combustor parameters such as the fuel-to-air ratio, heat release rate, and gas temperature. In contrast, if a single sensor array  102  is provided with a single wavelength filtering capability, then typically the heat release rate and gas temperature can be correlated or derived from the measured single chemical species. 
     Referring to  FIGS. 2A and 2B , in another embodiment of the image sensor  200  according to the present invention, a two-dimensional array  202  of apertures  204  may be provided. In this embodiment, multiple different filter elements  206  may be deposited directly onto the apertures  204  of the imaging array  202  to allow for multiple different color measurements to be carried out. The array  200  is best seen in the top view (i.e., facing the array) of  FIG. 2B . Thin film deposition of, e.g., silicon or silicon carbide, may be used to create a color filter array on a surface  208  of the image sensor  200 . Other materials that may be deposited include magnesium fluoride, calcium fluoride and various metal oxides. In the example shown in  FIG. 2 , there are four different color filters  206  arranged in a square (2×2), and this square pattern is repeated over the entire top surface  208  of the sensor  200 . The four different color filters  206  represent the predominant color for each of the chemical species (e.g., OH*, CH*, C2*, CO2*) desired to be measured. Each filter element  206  may have a microlens located above the element, and each group of four color filter elements provides for a multiple wavelength intensity map of the flame over the combustion region  106  ( FIG. 1 ). 
       FIG. 3  illustrates the three-dimensional combustion image sensor  100 ,  200  of  FIGS. 1  or  2  deployed in a typical combustor  300  that is part of a gas turbine engine  302 . In this example, the image sensor  100 ,  200  may be located in the transition duct downstream from the main combustion region. Each can in a typical combustor  300  of the gas turbine engine  302  may have an image sensor  100 ,  200  located therein to measure the characteristics of the flame in each can. The image sensor  100 ,  200  may be integrated with an air- or liquid-cooled mounting bracket, so as to be able to withstand the normally harsh thermal environment. As mentioned, the image sensor  100 ,  200  provides a three-dimensional, spatially-resolved map of the measured chemical species (e.g., OH*, CH*, C2*, CO2*), and from the measured chemical species various specific combustion parameters, such as fuel-to-air ratio, heat release rate, or gas temperature, may be correlated or derived in a known manner. The output of the image sensor may be provided to a controller  400  ( FIG. 4 ) that correlates the measure chemical species to the specific combustion parameters. In response to the correlated or derived combustion parameters, the controller can vary the flow parameters to the fuel nozzles  402  ( FIG. 4 ) in the combustor  300  to directly affect and balance or improve the combustion process within the gas turbine engine  302 . 
       FIG. 4  illustrates the three-dimensional image sensor  100 ,  200  of  FIGS. 1  or  2  integrated with the gas turbine controller  400 . The output signal from the sensor  100 ,  200  on a line  404  is fed to the controller  400  through an electrical cable or suitable fiber optic connection. The controller  400  processes the image information from the sensor  100 ,  200  and takes a control action when non-optimal operation of the combustor  300  is detected. In this example, the control action may comprise an adjustment of the individual fuel supply valves  406  that feed the fuel injection nozzles  402  within the fuel injection system of the engine  302 . In this way, the combustion process can be improved using the output of the image sensor  100 ,  200  in a feedback control system. Similarly, to achieve optimum operation, the controller  400  may vary other parameters automatically. These parameters may include, e.g., airflow distribution, diluent injection and fuel nozzle geometry. 
     Embodiments of the image sensor  100 ,  200  of the present invention in general provide a three-dimensional, spatially-resolved map of the combustion parameters in a reacting flow. The image sensor  100 ,  200  allows for the indirect three-dimensional measurement or correlation of various combustion parameters such as heat release rate, fuel-to-air ratio and gas temperature from the directly measured concentrations of various specific chemical species in the flame of the combustor  300 . The sensor  100 ,  200  includes a multi-aperture imaging device coupled to optical filters to collect light from the flame chemiluminescent emission. The light emission from excited state species such as OH*, CH*, C2* and CO2* is collected on a single, or a multiple multi-aperture array such that three-dimensional, spatially-resolved maps of these concentrations of these species are obtained. The measured three-dimensional, spatially-resolved maps can be correlated with parameters associated with the combustor  300  such as heat release rate, fuel-to-air ratio, and gas temperature in each combustor can. This can be used for combustor health monitoring as well as engineering assessment of the performance of a given combustor design. 
     A method for monitoring these various combustion parameters (fuel-to-air ratio, heat release rate, temperature, etc.) is part of a combustion monitoring package necessary for closed loop or model based control of a gas turbine combustor  300 . Such a package includes a monitor of combustion dynamics, emissions, and fuel-to-air ratio, heat release rate and gas temperature for each combustion chamber or can in a gas turbine engine  302 . In the alternative, embodiments of the invention are applicable to annular (i.e., non-can) combustors or afterburners, to measure the characteristics of the flame in these devices. Combustion monitoring is an integral part of advanced controls packages for high performance gas turbine combustors. Elements being monitored include combustion dynamic pressure oscillations, emissions, fuel-to-air ratio, heat release and gas temperature. Embodiments of the present invention provide for relatively greater fidelity in monitoring real time variations in the fuel-to-air ratio, heat release rate and gas temperature between combustion chambers so that fuel and air flow adjustments to each combustor can be made to reduce these variations. This results in relatively lower emissions and greater durability and operability over a wider range of gas turbine operation. 
     While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.