System and method for measuring temperature

Abstract

Systems and methods disclosed herein use a multichromatic pyrometer configured to determine a first temperature in a high temperature range and a monochromatic pyrometer configured to determine a second temperature in a low temperature range. The system uses information obtained from determining the first temperature in the high temperature range to facilitate later determining the second temperature in the low temperature range. The first temperature in the high temperature range and the second temperature in the low temperature range are used to monitor and control different engine operations occurring at different times.

Description

[0001] Statement regarding federally funded research or development

[0002] This invention was completed with the support of the U.S. government. The U.S. government may hold certain rights to this invention. Technical Field

[0003] This disclosure relates to systems and methods for measuring the temperature of components, such as parts or gases of a turbine or engine. Background Technology

[0004] At least some known turbines, such as gas turbine engines, include multiple turbine rotor blades that guide hot fluid through the gas turbine. These turbine rotor blades in the hot gas path may wear over time. For example, these hot gas path components may exhibit stress-related cracking caused by temperatures at or above predetermined parameters. Therefore, many known gas turbine engines include temperature monitoring systems (e.g., using pyrometers or thermocouples) that provide operating temperature data in real time (i.e., at the time of measurement).

[0005] In addition, many known gas turbine engines monitor temperature data as input to their regulatory operations, such as the firing rate (i.e., the rate and / or ratio of fuel and air combustion in the engine). In some cases, temperature data can be used as input to certain protective features of the engine.

[0006] At low engine temperatures, temperature monitoring can determine if the engine is warming up during startup. It is difficult to find a pyrometer that covers both the low temperatures of startup and the high temperatures of operations such as cruising. For low temperatures, thermocouples can be used to measure a lower temperature range. However, thermocouples increase the weight of the system and may require multiple thermocouples.

[0007] Therefore, improved systems and methods for temperature measurement will be welcomed in this field. Attached Figure Description

[0008] The complete and implementable disclosure of this disclosure is set forth in the specification with reference to the accompanying drawings, wherein:

[0009] Figure 1 This is a schematic diagram of a gas turbine engine including a thermal measurement system according to an exemplary aspect of this disclosure.

[0010] Figure 2 Based on exemplary aspects of this disclosure Figure 1 A schematic diagram of the thermal measurement system.

[0011] Figure 3This is a graph showing the relationship between optical power and temperature for different wavelength bands according to an exemplary aspect of this disclosure.

[0012] Figure 4 This is an illustration of a method according to an exemplary aspect of this disclosure. Detailed Implementation

[0013] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0014] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0015] For the purposes described below, the terms “upper,” “lower,” “right,” “left,” “vertical,” “horizontal,” “top,” “bottom,” “lateral,” “longitudinal,” and their derivatives are used in relation to their orientation in the accompanying drawings. However, it should be understood that various alternative variations may be employed in this disclosure, unless expressly stated otherwise. It should also be understood that the specific devices shown in the drawings and described in the following description are merely exemplary embodiments of this disclosure. Therefore, specific dimensions and other physical characteristics associated with the embodiments disclosed herein should not be considered limiting.

[0016] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0017] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and to the normal operating posture of the gas turbine engine or vehicle. For example, for a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0018] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0019] The terms “connection,” “fixation,” “attachment,” etc., refer to direct connection, fixation, or attachment, as well as indirect connection, fixation, or attachment via one or more intermediate components or features, unless otherwise stated herein.

[0020] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0021] The approximate language used throughout the specification and claims is applied to any quantitative expression that may be modified to allow for variation without altering its underlying function. Therefore, values ​​modified by one or more terms such as “about,” “approximate,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 10%, 15%, or 20%. These approximate margins may be applied to a single value, to either or both endpoints of a defined numerical range, and / or to a margin within a range between endpoints.

[0022] Throughout this specification and claims, scope limitations are combined and interchanged, and unless the context or language otherwise indicates otherwise, such scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0023] The term “turbine” or “turbomachinery” refers to a machine that includes one or more compressors, a heating section (e.g., a combustion section), and one or more turbines, which together produce torque output.

[0024] The term "gas turbine engine" refers to an engine that has a turbine as its power source, in whole or in part. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, etc.

[0025] The term "combustion section" refers to any heat addition system used in a turbine. For example, the term "combustion section" can refer to a section that includes one or more of a knock combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assemblies. In some exemplary embodiments, the combustion section may include an annular burner, a cylindrical burner, a tubular burner, a vortex burner (TVC), or other suitable combustion systems, or combinations thereof.

[0026] Unless otherwise stated, the terms “low” and “high,” or their respective degrees of comparison (e.g., lower, higher, where applicable), when used with compressors, turbines, shafts, or spool components, refer to relative speeds within the engine. For example, “low turbine” or “low-speed turbine” defines a component configured to operate at a speed (e.g., maximum permissible speed) lower than that of a “high turbine” or “high-speed turbine” at the engine.

[0027] The system and method disclosed herein use a multicolor pyrometer configured to determine temperatures within a high-temperature range and a monochromatic pyrometer configured to determine temperatures within a low-temperature range. The system uses information obtained from determining temperatures within the high-temperature range to facilitate subsequent determination of temperatures within the low-temperature range.

[0028] Temperatures within both the high-temperature and low-temperature ranges are used to monitor and control different engine operations occurring at different times. For example, temperatures within the high-temperature range can be inputs for regulating operations such as the combustion rate of a gas turbine engine, the rate and / or ratio of fuel and air combustion in the engine, etc. Temperatures within the low-temperature range can be inputs for monitoring start-up combustion or transient behavior.

[0029] A multicolor optical pyrometer configured for the high-temperature range may lack a signal in the low-temperature range. A monochromatic pyrometer is used for the low-temperature range. Although the system does not simultaneously measure temperatures in both the high-temperature and low-temperature ranges, information obtained from determining the temperature in the high-temperature range can be used to later determine the temperature in the low-temperature range. For example, since both the multicolor and monochromatic pyrometers use the same lens to receive light or photons emitted from objects in the engine's hot gas path, fouling (e.g., attenuation) and emissivity information can be determined by determining the temperature in the high-temperature range and used to determine the temperature in the low-temperature range.

[0030] One advantage of this system is that the monochromatic pyrometer can measure temperatures within a cryogenic range used for cryogenic operation. Another advantage is that the monochromatic pyrometer is co-located with the multicolor pyrometer. Compared to completely separate measurement systems (such as thermocouples), this co-location means less added weight to the engine and less space used within the engine.

[0031] like Figure 1 As shown, the turbofan engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 that provides a reference), a radial direction R, and a circumferential direction (i.e., the direction extending about the axial direction A; not described).

[0032] Typically, the turbofan engine 10 includes a fan section 14 and a turbine 16 disposed downstream of the fan section 14. The turbine 16 is sometimes also, or alternatively, referred to as the "core turbine engine".

[0033] The turbine 16 includes a housing 18, which is generally tubular and defines an inlet 20. The housing 18 surrounds, in a series flow relationship: a compressor section including a first boost or low-pressure (LP) compressor 22 and a second high-pressure (HP) compressor 24; a combustion section including a combustor 26; a turbine section including a first high-pressure (HP) turbine 28 and a second low-pressure (LP) turbine 30; and an exhaust nozzle section 32.

[0034] A high-pressure (HP) shaft 34 or spool drives the HP turbine 28 to the HP compressor 24. A low-pressure (LP) shaft 36 or spool drives the LP turbine 30 to the LP compressor 22. The compressor section, combustion section, turbine section, and injection exhaust nozzle section 32 are arranged in a series flow sequence and together define the core airflow path 37 through the turbine 16.

[0035] Fan section 14 includes a variable pitch, single-stage fan 38. Fan 38 includes a plurality of rotatable fan blades 40 spaced apart from disk 42. As shown, the fan blades 40 extend outward from disk 42 generally in the radial direction R.

[0036] The fan blade 40 is operatively coupled to one or more actuating members 44. For example, the actuating member 44 may be configured to change the pitch of the fan blade 40 relative to the pitch axis P. As described in further detail below, the fan blade 40 may have a forward pitch to generate forward thrust, or it may have a reverse pitch to generate reverse thrust.

[0037] The fan drive shaft 45 is operatively connected to and drives the fan 38. The fan blades 40, disk 42, and actuating member 44 can rotate together about the longitudinal centerline axis 12 via the fan drive shaft 45. The fan section 14 is connected to the turbine 16 during forward thrust operation. Specifically, the fan drive shaft 45 is connected to the LP shaft 36.

[0038] The disk 42 is covered by a rotatable forward nacelle 48, which has an aerodynamic profile to facilitate airflow through the multiple fan blades 40. Furthermore, the fan section 14 includes an annular fan housing or outer nacelle 50, which at least partially, and in the illustrated embodiment, circumferentially surrounds at least a portion of the fan 38 and turbine 16.

[0039] Furthermore, in the illustrated embodiment, the nacelle 50 is supported relative to the turbine 16 by a plurality of circumferentially spaced outlet guide vanes 52. A downstream section 54 of the nacelle 50 extends over the exterior of the turbine 16 to define a bypass airflow passage 56 between them.

[0040] During forward thrust operation of the turbofan engine 10, a volume of air 58 enters the turbofan engine 10 through the nacelle 50 and / or the relevant inlet 60 of the fan section 14. As the volume of air 58 passes through the fan blades, a first portion of the air 58, as indicated by arrow 62, is directed or directed into the bypass airflow passage 56, while a second portion of the air 58, as indicated by arrow 64, is directed or directed into the core airflow path 37.

[0041] The pressure of the second-section air 64 increases as it is directed through the LP compressor 22 and the HP compressor 24 and into the combustor 26. More specifically, the compressor section including the LP compressor 22 and the HP compressor 24 defines the total pressure ratio during operation of the turbofan engine 10 at rated speed. The total pressure ratio is the ratio of the outlet pressure of the compressor section (i.e., the pressure of the second-section air 64 at the rear end of the compressor section) to the inlet pressure of the compressor section (i.e., the pressure of the second-section air 64 at the inlet 20 of the compressor section).

[0042] A second portion of compressed air 64 from the compressor section is mixed with fuel and burned in the combustion section to provide combustion gas 66. The combustion gas 66 is directed from the combustor 26 through the HP turbine 28, where a portion of the thermal and / or kinetic energy from the combustion gas 66 is extracted via a successive stage of HP turbine stator blades 68 coupled to the housing 18 and a plurality of HP turbine rotor blades 70 coupled to the HP shaft 34 or spool, thereby causing the HP shaft 34 or spool to rotate, thus supporting the operation of the HP compressor 24.

[0043] The combustion gas 66 is then directed through the LP turbine 30, where a second portion of thermal and kinetic energy is extracted from the combustion gas 66 via a successive stage of LP turbine stator blades 72 connected to the housing 18 and a plurality of LP turbine rotor blades 74 connected to the LP shaft 36 or spool, thereby causing the LP shaft 36 or spool to rotate, thereby supporting the operation of the LP compressor 22 and / or the rotation of the fan 38.

[0044] Combustion gas 66 is then directed through the injection exhaust nozzle section 32 of turbine 16 to provide propulsive thrust. Simultaneously, as the first portion of air 62 is directed through the bypass airflow passage 56 before exiting from the fan nozzle exhaust section 76 of turbofan engine 10, the pressure of the first portion of air 62 increases significantly, also providing propulsive thrust. HP turbine 28, LP turbine 30, and injection exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gas 66 through turbine 16.

[0045] The engine 10 also includes a thermal measurement system 100 and an engine control unit 102. The thermal measurement system 100 is configured to measure the temperature of an object (e.g., turbine rotor blades 74) in the hot gas path 78 and provide that temperature to the engine control unit 102. The engine control unit 102 can monitor the health of the components of the engine 10 and control various aspects of the engine 10 (e.g., geometry, operation, actuators) based on that temperature.

[0046] The engine control unit 102 may be located near or away from the thermal measurement system 100, or the thermal measurement system 100 may include the engine control unit 102. For example, the engine control unit 102 may be a full authority digital engine control (FADEC), an engine control unit (ECU), or the like, for providing fully digital control of the engine 10.

[0047] For further reference Figure 2 A schematic diagram of a thermal measurement system 100 and an engine control unit 102 is provided. The engine control unit 102 includes engine control modules 104 and 106 to monitor and / or control the operation of the engine 10. For illustrative purposes, the engine control modules 104 and 106 may include a set of control loops, control parameters, computer-executable instructions, software modules, etc. In an alternative embodiment, the thermal measurement system 100 may include engine control modules 104 and 106.

[0048] The first engine control module 104 uses a high target temperature T1 as input to monitor or control high-temperature operation of the engine 10 (e.g., those performed during idling, takeoff, cruise, or approach). The second engine control module 106 uses a low target temperature T2 as input to monitor or control low-temperature operation of the engine 10 (e.g., those performed during engine 10 startup). For example, the high target temperature T1 and the low target temperature T2 are exhaust gas temperatures (EGT).

[0049] During takeoff, cruise, approach, engine acceleration, deceleration, etc., the combustion gases 66 and / or objects (e.g., turbine rotor blades 74) in the hot gas path 78 have high temperatures within a high temperature range. For example, the high temperature range may be 1200 to 2600 degrees Fahrenheit or 922 to 1700 Kelvin (K). When the combustion gases 66 and / or objects (e.g., turbine rotor blades 74) in the hot gas path 78 have high temperatures within the high temperature range, the first engine control module 104 uses a high target temperature T1 to monitor or control the engine 10.

[0050] The thermal measurement system 100 determines a high target temperature T1 within a high-temperature range as an input to the first engine control module 104. The first engine control module 104 can monitor the high target temperature T1 to determine the performance status and health condition of the engine 10. The first engine control module 104 can also control the engine 10 based on the high target temperature T1 (e.g., combustion of the engine 10). Because the first engine control module 104 monitors and controls the engine 10 during takeoff, cruise, approach, etc., the thermal measurement system 100 is typically configured to ensure high accuracy of the high target temperature T1.

[0051] During startup, the combustion gases 66 and / or objects (e.g., turbine rotor blades 74) in the hot gas path 78 have low temperatures within a low-temperature range. For example, the low-temperature range may be 500 to 1000 degrees Fahrenheit (F) or Kelvin (K). When the combustion gases 66 and / or objects (e.g., turbine rotor blades 74) in the hot gas path 78 have low temperatures within a low-temperature range, the second engine control module 106 uses a low target temperature T2 during startup, etc.

[0052] The thermal measurement system 100 determines a low target temperature T2 within the low-temperature range as an input to the second engine control module 106. The second engine control module 106 can monitor start-up combustion or transient behavior, for example, by monitoring the increase of the low target temperature T2 after engine 10 starts. As described in further detail below, the direction and relative movement of the low target temperature T2 may be sufficient for monitoring temperatures within the low-temperature range during start-up. Therefore, the accuracy of the low target temperature T2 within the low-temperature range is generally lower than the accuracy of the high target temperature T1 within the high-temperature range.

[0053] Engine control modules 104 and 106 are typically associated with different temperature ranges and the operation of engine 10, which typically does not overlap in time.

[0054] continue Figure 2 , Figure 2 A schematic diagram of a thermal measurement system 100 and an engine control unit 102 is shown, with further detailed description of the thermal measurement system 100. The thermal measurement system 100 is configured to determine a high target temperature T1 within a high-temperature range as an input to a first engine control module 104 during high-temperature operation of the engine 10, and to determine a low target temperature T2 within a low-temperature range as an input to a second engine control module 106 during low-temperature operation of the engine 10. Although in Figure 1 The diagram shows an example location of the thermal measurement system 100, but the thermal measurement system 100 can be located at other locations, such as downstream of the burner 26. The thermal measurement system 100 can be directed at any rotating or static part or object, such as turbine rotor blades 74 or a disc.

[0055] Specifically, the thermal measurement system 100 includes a multicolor pyrometer 110 configured to measure temperatures in a high-temperature range and a monochromatic pyrometer 112 configured to measure temperatures in a low-temperature range. Typically, the multicolor pyrometer 110 uses a lower wavelength to measure higher temperatures, while the monochromatic pyrometer 112 uses a higher wavelength to measure lower temperatures.

[0056] The multicolor pyrometer 110 and the monochromatic pyrometer 112 can be pointed at and optically communicated with an object exposed to the hot gas path 78 of the combustion gas 66. Figure 2In this context, the object is turbine rotor blade 74. In an alternative embodiment, a multicolor pyrometer 110 and a monochromatic pyrometer 112 may be pointed at and optically communicated with other objects in the hot gas path 78.

[0057] The multicolor pyrometer 110 and the monochromatic pyrometer 112 are both located in the sensor housing 114. The sensor housing includes a lens 116 through which light 118 emitted from the turbine rotor blades 74 is received for both the multicolor pyrometer 110 and the monochromatic pyrometer 112.

[0058] The multicolor pyrometer 110 and the monochromatic pyrometer 112 may include detectors that are optically filtered to a predetermined wavelength band defining an optical sensing range. In some embodiments, the detectors are optically filtered using bandpass filters.

[0059] A wavelength or wavelength band can be selected such that data is received from a point on the turbine rotor blade 74 at a single wavelength with little or no interaction with the water content of the combustion gas 66. Since the water content of the combustion gas 66 can absorb and remit the light 118 from the turbine rotor blade 74, selecting a wavelength or wavelength band such that there is little or no interaction with the water content of the combustion gas 66 allows for a more accurate determination of the temperature of the turbine rotor blade 74 or the object.

[0060] The temperature of the turbine rotor blades 74 or other moving parts is sufficient to estimate the temperature of the combustion gas 66. For example, by moving the moving parts through the hot gas path and the temperature distribution in the gas path, the natural average value of the gas temperature is obtained.

[0061] Also refer to Figure 3 , Figure 3 Exemplary optical power at object temperature for different wavelength bands that do not interact with water in combustion gas 66 is shown. The first wavelength band may have a center wavelength between 1.1 micrometers (µm) and 1.4 µm. A particular embodiment may have a center wavelength of 1.24 µm. The second wavelength band may have a center wavelength between 1.5 µm and 1.7 µm. For example, the second wavelength band may have a center wavelength of 1.625 µm. The third wavelength band may have a center wavelength between 3.3 µm and 4.4 µm.

[0062] As an example, for 1.625um and 1.24um, the bandpass filter can have a full width at half maximum (FWHM) of 50nm.

[0063] The detector can be filtered for other wavelength bands (not shown). For example, the detector can be filtered for the 2.1µm to 2.4µm wavelength band.

[0064] Examining the relationship between optical power (e.g., luminous flux) and object temperature, the optical power output of each wavelength band decreases exponentially with decreasing temperature. As the target temperature decreases, the luminous flux in each band decreases. Relatively speaking, at lower target temperatures, higher wavelength bands have more luminous flux, which can result in higher signal strength and lower minimum resolution temperature, provided there is a sufficient signal-to-noise ratio.

[0065] The lower limit of the detector's temperature range can be defined at the temperature at which the detector's output satisfies a threshold amount of optical power output 124. The threshold amount of optical power output 124 can be a condition where the detector output has an acceptable signal-to-noise ratio or otherwise provides a measurement with acceptable accuracy. For example, the threshold amount of optical power output 124 can be 1 nanowatt (nW), such as... Figure 3 As shown.

[0066] The upper limit of the detector's temperature range can be limited to the temperature at which the detector's output saturates (e.g., the maximum power output achievable by the amplifier). For example, the upper limit of the first temperature range for a first wavelength filtered detector could be 2500°F, and the upper limit of the second temperature range for a second wavelength filtered detector could also be 2500°F.

[0067] Different types of detectors may be able to operate in different wavelength bands. For example, InGaAs detectors (both standard and "extended" wavelength detectors) may have limited responsivity at longer wavelengths (e.g., above 2.6 μm). A standard InGaAs detector may have a responsivity cutoff at 1.7 μm, while an extended InGaAs detector may have a responsivity cutoff at 2.6 μm, allowing for optical responses or signals over a wider range. Due to poorer electrical characteristics, extended InGaAs detectors generally perform worse than standard InGaAs detectors (e.g., in terms of accuracy). For example, there may be higher dark current and lower shunt resistance than with standard InGaAs detectors.

[0068] refer to Figure 3 To achieve a lower minimum resolution temperature for the pyrometer, wavelengths above 2.6 μm are required. Within the third permeable wavelength band, from 3.3 to 4.4 μm (e.g., longer wavelengths above 1.7 μm or 2.6 μm), other detectors or materials, such as thermopile or other long-wavelength detectors, can be used to measure luminous flux. Thermopiles can be used at even higher wavelengths (e.g., because they are sensitive to such wavelengths). For example, thermopiles are sensitive to wavelength ranges insensitive to InGaAs. As the temperature decreases, the spectrum emitted by objects (e.g., blackbodies) shifts out of the range of InGaAs detectors, but thermopiles remain sensitive in these regions. Bandpass filters can be used to filter thermopiles at higher wavelengths.

[0069] The multicolor pyrometer 110 includes a plurality of detectors 120, 122. The detectors 120, 122 are optically filtered to a predetermined wavelength band defining an optical sensing range. In some embodiments, these filters are bandpass filters. In some embodiments, the detectors 120, 122 of the multicolor pyrometer 110 are indium gallium arsenide (InGaAs) detectors.

[0070] For example, the first detector 120 is filtered to a first wavelength band whose center wavelength is in the range of 1.1 micrometers (µm) to 1.4 µm (e.g., centered at 1.24 µm). The second detector 122 can be filtered with a center wavelength in the range of 1.5 µm to 1.7 µm (e.g., centered at 1.625 µm). Thus, the multicolor pyrometer 110 is configured to determine a high target temperature T1, for example, in the range of 1000 degrees Fahrenheit (F) to 2500 degrees Fahrenheit (F), as described in further detail below.

[0071] For example, a bandpass filter can have a full width at half maximum (FWHM) of 50 nm.

[0072] To measure a low target temperature T2 during cryogenic operation of engine 10, for example, in the range of 0 to 1000 degrees Fahrenheit, monochromatic pyrometer 112 includes a third detector 152, which is filtered, for example, for a third wavelength band whose center wavelength is in the band of 3.3 μm to 4.4 μm. In some embodiments of monochromatic pyrometer 112, the third detector 152 is a thermopile detector.

[0073] Although the monochromatic pyrometer 112 may have lower accuracy than the multicolor pyrometer 110, for transient temperatures (e.g., the transient response of a gas), the accuracy of the monochromatic pyrometer 112 does not need to be as high as that of the multicolor pyrometer 110. The low target temperature T2 from the monochromatic pyrometer 112 can be used by the second engine control module 106 to determine whether the engine is started or ignited, the rate of temperature change (e.g., increasing at a rapid rate), etc.

[0074] When heated, the turbine rotor blades 74 emit photons or light 118. Each detector 120, 122, 152 receives photons or light 118 having a wavelength within the corresponding optical sensing range and outputs a measurement signal associated with the irradiance of the turbine rotor blades 74.

[0075] Detectors 120, 122, and 132 may have custom bandpass filters 170, 172, and 174 specific to each color detector 120, 122, and 132. Filters 170, 172, and 174 filter the wide-wavelength band radiation signal (e.g., light 118) from turbine rotor blades 74 into a narrow wavelength band corresponding to the wavelength band filtered by detectors 120, 122, and 152.

[0076] Alternatively, filters (e.g., gratings) can be used, and the light entering the grating is spatially dispersed across various detectors (e.g., pixels).

[0077] The measurement signals from detectors 120, 122, and 152 can be represented by the following equation:

[0078] I = F*ε*P(λ,Tb),

[0079] Where I is the measured irradiance, F is the fouling associated with the thermal measurement system 100 (e.g., light attenuation) (e.g., the dirty lens 116 affecting all detectors 120, 122, 152), ε is the emissivity associated with the object (e.g., turbine rotor blade 74), λ is the wavelength, and Tb is the blade temperature. The fouling emissivity (F*ε) can be more generally expressed as a correction factor that takes into account fouling, attenuation, emissivity, and other factors (e.g., chipping due to misalignment).

[0080] According to Planck's law, P is defined as the irradiance of a blackbody, given by the following formula:

[0081] P(λ,Tb)=C1 / (λ^5[exp(C2 / λTb)-1]),

[0082] Where C1 = 1.19 x 10⁴ W um⁴ / cm² Sr, C2 = 1.438 x 10⁴ um*K. In this formula, the wavelength bands of detectors 120 and 122 are chosen such that gas absorption can be assumed to be zero.

[0083] Debris buildup and emissivity are often unknown, and variations in debris buildup can resemble temperature variations in irradiance I measurements. A multicolor pyrometer 110 can be used to calculate the blade temperature Tb (high target temperature T1) within a high-temperature range (e.g., for the first engine control module 104) using the ratio of a first measurement I1 from a first detector 120 to a second measurement I2 from a second detector 122. Using this ratio, debris buildup and emissivity are eliminated, and the blade temperature Tb (e.g., high target temperature T1) can be calculated as follows:

[0084] I1 / I2=P(λ1,Tb) / P(λ2,Tb).

[0085] Substituting the irradiance P from Planck's law into the equation, the ratio becomes:

[0086] I1 / I2=(exp(C2 / (λ2Tb))–1) / (exp(C2 / (λ1Tb))–1).

[0087] With a good approximation, the "-1" can be ignored to obtain:

[0088] Tb=C2(1 / λ2-1 / λ1)ln(I2 / I1).

[0089] exist Figure 2 In this process, the calculation of the blade temperature Tb, which is the high target temperature T1, can occur at the first temperature module 180. For example, the first temperature module 180 can store or access constants (including constants C1, C2 and wavelengths λ1, λ2 associated with detectors 120, 122) used to calculate the blade temperature Tb and receive a first measurement value I1 of irradiance from the first detector 120 and a second measurement value I2 of irradiance from the second detector 122.

[0090] Once the blade temperature Tb (e.g., the high target temperature Tl) is determined by the first temperature module 180, the first temperature module 180 provides the high target temperature Tl to the engine control unit 102 as an input to the first engine control module 104.

[0091] At the correction module 182, a correction factor (e.g., fouling and emissivity (F*ε)) can be determined using the value of the high target temperature T1 and one of the first and second measurements of irradiance, I1 and I2, as follows:

[0092] F*ε=I / (P(λ,Tb)).

[0093] The first temperature module 180 can provide the high target temperature T1 to the correction module 182, and the correction module 182 receives irradiance measurements I1, I2 from one of the detectors 120, 122 (e.g., in...). Figure 2 In this process, a second measurement value I2 of irradiance is received from detector 122. The correction module 182 can store or access constants used to calculate correction factors (e.g., fouling and emissivity). For example, the correction module 182 can store constants C1, C2 and wavelengths λ1, λ2 associated with detectors 120, 122, receiving irradiance measurements I1, I2 from detectors 120, 122.

[0094] Once the correction factors (e.g., fouling and emissivity) are determined by the correction module 182, the values ​​of the correction factors (e.g., fouling and emissivity) can be stored (e.g., stored in memory 184) for later use by the second temperature module 186.

[0095] The values ​​of correction factors (e.g., fouling and emissivity) are used to correct the third measurement I3 of irradiance measured by the third detector 152 of the monochromatic pyrometer 112. Attenuation or fouling of the multicolor pyrometer 110 can occur at different wavelengths, times, operating temperatures, and temperatures, for example, because the multicolor pyrometer 110 and the monochromatic pyrometer 112 are located in the same sensor housing 114 and have the same lens 116. For example, if lens 116 becomes dirty, all detectors 120, 122, and 152 are affected. Emissivity may be wavelength- or temperature-dependent, and in some cases, wavelength or temperature correction may be required.

[0096] The values ​​of fouling and emissivity do not need to be measured in real time to be usable by the monochromatic pyrometer 112. For example, fouling or attenuation typically changes slowly over time relative to the frequency at which these values ​​are determined and used.

[0097] The second temperature module 186 can calculate the blade temperature Tb (e.g., low target temperature T2) within the low-temperature range as input to the second engine control module 106. The second temperature module 186 can access stored values ​​of correction factors (e.g., fouling and emissivity) from the memory 184 and receive a third measurement value I3 of irradiance from the third detector 152.

[0098] Although correction factors (e.g., fouling and emissivity) are calculated for different temperatures and at different times to monitor different operations of engine 10, fouling or degradation may change slowly over time, and emissivity at higher temperatures can be used to approximate emissivity at lower temperatures. The second temperature module 186 can determine the low target temperature T2 based on the following:

[0099] Tb=(λ / C2)*ln(F*ε*[C1 / (λ^5*I)]+1).

[0100] The second temperature module 186 can store or access constants used to calculate the low target temperature T2 (including constants C1, C2, and wavelength λ3 and frequency f3 associated with the third detector 152, which receives a third measurement of irradiance I3 from the detector 152).

[0101] Once the low target temperature T2 is determined by the second temperature module 186, the second temperature module 186 provides the low target temperature T2 to the engine control unit 102 as an input to the second engine control module 106.

[0102] In at least some embodiments, the thermal measurement system 100 and the engine control unit 102 may be or include one or more computing devices. For the purpose of teaching the computing device 190 of the thermal measurement system 100, the computing device 190 will be described in further detail, and the description of the computing device 190 applies to the computing device of the engine control unit 102.

[0103] The computing device 190 may include one or more processors 192 and one or more memory devices 184. The one or more processors 192 may include any suitable processing device, such as a microprocessor, microcontroller, integrated circuit, logic device and / or other suitable processing device.

[0104] One or more memory devices 184 may include one or more computer-readable media, including but not limited to non-transitory computer-readable media, RAM, ROM, hard disk drives, flash drives and / or other memory devices.

[0105] One or more memory devices 184 may store information accessible by one or more processors 192, including computer-readable instructions 194 executable by one or more processors 192 (e.g., modules 180, 182, 186, 104, 106 described above). Instructions 194 may be any set of instructions that causes one or more processors 192 to perform operations when executed by one or more processors 192.

[0106] In some embodiments, instructions 194 may be executed by one or more processors 192 to cause one or more processors 192 to perform operations, such as any operations and functions configured for the thermal measurement system 100 and / or computing device 190, as described herein, receiving measurements from detectors 120, 122, 152, calculating temperatures T1, T2, calculating values ​​of correction factors including fouling and emissivity, low-temperature monitoring and control, high-temperature monitoring and control, and / or any other operation or function of one or more computing devices 190. Instructions may be software written in any suitable programming language or may be implemented in hardware. Additionally, and / or alternatively, instructions may be executed in logical and / or virtual independent threads on the processor.

[0107] The memory device 184 may further store data 196 that can be accessed by one or more processors 192. For example, data 196 may include constants from the equations described above, calculations of fouling and emissivity, calculations of temperature, wavelengths and frequencies associated with detectors 120, 122, 152, and / or calculations of any other data and / or information described herein.

[0108] The computing device 190 may also include a network interface 198 for communicating, for example, with other components. The network interface 198 may include any suitable components for communicating with one or more network interfaces, including, for example, a transmitter, receiver, port, controller, antenna, and / or other suitable components.

[0109] The thermal measurement system 100 (e.g., computing device 190) can perform functions such as Figure 4 The method 200 is shown. According to the first step 210, the thermal measurement system 100 can receive a request for a high target temperature T1 from the engine control unit 102. The engine control unit 102 can request the high target temperature T1 as an input to the first engine control module 104. For example, the first engine control module 104 can use the high target temperature T1 to determine the performance status and health status of the components of the engine 10 during one of the following periods: idling, takeoff, cruise, and approach.

[0110] In the second step 220, the thermal measurement system 100 uses a multicolor pyrometer 110 to determine the high target temperature T1 of the object (e.g., turbine rotor blade 74) within a high temperature range. The high temperature range can be 1200 to 2600 degrees Fahrenheit or 900 to 1700 Kelvin (K).

[0111] The second step 220 includes measuring a first measurement value I1 of irradiance at a first wavelength λ1 using a first detector 120, and measuring a second measurement value I2 of irradiance at a second wavelength λ2 using a second detector 122. The second step 220 also includes determining a high target temperature T1 (e.g., as described above) using the first measurement value I1 of irradiance at the first wavelength λ1 and the second measurement value I2 of irradiance at the second wavelength λ2.

[0112] At the third step 230, the thermal measurement system 100 provides a high target temperature T1 to the engine control unit 102. The engine control unit 102 uses the high target temperature T1 as an input to the first engine control module 104 to monitor and / or control the engine 10.

[0113] At the fourth step 240, the thermal measurement system 100 determines the value of a correction factor (e.g., fouling and emissivity) based on at least one of the high target temperature Tl and a first measurement value I1 of irradiance at a first wavelength λ1 and a second measurement value I2 of irradiance at a second wavelength λ2.

[0114] At step 250, the thermal measurement system 100 stores the values ​​of correction factors (e.g., fouling and emissivity).

[0115] At step 260, the thermal measurement system 100 can receive a request for a low target temperature T2 from the engine control unit 102. The engine control unit 102 can request the low target temperature T2 as an input to the second engine control module 106. For example, the second engine control module 106 can monitor changes in the low target temperature T2 during engine 10 startup to confirm that the temperature is rising after engine 10 startup.

[0116] At step 270, the thermal measurement system 100 uses a monochromatic pyrometer 112 to determine the low target temperature T2 within the low temperature range. The low temperature range can be 500 to 1000 degrees Fahrenheit (F) or 533 to 811 Kelvin (K).

[0117] Step 270 includes measuring a third measurement I3 of irradiance at a third wavelength λ3 using a third detector 152 and obtaining a value for a correction factor (e.g., updated values ​​for fouling and emissivity). Step 270 also includes calculating the low target temperature T2 (e.g., as described above) using the third measurement I3 of irradiance at the third wavelength λ3 and the value of the correction factor (e.g., fouling and emissivity).

[0118] At step 280, the thermal measurement system 100 provides a low target temperature T2 to the engine control unit 102. The engine control unit 102 uses the low target temperature T2 as an input to the second engine control module 106 to monitor and / or control the engine 10.

[0119] This written description uses examples to disclose this disclosure, including best practices, and to enable any person skilled in the art to practice this disclosure, including making and using any device or system and performing any combination of methods. The patent scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0120] In summary, the system and method disclosed herein utilize a multicolor pyrometer configured to determine temperatures within a high-temperature range and a monochromatic pyrometer configured to determine temperatures within a low-temperature range. The system uses information obtained from determining temperatures within the high-temperature range to facilitate the subsequent determination of temperatures within the low-temperature range.

[0121] Temperatures within both the high-temperature and low-temperature ranges are used to monitor and control different engine operations occurring at different times. For example, temperatures within the high-temperature range can be inputs for regulating operations such as the combustion rate of a gas turbine engine, the rate and / or ratio of fuel and air combustion in the engine, etc. Temperatures within the low-temperature range can be inputs for monitoring start-up combustion or transient behavior.

[0122] A multicolor optical pyrometer configured for the high-temperature range may lack a signal in the low-temperature range. A monochromatic pyrometer is used for the low-temperature range. Although the system does not simultaneously measure temperatures in both the high-temperature and low-temperature ranges, information obtained from determining the temperature in the high-temperature range can be used to later determine the temperature in the low-temperature range. For example, since both the multicolor and monochromatic pyrometers use the same lens to receive light or photons emitted from objects in the hot gas path of the engine, fouling (e.g., attenuation) and emissivity information can be determined by determining the temperature in the high-temperature range and used to determine the temperature in the low-temperature range.

[0123] One advantage of this system is that the monochromatic pyrometer can measure temperatures within a cryogenic range used for cryogenic operation. Another advantage is that the monochromatic pyrometer is co-located with the multicolor pyrometer. Compared to completely separate measurement systems (such as thermocouples), this co-location means less added weight to the engine and less space used within the engine.

[0124] Further aspects are provided by the following topics:

[0125] A thermal measurement system includes: a first detector configured to measure a first measurement of irradiance related to a first wavelength; a second detector configured to measure a second measurement of irradiance related to a second wavelength; a third detector configured to measure a third measurement of irradiance related to a third wavelength; and a computing device configured to: determine a high target temperature within a first temperature range based on the ratio of the first measurement of irradiance to the second measurement of irradiance; determine a value of a correction factor based on the high target temperature and one of the first and second measurements of irradiance; and determine a low target temperature within a second temperature range based on the value of the correction factor and the third measurement of irradiance, wherein the second temperature range is lower than the first temperature range.

[0126] The thermal measurement system according to one or more of these clauses, wherein the first temperature range is 1200 to 2600 degrees Fahrenheit, and the second temperature range is 500 to 1000 degrees Fahrenheit.

[0127] A thermal measurement system according to one or more of these clauses, wherein the thermal measurement system is configured to measure the temperature of an object in the hot gas path of an engine.

[0128] A thermal measurement system according to one or more of these clauses, wherein the first wavelength and the second wavelength are shorter than the third wavelength.

[0129] The thermal measurement system according to one or more of these clauses, wherein: the first wavelength is in the range of 1.1 to 1.4 micrometers; the second wavelength is in the range of 1.5 to 1.7 micrometers; and the third wavelength is in the range of 3.3 to 4.2 micrometers.

[0130] The thermal measurement system according to one or more of these clauses, wherein the first detector and the second detector are InGaAs detectors.

[0131] The thermal measurement system according to one or more of these clauses, wherein the third detector is a thermopile detector.

[0132] A thermal measurement system according to one or more of these clauses, wherein the thermal measurement system includes a multicolor pyrometer and a monochromatic pyrometer, wherein the multicolor pyrometer includes a first detector and a second detector, and wherein the monochromatic pyrometer includes the third detector.

[0133] The thermal measurement system according to one or more of these items includes a lens through which light is received for the first detector, the second detector, and the third detector.

[0134] A thermal measurement system according to one or more of these clauses, wherein the computing device is configured to provide the high target temperature and the low target temperature to the engine control unit.

[0135] According to one or more of these clauses, the thermal measurement system wherein the computing device is configured to receive from the engine control device a first request for the high target temperature within the first temperature range.

[0136] According to one or more of these clauses, the thermal measurement system wherein the computing device is configured to measure a first measurement of the irradiance and a second measurement of the irradiance in response to a first request from the engine control device for the high target temperature within the first temperature range.

[0137] According to one or more of these clauses, the thermal measurement system wherein the computing device is configured to receive from the engine control device a second request for the low target temperature within the second temperature range.

[0138] According to one or more of these clauses, the thermal measurement system wherein the computing device is configured to, in response to a second request from the engine control unit for the low target temperature within the second temperature range, measure a third measurement of the irradiance and access the value of the correction factor.

[0139] The thermal measurement system according to one or more of these clauses, wherein the correction factor includes fouling and emissivity.

[0140] A method includes: determining a high target temperature of an object in a hot gas path of an engine using a thermal measurement system, wherein the high target temperature is within a first temperature range, wherein the high target temperature is determined based on: a first measurement of irradiance at a first wavelength using a first detector; and a second measurement of irradiance at a second wavelength using a second detector; determining a value of a correction factor using the thermal measurement system based on the high target temperature and at least one of the first measurement of irradiance at the first wavelength and the second measurement of irradiance at the second wavelength; and determining a low target temperature of the object in the hot gas path of the engine using the thermal measurement system, wherein the low target temperature is within a second temperature range, wherein the low target temperature is determined based on: a third measurement of irradiance at a third wavelength using a third detector; and the value of the correction factor; and wherein the second temperature range is lower than the first temperature range.

[0141] The method according to one or more of these clauses, wherein the correction factor includes fouling and emissivity.

[0142] The method according to one or more of these terms, wherein the first temperature range is 1200 to 2600 degrees Fahrenheit, and the second temperature range is 500 to 1000 degrees Fahrenheit.

[0143] According to one or more of these provisions, the first wavelength and the second wavelength are shorter than the third wavelength.

[0144] The method according to one or more of these clauses includes receiving light from the turbine rotor blades in the hot gas path of the engine via a lens through the thermal measurement system for the first detector, the second detector, and the third detector.

Claims

1. A thermal measurement system, characterized in that, include: A first detector, configured to measure a first measurement of irradiance related to a first wavelength; A second detector, configured to measure a second measurement of irradiance related to a second wavelength; A third detector is configured to measure a third measurement of irradiance related to a third wavelength; as well as Computing device, the computing device being configured to: The high target temperature within the first temperature range is determined based on the ratio of the first measured value of the irradiance to the second measured value of the irradiance. The value of the correction factor is determined based on the high target temperature and one of the first and second measurements of the irradiance. as well as Based on the value of the correction factor and the third measurement of the irradiance, a low target temperature within a second temperature range is determined, wherein the second temperature range is lower than the first temperature range.

2. The thermal measurement system according to claim 1, characterized in that, in, The first temperature range is 1200 to 2600 degrees Fahrenheit, and the second temperature range is 500 to 1000 degrees Fahrenheit.

3. The thermal measurement system according to claim 1, characterized in that, in, The thermal measurement system is configured to measure the temperature of objects in the hot gas path of the engine.

4. The thermal measurement system according to claim 1, characterized in that, in, The first wavelength and the second wavelength are shorter than the third wavelength.

5. The thermal measurement system according to claim 1, characterized in that, in: The first wavelength is in the range of 1.1 to 1.4 micrometers; The second wavelength is in the range of 1.5 to 1.7 micrometers; and The third wavelength is in the range of 3.3 to 4.2 micrometers.

6. The thermal measurement system according to claim 1, characterized in that, in, The first detector and the second detector are InGaAs detectors.

7. The thermal measurement system according to claim 1, characterized in that, in, The third detector is a thermopile detector.

8. The thermal measurement system according to claim 1, characterized in that, in, The thermal measurement system includes a multicolor pyrometer and a monochromatic pyrometer, wherein the multicolor pyrometer includes a first detector and a second detector, and wherein the monochromatic pyrometer includes a third detector.

9. The thermal measurement system according to claim 1, characterized in that, It includes a lens through which light is received for the first detector, the second detector, and the third detector.

10. The thermal measurement system according to claim 1, characterized in that, in, The computing device is configured to provide the high target temperature and the low target temperature to the engine control unit.

11. The thermal measurement system according to claim 10, characterized in that, in, The computing device is configured to receive from the engine control device a first request for the high target temperature within the first temperature range.

12. The thermal measurement system according to claim 11, characterized in that, in, The computing device is configured to, in response to a first request from the engine control unit for the high target temperature within the first temperature range, measure a first measurement of the irradiance and a second measurement of the irradiance.

13. The thermal measurement system according to claim 11, characterized in that, in, The computing device is configured to receive a second request from the engine control device for the low target temperature within the second temperature range.

14. The thermal measurement system according to claim 13, characterized in that, in, The computing device is configured to, in response to a second request from the engine control unit for the low target temperature within the second temperature range, measure a third measurement of the irradiance and access the value of the correction factor.

15. The thermal measurement system according to claim 1, characterized in that, in, The correction factors include fouling and emissivity.

16. A method, characterized in that, include: The high target temperature of an object in the hot gas path of the engine is determined by a thermal measurement system, wherein the high target temperature is within a first temperature range, and wherein the high target temperature is determined based on the following: The first measurement of irradiance at the first wavelength using the first detector; and The second measurement of irradiance at the second wavelength is used with the second detector; The value of the correction factor is determined by the thermal measurement system based on the high target temperature and at least one of a first measurement of the irradiance at the first wavelength and a second measurement of the irradiance at the second wavelength; and The low target temperature of the object in the hot gas path of the engine is determined by the thermal measurement system, wherein the low target temperature is within a second temperature range, and wherein the low target temperature is determined based on the following: The third measurement of irradiance at the third wavelength using the third detector; and The value of the correction factor; and The second temperature range is lower than the first temperature range.

17. The method according to claim 16, characterized in that, in, The correction factors include fouling and emissivity.

18. The method according to claim 16, characterized in that, in, The first temperature range is 1200 to 2600 degrees Fahrenheit, and the second temperature range is 500 to 1000 degrees Fahrenheit.

19. The method according to claim 16, characterized in that, in, The first wavelength and the second wavelength are shorter than the third wavelength.

20. A computer-readable medium, characterized in that, Includes instructions that, when executed by the processor, cause the processor to: Determine the high target temperature of an object in the hot gas path of the engine, wherein the high target temperature is within a first temperature range, and wherein the high target temperature is determined based on the following: The first measurement of irradiance at the first wavelength using the first detector; and The second measurement of irradiance at the second wavelength is used with the second detector; The value of the correction factor is determined based on the high target temperature and at least one of a first measurement of the irradiance at the first wavelength and a second measurement of the irradiance at the second wavelength; and Determine the low target temperature of the object in the hot gas path of the engine, wherein the low target temperature is within a second temperature range, and wherein the low target temperature is determined based on the following: The third measurement of irradiance at the third wavelength using the third detector; and The value of the correction factor; and The second temperature range is lower than the first temperature range.

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