WO2007087081A2 - Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine - Google Patents
Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine Download PDFInfo
- Publication number
- WO2007087081A2 WO2007087081A2 PCT/US2006/060572 US2006060572W WO2007087081A2 WO 2007087081 A2 WO2007087081 A2 WO 2007087081A2 US 2006060572 W US2006060572 W US 2006060572W WO 2007087081 A2 WO2007087081 A2 WO 2007087081A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- optic
- transmitting
- combustion
- optically coupled
- receiving
- Prior art date
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/80—Diagnostics
Definitions
- the present invention is directed toward a method and apparatus for monitoring and control of a combustion process, and more particularly toward a method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine.
- TDLAS Tunable Diode Laser Absorption Spectroscopy
- TDLAS wavelength modulation spectroscopy and direct absorption spectroscopy. Each of these techniques is based upon a predetermined relationship between the quantity and nature of laser light received by a detector after the light has been transmitted through a combustion zone (or combustion chamber) and absorbed in specific spectral bands which are characteristic of the combustion species present in the combustion zone. The absorption spectrum received by the detector is used to determine the combustion properties, including the quantity of the combustion species under analysis and associated combustion parameters such as temperature. [0003]
- One particularly useful implementation of TDLAS utilizes wavelength- multiplexed diode laser measurements in order to monitor multiple combustion species and combustion parameters.
- PCT/US2004/010048 International Publication No.
- WO 2004/090496 entitled “Method and Apparatus for the Monitoring and Control of Combustion” (“WO '496”), the content of which is incorporated in its entirely herein.
- Determining combustion properties can be used to improve combustion efficiency in, for example, gas turbine engines, while simultaneously reducing the harmful emissions such as nitrogen oxides.
- Monitoring combustion properties within gas turbine engines also has the potential to improve turbine blade lifetime and all other engine components aft of the combustion zone as well as providing a useful diagnostic to identify malfunctioning engines.
- FIG. 1 is a schematic view of a gas turbine engine 10 including a combustion zone 12.
- the combustion zone 12 is defined between a cylindrical outer casing 14 and a cylindrical inner casing 16.
- a turbine shaft 18 resides within the inner casing 16. The confined area in the vicinity of the combustion zone complicates effective access.
- FIG. 2 is a schematic cross-section of the combustion zone 12 taken along lines
- FIG. 2 shows the cylindrical outer casing 14, the cylindrical inner casing 16, the turbine shaft 18 and a number of combustor fuel cups 20 between the inner and outer casings.
- One possibility for providing line of sight access to the combustion zone is to provide a transmitting optic 22 associated with the borescope port 24 on the outer casing and a receiving optic 26 associated with a port in the inner casing.
- the turbine shaft that is housed in the inner casing prevents any optics from being placed inside the inner casing.
- FIG. 3 A second possibility is illustrated in Fig. 3, with like reference numbers associated with like elements.
- a line of sight is provided by passing the laser from one borescope inspection port 24 A to a second borescope inspection port 24B.
- the line of sight skirts the central inner casing essentially forming a cord 28 through the annular combustion space. While potentially feasible, such a design is problematic because of the high-pressure, high-temperature environment and the difficulty of steering the beam at the severe angle required by the engine geometry.
- the present invention is directed toward overcoming one or more of the problems discussed above.
- FIG. 1 is a partial sectional view taken along a lengthwise axis of a schematic representation of a gas turbine engine
- FIG. 2 is a schematic cross-sectional view of the combustion zone of the gas turbine engine of Fig. 1 taken along lines A-A of Fig. 1 illustrating one potential optical coupling of a transmitting/receiving optic pair;
- Fig. 3 is similar to Fig. 2 only illustrating a second potential coupling of a transmitting/receiving optic pair
- Fig. 4 is similar to Fig. 2 only illustrating coupling of a transmitting/receiving optic pair configured in accordance with the present invention
- FIG. 5 is a schematic representation of an embodiment of an apparatus for measuring combustion parameters within a combustion zone of a gas turbine engine in accordance with the present invention using a single wavelength beam input;
- FIG. 6 is a schematic representation of an embodiment of an apparatus for measuring combustion parameters within a combustion zone of a gas turbine engine in accordance with the present invention using a multiplexed beam input;
- Fig. 7 is a graph of reflected signal versus time at four different wavelengths between 1348-1559 nm measured in one example in accordance with the present invention.
- a first aspect of the invention is a method for measuring combustion properties within a combustion zone of a gas turbine engine, the combustion zone being defined between an inner and outer casing.
- the method comprises transmitting a beam from a transmit optic optically coupled to a port in the outer casing off a portion of the inner casing and receiving a portion of the beam reflected off the inner casing with a receiving optic optically coupled to a port in the outer casing.
- the transmit optic and the receiving optic may be optically coupled to the same port and the port may be a preexisting borescope port provided in the outer casing by the engine manufacturer to observe a turbine blade during servicing.
- the transmitting step may include transmitting a beam comprising a plurality of discrete multiplexed wavelengths.
- the method may further include demultiplexing the portion of the beam received by the receiving optic into discrete wavelengths and detecting at least one discrete wavelength of the demultiplexed beam.
- the method may further include determining the concentration of at least one combustion species based upon the intensity of the at least one detected wavelength.
- the method may also include determining the concentration of a plurality of combustion species based upon the intensity of a plurality of detected discrete wavelengths of a multiplexed beam.
- Engine input parameters may be varied in response to select concentrations of the combustion species to affect engine performance.
- the concentration of at least one combustion property, such as a combustion species may be monitored to determine an engine malfunction.
- the method may further include treating a portion of the inner casing to improve its reflectivity.
- a second aspect of the present invention is a gas turbine engine comprising a combustion zone between an inner and an outer casing.
- a port in the outer casing is operatively associated with the combustion zone substantially opposite a portion of the inner casing.
- a transmitting and receiving pair of optics are optically coupled with the port, with the transmitting and receiving pair of optics being configured so that the transmitting optic transmits a beam off the portion of the inner casing and the receiving optic receives at least a portion of the beam reflected off the portion of the inner casing.
- the gas turbine engine may further include first and second ports in the outer casing operatively associated with the combustion chamber, the transmitting optic being optically coupled with the first port and the receiving optic being optically coupled with the second port.
- the portion of the inner casing may be treated to improve its reflectivity.
- Yet another aspect of the present invention is an apparatus for measuring combustion parameters of a gas turbine engine, the gas turbine engine having a combustion zone defined between an inner and an outer casing and a port in the outer casing in communication with the inner casing.
- the apparatus includes a laser generating a beam of a discrete wavelength and a transmitting optic optically coupled to the laser for transmitting the beam.
- a receiving optic is further provided and the receiving optic and the transmitting optic are configured for operative association with the port in the outer casing of the gas turbine engine, whereby the transmitting optic and the receiving optic are optically coupled by reflecting the beam off the portion of the inner casing.
- the system further comprises a plurality of lasers each generating a beam of a discrete wavelength and a multiplexer optically coupled to the plurality of lasers for multiplexing the discrete wavelength beams to a multiplexed beam.
- the multiplexer is optically coupled to the transmitting optic to convey the multiplexed beam thereto.
- Such an embodiment may further include a demultiplexer optically coupled to the receiving optic and a detector optically coupled to the demultiplexer for detecting each discrete wavelength beam received by the receiving optic.
- a computer may be coupled to each detector with the computer being programmed to determine a concentration of at least one combustion species based upon an output of the detectors.
- the computer may be further programmed to control engine input parameters as a function of the concentration of the at least one combustion species.
- the computer may be programmed to determine an engine malfunction based upon the concentration of at least one combustion species.
- Fig. 1 which is described briefly above depicts in schematic form a partial sectional view taken along an axis of a gas turbine engine 10 illustrating the combustion chamber 12.
- Fig. 4 is a cross-section view taken along lines A-A of Fig. 1 illustrating in schematic form the operative association of a transmitting optic 22 and a receiving optic 26 pair in accordance with the present invention.
- the transmitting/receiving optics pair 22, 26 are optically coupled to a port 24 in an outer casing 14 and physically secured to the outer casing.
- the port 24 may be a borescope port which is a penetration in the outer casing available near the combustion zone on many modern gas turbine engines.
- the borescope ports are intended to allow observations of the turbine blade during servicing, but are further intended to be accessible only when the engine is not running. Thus, these ports typically are plugged during engine operation.
- the transmitting/receiving optics pair 22, 26 are secured to the port 24 and the outer casing in a manner enabling them to function as the plug they replace.
- the transmitting/receiving optics pair 22, 26 are configured for operative association with the port 24 in the outer casing of the gas turbine so that the transmitting optic and the receiving optic are optically coupled by reflecting the beam 30 off a portion 32 of the inner casing 16 substantially opposite the port 24.
- substantially opposite means positioned so that light reflects off the portion 32 of the inner casing in a near-specular manner between the transmitting/receiving optics pair. In this manner, a line of sight between the transmitting optic 22 and the receiving optic 26 can be achieved in the combustion zone of the gas turbine engine with minimal intrusion.
- the transmitting optic 22 may direct the beam 34 illustrated in phantom lines off the inner casing to a receiving optic 26 associated with a distinct port. In such an embodiment the portion 36 of the inner casing upon which the beam is reflected would be between the transmitting/receiving optics 22, 26.
- the beam 30 is reflected off the portion 32 of the inner casing 16 in a near-specular manner so that it nearly retraces its path to the receiving optic 26 located in close proximity to the transmitting optic.
- the portion 32 of the inner casing may be polished or coated in some manner to increase the reflectivity of the portion 32 of the inner casing.
- the size of the portion may vary in accordance with tolerances, but a section as small as 5 mm in diameter may be sufficient to significantly improve the optical transmission.
- a coating of a highly reflective material may be applied to the portion 32 of the inner casing.
- the portion 32 of the inner casing may be treated to resist collection of soot deposits. All manner of treating the portion 32 of the inner casing to improve reflectivity and minimize soot deposition are with the scope of the invention.
- Fig. 5 illustrates schematically one embodiment of the present invention in the form of a system or sensing apparatus 50 for sensing, monitoring and control of a combustion process.
- the apparatus 50 comprises a tunable diode laser 52 that is optically coupled to an individual optical fiber 54 which may be a single mode optical fiber.
- the optical fiber 54 is further optically coupled to a transmitting optic 22 which may include a collimating lens or other optics suitable for producing a collimated transmitted beam 30.
- “coupled” or “optically coupled” or “in optical communication with” is defined as a functional relationship between counterparts where light can pass from a first component to a second component either through or not through intermediate components or free space.
- the transmitting optic 22 and the receiving optic 26 are optically coupled to a port 24 in the cylindrical outer casing 14, whereby the beam 30 is transmitted off a portion 32 of the inner casing 16 to be received by the receiving optic 26.
- the portion 32 of the inner casing may be substantially opposite the port 24.
- the portion 32 may be treated to improve reflectivity or minimize soot collection as discussed above with respect to Fig. 4.
- the receiving optic 26 is optically coupled to a optical fiber 56, which may be a multi-mode optical fiber.
- Optical fiber 56 is optically coupled to a detector 58, which typically is a photodetector sensitive to the frequency of laser light generated by laser 52.
- the detector 58 generates an electrical signal based upon the nature and quantity of light transmitted to the detector 58.
- the electrical signal from the detector 58 is digitized and analyzed in a computer or data processing system 60.
- the computer 60 is programmed to determine a combustion property, such as a concentration of at least one combustion species, based upon the output of the detector.
- the computer may further be programmed to control engine input parameters such as air and fuel provided to the combustion zone as a function of the concentration of the combustion species, as illustrated by the arrow 62.
- the computer 60 may be programmed to determine an engine malfunction based upon the concentration of a combustion species and produce a warning signal.
- the invention contemplates the use of fiber optic coupling to the electronic and optical components on both the transmitting and receiving sides of the sensing apparatus 50 to allow delicate temperature sensitive apparatus such as the tunable diode laser 52, the detector 58 and the data processing system or computer 60 to be located in a suitable operating environment away from the gas turbine engine.
- delicate temperature sensitive apparatus such as the tunable diode laser 52, the detector 58 and the data processing system or computer 60 to be located in a suitable operating environment away from the gas turbine engine.
- the relatively robust transmitting and receiving optics 22, 26 need to be situated near the hostile environment of the combustion chamber 12.
- Fig. 6 schematically illustrates a multiplexed sensing apparatus 70 in accordance with the present invention.
- a plurality of tunable diode lasers 52A-52D are optically coupled to an optical fiber 72 (which may be a single mode optical fiber) and routed to a multiplexer 74.
- laser light from some or all of the diode lasers 12A-12D is multiplexed to form a multiplexed beam having multiple select frequencies.
- the multiplexed beam is optically coupled to an optical fiber 75 and transmitted to the transmitting optic 22.
- a receiving optic 26 forms a transmitting/receiving optics pair with the transmitting optic 22.
- the transmitting/receiving optics pair 22, 26 are optically coupled to a port 24 in an outer cylindrical casing 14 of a gas turbine engine, as described with respect to Fig. 5.
- the beam 82 which in this case is a multiplexed beam, is reflected off a portion 32 of the inner casing 16 for receipt by the receiving optic 26.
- the receiving optic 26 optically communicates with a demultiplexer 86 by means of optical fiber 88.
- the demultiplexer 86 demultiplexes multiplexed beams to discrete wavelengths and each wavelength is optically communicated to a corresponding detector 58A-58D, which in turn is coupled to the data processor or computer 90, which may be programmed as discussed above with respect to the computer 60 of Fig. 6.
- the embodiment illustrated in Fig. 6 may include any number of tunable diode lasers 52A-52D generating a variety of wavelengths, though only four are illustrated for the sake of simplicity. A like number of photodiode detectors 58 are provided.
- the multiplexer 74 and demultiplexer 86 may be components designed for use it the telecommunications industry. Suitable multiplexers/demultiplexers are described in greater detail in WO '496, referenced above. Other aspects of the method and apparatus for the monitoring and control of combustion described in WO '496 may be included with the apparatus described in Figs. 5 and 6 as necessary or desired.
- using multiple sets of transmitting/receiving optics pairs and optical switches and/or routers to provide a beam of multiplexed light to each pair and for providing the beam to the detectors may be useful, particularly for a tomographic representation of combustion properties wherein the combustion zone.
- the surface of the inner casing may degrade over time due to deposition of carbonations material (essentially soot). It is anticipated that even with a fouled inner casing in which the reflectivity of the surface will degrade and become more highly scattered, approximately one part per million of the light will remain detectable. In this event, the measurement becomes more like a LIDAR (Laser Radar) in which back scattered laser light is observed from the inner casing surface instead of specular reflection.
- LIDAR Laser Radar
- Data was collected from a transmitting/receiving pair of optics associated with a portion of an inner casing.
- the portion of the inner casing which the beam was directed to had been bead-blasted, which produces a higher degree of scattering than a typical inner casting of an engine would provide.
- Four wavelengths were multiplexed onto a single mode fiber, collimated and then directed by a transmit optic onto the bead blasted portion of the inner casing.
- the receiving optic was positioned to catch the specular reflection from the portion of the inner casing.
- Fig. 7 is a table setting forth the reflecting data collected.
Abstract
A method for measuring combustion parameters within a combustion zone of a gas turbine engine, the combustion zone being defined between an inner and outer casing. The method comprises transmitting a beam from a transmit optic optically coupled to a bore in the outer casing off a portion of the inner casing and receiving a portion of the beam reflected off the inner casing with a receiving optic optically coupled to a bore in the outer casing. An apparatus for practicing the method comprises a laser generating a beam and a transmitting/receiving optics pair, the transmitting/receiving optics pair being configured for operative association with a port in an outer casing of a gas turbine engine, whereby the transmitting/receiving optics are in optical communication by reflecting the beam off a portion of an inner casing.
Description
METHOD AND APPARATUS FOR SPECTROSCOPIC
MEASUREMENTS IN THE COMBUSTION
ZONE OF A GAS TURBINE ENGINE
TECHNICAL FIELD
[0001] The present invention is directed toward a method and apparatus for monitoring and control of a combustion process, and more particularly toward a method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine.
BACKGROUND OF THE INVENTION
[0002] Laser-based spectroscopic instruments have been implemented in a variety of environments to extract measurement data. Laser-based measurement apparatus can be implemented in situ and offer the further advantage of high speed feedback suitable for dynamic process control. One technique for measuring combustion species such as gas composition, temperature and other combustion parameters (collectively, "combustion properties") utilizes Tunable Diode Laser Absorption Spectroscopy (TDLAS). TDLAS is typically implemented with diode lasers operating in the near-infrared and mid-infrared spectral regions. Suitable lasers have been extensively developed for use in the telecommunications industry and are, therefore, readily available for TDLAS. Various techniques for TDLAS which are more or less suitable for sensing control of combustion processes have been developed. Commonly known techniques are wavelength modulation spectroscopy and direct absorption spectroscopy. Each of these techniques is based upon a predetermined relationship between the quantity and nature of laser light received by a detector after the light has been transmitted through a combustion zone (or combustion chamber) and absorbed in specific spectral bands which are characteristic of the combustion species present in the combustion zone. The absorption spectrum received by the detector is used to determine the combustion properties, including the quantity of the combustion species under analysis and associated combustion parameters such as temperature. [0003] One particularly useful implementation of TDLAS utilizes wavelength- multiplexed diode laser measurements in order to monitor multiple combustion species and combustion parameters. One such system is described in PCT/US2004/010048 (International Publication No. WO 2004/090496) entitled "Method and Apparatus for the Monitoring and Control of Combustion" ("WO '496"), the content of which is incorporated in its entirely herein.
[0004] Determining combustion properties can be used to improve combustion efficiency in, for example, gas turbine engines, while simultaneously reducing the harmful emissions such as nitrogen oxides. Monitoring combustion properties within gas turbine engines also has the potential to improve turbine blade lifetime and all other engine components aft of the combustion zone as well as providing a useful diagnostic to identify malfunctioning engines.
[0005] While monitoring combustion properties in gas turbine engines would appear to have many potential benefits, making the measurements has proven extremely difficult. The difficulty stems from two major sources. First, the high-pressure and temperature of the combustion zone (30-40 bar, 2200 K) creates an environment in which normal spectral features are highly distorted, leading to difficulty in interpreting data even if it can be obtained. Second, making such measurements in an operating engine requires optical access; that is, a penetration or penetrations in the engine casing through which one can direct a laser beam over a line of sight. This is very difficult to arrange in an operating gas turbine engines due to the harsh nature of the engine environment, the limited space available for monitoring components and the need to minimize impact on critical components. [0006] To illustrate the difficulty of providing line of sight optical access to the combustion zone of a gas turbine engine, Fig. 1 is a schematic view of a gas turbine engine 10 including a combustion zone 12. The combustion zone 12 is defined between a cylindrical outer casing 14 and a cylindrical inner casing 16. A turbine shaft 18 resides within the inner casing 16. The confined area in the vicinity of the combustion zone complicates effective access.
[0007] Fig. 2 is a schematic cross-section of the combustion zone 12 taken along lines
A-A of Fig. 1. Fig. 2 shows the cylindrical outer casing 14, the cylindrical inner casing 16, the turbine shaft 18 and a number of combustor fuel cups 20 between the inner and outer casings. One possibility for providing line of sight access to the combustion zone is to provide a transmitting optic 22 associated with the borescope port 24 on the outer casing and a receiving optic 26 associated with a port in the inner casing. However, the turbine shaft that is housed in the inner casing prevents any optics from being placed inside the inner casing.
[0008] A second possibility is illustrated in Fig. 3, with like reference numbers associated with like elements. Here a line of sight is provided by passing the laser from one borescope inspection port 24 A to a second borescope inspection port 24B. In such an embodiment, the line of sight skirts the central inner casing essentially forming a cord 28
through the annular combustion space. While potentially feasible, such a design is problematic because of the high-pressure, high-temperature environment and the difficulty of steering the beam at the severe angle required by the engine geometry. [0009] The present invention is directed toward overcoming one or more of the problems discussed above.
BRIEF DESCRIPTION OF THE DRAWINGS
[0010] Fig. 1 is a partial sectional view taken along a lengthwise axis of a schematic representation of a gas turbine engine;
[0011] Fig. 2 is a schematic cross-sectional view of the combustion zone of the gas turbine engine of Fig. 1 taken along lines A-A of Fig. 1 illustrating one potential optical coupling of a transmitting/receiving optic pair;
[0012] Fig. 3 is similar to Fig. 2 only illustrating a second potential coupling of a transmitting/receiving optic pair;
[0013] Fig. 4 is similar to Fig. 2 only illustrating coupling of a transmitting/receiving optic pair configured in accordance with the present invention;
[0014] Fig. 5 is a schematic representation of an embodiment of an apparatus for measuring combustion parameters within a combustion zone of a gas turbine engine in accordance with the present invention using a single wavelength beam input;
[0015] Fig. 6 is a schematic representation of an embodiment of an apparatus for measuring combustion parameters within a combustion zone of a gas turbine engine in accordance with the present invention using a multiplexed beam input; and
[0016] Fig. 7 is a graph of reflected signal versus time at four different wavelengths between 1348-1559 nm measured in one example in accordance with the present invention.
SUMMARY OF THE INVENTION
[0017] A first aspect of the invention is a method for measuring combustion properties within a combustion zone of a gas turbine engine, the combustion zone being defined between an inner and outer casing. The method comprises transmitting a beam from a transmit optic optically coupled to a port in the outer casing off a portion of the inner casing and receiving a portion of the beam reflected off the inner casing with a receiving optic optically coupled to a port in the outer casing. The transmit optic and the receiving optic may be optically coupled to the same port and the port may be a preexisting borescope port provided in the outer casing by the engine manufacturer to observe a turbine blade during
servicing. The transmitting step may include transmitting a beam comprising a plurality of discrete multiplexed wavelengths. In such an embodiment, the method may further include demultiplexing the portion of the beam received by the receiving optic into discrete wavelengths and detecting at least one discrete wavelength of the demultiplexed beam. The method may further include determining the concentration of at least one combustion species based upon the intensity of the at least one detected wavelength. The method may also include determining the concentration of a plurality of combustion species based upon the intensity of a plurality of detected discrete wavelengths of a multiplexed beam. Engine input parameters may be varied in response to select concentrations of the combustion species to affect engine performance. In addition, or alternatively, the concentration of at least one combustion property, such as a combustion species may be monitored to determine an engine malfunction. The method may further include treating a portion of the inner casing to improve its reflectivity.
[0018] A second aspect of the present invention is a gas turbine engine comprising a combustion zone between an inner and an outer casing. A port in the outer casing is operatively associated with the combustion zone substantially opposite a portion of the inner casing. A transmitting and receiving pair of optics are optically coupled with the port, with the transmitting and receiving pair of optics being configured so that the transmitting optic transmits a beam off the portion of the inner casing and the receiving optic receives at least a portion of the beam reflected off the portion of the inner casing. The gas turbine engine may further include first and second ports in the outer casing operatively associated with the combustion chamber, the transmitting optic being optically coupled with the first port and the receiving optic being optically coupled with the second port. The portion of the inner casing may be treated to improve its reflectivity.
[0019] Yet another aspect of the present invention is an apparatus for measuring combustion parameters of a gas turbine engine, the gas turbine engine having a combustion zone defined between an inner and an outer casing and a port in the outer casing in communication with the inner casing. The apparatus includes a laser generating a beam of a discrete wavelength and a transmitting optic optically coupled to the laser for transmitting the beam. A receiving optic is further provided and the receiving optic and the transmitting optic are configured for operative association with the port in the outer casing of the gas turbine engine, whereby the transmitting optic and the receiving optic are optically coupled by reflecting the beam off the portion of the inner casing. In one embodiment, the system further comprises a plurality of lasers each generating a beam of a discrete wavelength and a
multiplexer optically coupled to the plurality of lasers for multiplexing the discrete wavelength beams to a multiplexed beam. The multiplexer is optically coupled to the transmitting optic to convey the multiplexed beam thereto. Such an embodiment may further include a demultiplexer optically coupled to the receiving optic and a detector optically coupled to the demultiplexer for detecting each discrete wavelength beam received by the receiving optic. A computer may be coupled to each detector with the computer being programmed to determine a concentration of at least one combustion species based upon an output of the detectors. The computer may be further programmed to control engine input parameters as a function of the concentration of the at least one combustion species. The computer may be programmed to determine an engine malfunction based upon the concentration of at least one combustion species.
DETAILED DESCRIPTION OF THE INVENTION
[0020] Fig. 1, which is described briefly above depicts in schematic form a partial sectional view taken along an axis of a gas turbine engine 10 illustrating the combustion chamber 12. Fig. 4 is a cross-section view taken along lines A-A of Fig. 1 illustrating in schematic form the operative association of a transmitting optic 22 and a receiving optic 26 pair in accordance with the present invention. In the embodiment illustrated in Fig. 4, the transmitting/receiving optics pair 22, 26 are optically coupled to a port 24 in an outer casing 14 and physically secured to the outer casing. The port 24 may be a borescope port which is a penetration in the outer casing available near the combustion zone on many modern gas turbine engines. The borescope ports are intended to allow observations of the turbine blade during servicing, but are further intended to be accessible only when the engine is not running. Thus, these ports typically are plugged during engine operation. The transmitting/receiving optics pair 22, 26 are secured to the port 24 and the outer casing in a manner enabling them to function as the plug they replace. The transmitting/receiving optics pair 22, 26 are configured for operative association with the port 24 in the outer casing of the gas turbine so that the transmitting optic and the receiving optic are optically coupled by reflecting the beam 30 off a portion 32 of the inner casing 16 substantially opposite the port 24. As used herein, "substantially opposite" means positioned so that light reflects off the portion 32 of the inner casing in a near-specular manner between the transmitting/receiving optics pair. In this manner, a line of sight between the transmitting optic 22 and the receiving optic 26 can be achieved in the combustion zone of the gas turbine engine with minimal intrusion. In an alternative embodiment illustrated in Fig. 3, the transmitting optic 22 may
direct the beam 34 illustrated in phantom lines off the inner casing to a receiving optic 26 associated with a distinct port. In such an embodiment the portion 36 of the inner casing upon which the beam is reflected would be between the transmitting/receiving optics 22, 26. [0021] Returning to the embodiment illustrated in Fig. 4, the beam 30 is reflected off the portion 32 of the inner casing 16 in a near-specular manner so that it nearly retraces its path to the receiving optic 26 located in close proximity to the transmitting optic. The portion 32 of the inner casing may be polished or coated in some manner to increase the reflectivity of the portion 32 of the inner casing. The size of the portion may vary in accordance with tolerances, but a section as small as 5 mm in diameter may be sufficient to significantly improve the optical transmission. In addition or as an alternative to polishing a portion of the inner casing, a coating of a highly reflective material may be applied to the portion 32 of the inner casing. Alternatively or in addition, the portion 32 of the inner casing may be treated to resist collection of soot deposits. All manner of treating the portion 32 of the inner casing to improve reflectivity and minimize soot deposition are with the scope of the invention.
[0022] Fig. 5 illustrates schematically one embodiment of the present invention in the form of a system or sensing apparatus 50 for sensing, monitoring and control of a combustion process. The apparatus 50 comprises a tunable diode laser 52 that is optically coupled to an individual optical fiber 54 which may be a single mode optical fiber. The optical fiber 54 is further optically coupled to a transmitting optic 22 which may include a collimating lens or other optics suitable for producing a collimated transmitted beam 30. As used herein, "coupled" or "optically coupled" or "in optical communication with" is defined as a functional relationship between counterparts where light can pass from a first component to a second component either through or not through intermediate components or free space. The transmitting optic 22 and the receiving optic 26 are optically coupled to a port 24 in the cylindrical outer casing 14, whereby the beam 30 is transmitted off a portion 32 of the inner casing 16 to be received by the receiving optic 26. As depicted in Fig. 5, the portion 32 of the inner casing may be substantially opposite the port 24. The portion 32 may be treated to improve reflectivity or minimize soot collection as discussed above with respect to Fig. 4. The receiving optic 26 is optically coupled to a optical fiber 56, which may be a multi-mode optical fiber. Optical fiber 56 is optically coupled to a detector 58, which typically is a photodetector sensitive to the frequency of laser light generated by laser 52. The detector 58 generates an electrical signal based upon the nature and quantity of light transmitted to the detector 58. The electrical signal from the detector 58 is digitized and analyzed in a
computer or data processing system 60. The computer 60 is programmed to determine a combustion property, such as a concentration of at least one combustion species, based upon the output of the detector. The computer may further be programmed to control engine input parameters such as air and fuel provided to the combustion zone as a function of the concentration of the combustion species, as illustrated by the arrow 62. Alternatively, or in combination, the computer 60 may be programmed to determine an engine malfunction based upon the concentration of a combustion species and produce a warning signal. [0023] The invention contemplates the use of fiber optic coupling to the electronic and optical components on both the transmitting and receiving sides of the sensing apparatus 50 to allow delicate temperature sensitive apparatus such as the tunable diode laser 52, the detector 58 and the data processing system or computer 60 to be located in a suitable operating environment away from the gas turbine engine. Thus, only the relatively robust transmitting and receiving optics 22, 26 need to be situated near the hostile environment of the combustion chamber 12.
[0024] Fig. 6 schematically illustrates a multiplexed sensing apparatus 70 in accordance with the present invention. Like reference numbers refer to the same elements as Fig. 5. In this embodiment a plurality of tunable diode lasers 52A-52D are optically coupled to an optical fiber 72 (which may be a single mode optical fiber) and routed to a multiplexer 74. Within the multiplexer 74 laser light from some or all of the diode lasers 12A-12D is multiplexed to form a multiplexed beam having multiple select frequencies. The multiplexed beam is optically coupled to an optical fiber 75 and transmitted to the transmitting optic 22. A receiving optic 26 forms a transmitting/receiving optics pair with the transmitting optic 22. The transmitting/receiving optics pair 22, 26 are optically coupled to a port 24 in an outer cylindrical casing 14 of a gas turbine engine, as described with respect to Fig. 5. As with Fig. 5, the beam 82, which in this case is a multiplexed beam, is reflected off a portion 32 of the inner casing 16 for receipt by the receiving optic 26. The receiving optic 26 optically communicates with a demultiplexer 86 by means of optical fiber 88. The demultiplexer 86 demultiplexes multiplexed beams to discrete wavelengths and each wavelength is optically communicated to a corresponding detector 58A-58D, which in turn is coupled to the data processor or computer 90, which may be programmed as discussed above with respect to the computer 60 of Fig. 6.
[0025] The embodiment illustrated in Fig. 6 may include any number of tunable diode lasers 52A-52D generating a variety of wavelengths, though only four are illustrated for the sake of simplicity. A like number of photodiode detectors 58 are provided.
[0026] The multiplexer 74 and demultiplexer 86 may be components designed for use it the telecommunications industry. Suitable multiplexers/demultiplexers are described in greater detail in WO '496, referenced above. Other aspects of the method and apparatus for the monitoring and control of combustion described in WO '496 may be included with the apparatus described in Figs. 5 and 6 as necessary or desired. For example, using multiple sets of transmitting/receiving optics pairs and optical switches and/or routers to provide a beam of multiplexed light to each pair and for providing the beam to the detectors may be useful, particularly for a tomographic representation of combustion properties wherein the combustion zone.
[0027] In use, the surface of the inner casing may degrade over time due to deposition of carbonations material (essentially soot). It is anticipated that even with a fouled inner casing in which the reflectivity of the surface will degrade and become more highly scattered, approximately one part per million of the light will remain detectable. In this event, the measurement becomes more like a LIDAR (Laser Radar) in which back scattered laser light is observed from the inner casing surface instead of specular reflection. However, with the addition of laser modulation and frequency lock-in techniques as well as more efficient avalanche photodiode detectors, it is believed that these LIDAR-type measurements will be adequate for monitoring of combustion species.
EXAMPLE
[0028] The following example is provided for illustrative purposes only and is not intended to limit the scope of the invention.
[0029] Data was collected from a transmitting/receiving pair of optics associated with a portion of an inner casing. In this example, the portion of the inner casing which the beam was directed to had been bead-blasted, which produces a higher degree of scattering than a typical inner casting of an engine would provide. Four wavelengths were multiplexed onto a single mode fiber, collimated and then directed by a transmit optic onto the bead blasted portion of the inner casing. The receiving optic was positioned to catch the specular reflection from the portion of the inner casing. Fig. 7 is a table setting forth the reflecting data collected. The multiplexed wavelength beams were at the following wavelengths: 1 = 1348 nm; 2 = 1376 nm; 3 = 1394 nm and 4 = 1559 nm. These wavelengths were chosen as being useful for measuring combustion species such as water (H2O), carbon dioxide (CO2) and carbon monoxide (CO). Even with the bead-blasted, highly scattering material, Fig. 7 illustrates between 1000-2500 parts per million (0.1 - 0.25%) of the transmitted beam being
received by the receiving optic. By way of comparison, the light captured using a polished portion 32 of the inner casing was determined. The polished sample provided a reflectivity of approximately 200,000 parts per million, or approximately 20%. This example suggests that sufficient light from a beam can be transmitted to the receiving optic to enable measurement of combustion species.
[0030] While the invention has been particularly shown and described with reference to a number of embodiments, it would be understood by those skilled in the art that changes in the form and details may be made to the various embodiments disclosed herein without departing from the spirit and scope of the invention and that the various embodiments disclosed herein are not intended to act as limitations on the scope of the claims.
Claims
1. A method of measuring combustion properties within a combustion zone of a gas turbine engine, the combustion zone being defined between an inner and an outer casting, the method comprising: a) transmitting a beam from a transmit optic optically coupled to a port in the outer casing off a portion of the inner casing; and b) receiving a portion of the beam reflected off the portion of the inner casing with a receiving optic optically coupled to a port in the outer casing.
2. The method of claim 1 wherein the transmit optic and the receiving optic are optically coupled to the same port.
3. The method of claim 2 wherein the port is a preexisting borescope port provided by the engine manufacturer to observe a turbine blade during servicing.
4. The method of claim 1 further comprising in step a), transmitting a beam comprising a plurality of discrete multiplexed wavelengths.
5. The method of claim 4 further comprising: c) demultiplexing the portion of the beam received by the receiving optic into discrete wavelengths; and d) detecting at least one discrete wavelength of the demultiplexed beam.
6. The method of claim 5 further comprising: e) determining the concentration of at least one combustion species based upon the intensity of the at least one detected wavelength.
7. The method of claim 6 further comprising in step e), determining the concentration of a plurality of combustion species based upon the intensity of a plurality of detected discrete wavelengths.
8. The method of claim 7 further comprising: f) altering engine input parameters in response to select concentrations of the combustion species.
9. The method of claim 6 further comprising monitoring the concentration of the at least one combustion species to determine engine malfunction.
10. The method of claim 1 further comprising prior to step a), treating the portion of the inner casing to improve its reflectivity.
11. A gas turbine engine comprising: a combustion zone between an inner and outer casing; a port in the outer casing operatively associated with the combustion chamber substantially opposite a portion of the inner casing; and a transmitting and receiving pair of optics optically coupled with the port, the transmitting and receiving pair of optics being configured so that the transmitting optic transmits a beam off the portion of the inner casing and the receiving optic receives at least a portion of the beam reflected off the portion of the inner casing.
12. The gas turbine engine of claim 1 further comprising first and second ports in the outer casing operatively associated with the combustion chamber the transmitting optic being optically coupled with the first port and the receiving optic being optically coupled with the second port.
13. The gas turbine engine of claim 1 wherein the portion of the inner casing is treated to improve its reflectivity.
14. An apparatus for measuring combustion parameters of a gas turbine engine, the gas turbine engine having a combustion zone defined between an inner and an outer casting and port in the outer casing, the apparatus comprising: a laser generating a beam of light; a transmitting optic optically coupled to the laser transmitting the beam; and a receiving optic, the receiving optic and the transmitting optic being configured for operative association with the port in the outer casing of the gas turbine engine, whereby the transmitting optic and the receiving optic are optically coupled by reflecting the beam off a portion of the inner casing.
15. The apparatus of claim 14 further comprising: a plurality of lasers each generating a beam of a discrete wavelength; and a multiplexer optically coupled to the plurality of lasers for multiplexing the discrete wavelength beams into a multiplexed beam, the multiplexer being optically coupled to the transmitting optic.
16. The apparatus of claim 15 further comprising: a demultiplexer optically coupled to the receiving optic; and a detector optically coupled to the demultiplexer for detecting each discrete wavelength beam received by the receiving optic.
17. The apparatus of claim 16 further comprising a computer coupled to each detector, the computer being programmed to determine a concentration of at least one combustion species based upon an output of the detectors.
18. The apparatus of claim 17 further comprising the computer being programmed to control engine input parameters as a function of the concentration of the at least one combustion species.
19. The apparatus of claim 18 wherein the computer is programmed to determine engine malfunction based upon the concentration of the at least one combustion species.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP06850383.8A EP1952003B1 (en) | 2005-11-04 | 2006-11-06 | Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine |
ES06850383.8T ES2495719T3 (en) | 2005-11-04 | 2006-11-06 | Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine |
US12/092,673 US8544279B2 (en) | 2005-11-04 | 2006-11-06 | Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine |
JP2008539167A JP5180088B2 (en) | 2005-11-04 | 2006-11-06 | Method and apparatus for spectroscopic measurements in a combustor of a gas turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US73343105P | 2005-11-04 | 2005-11-04 | |
US60/733,431 | 2005-11-04 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2007087081A2 true WO2007087081A2 (en) | 2007-08-02 |
WO2007087081A3 WO2007087081A3 (en) | 2008-04-24 |
Family
ID=38309718
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2006/060572 WO2007087081A2 (en) | 2005-11-04 | 2006-11-06 | Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine |
Country Status (5)
Country | Link |
---|---|
US (1) | US8544279B2 (en) |
EP (1) | EP1952003B1 (en) |
JP (1) | JP5180088B2 (en) |
ES (1) | ES2495719T3 (en) |
WO (1) | WO2007087081A2 (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009042192A (en) * | 2007-08-11 | 2009-02-26 | Okayama Univ | Gas concentration detection device |
WO2009061586A2 (en) * | 2007-10-16 | 2009-05-14 | Zolo Technologies, Inc. | In situ optical probe and methods |
WO2011019755A1 (en) * | 2009-08-10 | 2011-02-17 | Zolo Technologies, Inc. | Mitigation of optical signal noise using a multimode transmit fiber |
EP2458351A1 (en) * | 2010-11-30 | 2012-05-30 | Alstom Technology Ltd | Method of analyzing and controlling a combustion process in a gas turbine and apparatus for performing the method |
FR2969291A1 (en) * | 2010-12-17 | 2012-06-22 | Gen Electric | SYSTEM AND METHOD FOR REAL-TIME MEASUREMENT OF THE WEALTH OF A MIXTURE OF GAS AND FUEL |
US8544279B2 (en) | 2005-11-04 | 2013-10-01 | Zolo Technologies, Inc. | Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine |
US9366621B2 (en) | 2012-04-19 | 2016-06-14 | Zolo Technologies, Inc. | In-furnace retro-reflectors with steerable tunable diode laser absorption spectrometer |
EP3109613A1 (en) * | 2015-06-26 | 2016-12-28 | Rolls-Royce Deutschland Ltd & Co KG | Monitoring system and turbo engine with a monitoring system |
Families Citing this family (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8371102B1 (en) * | 2008-02-26 | 2013-02-12 | Spectral Sciences, Inc. | Combustor control based on fuel modulation and passive optical sensors |
US20100171956A1 (en) * | 2009-01-07 | 2010-07-08 | Zolo Technologies, Inc. | Alignment Free Single-Ended Optical Probe and Methods for Spectroscopic Measurements in a Gas Turbine Engine |
DK2376840T3 (en) * | 2009-01-09 | 2019-02-04 | John Zink Co Llc | METHOD AND APPARATUS FOR MONITORING OF COMBUSTION PROPERTIES IN THE INTERIOR OF A HEAT WATER COOKER |
US8416415B2 (en) * | 2009-04-27 | 2013-04-09 | General Electric Company | Gas turbine optical imaging system |
US8456634B2 (en) * | 2009-06-15 | 2013-06-04 | General Electric Company | Optical interrogation sensors for combustion control |
US20110008737A1 (en) * | 2009-06-15 | 2011-01-13 | General Electric Company | Optical sensors for combustion control |
US8790006B2 (en) * | 2009-11-30 | 2014-07-29 | General Electric Company | Multiwavelength thermometer |
US8505303B2 (en) * | 2009-12-11 | 2013-08-13 | General Electric Company | Impurity detection in combustor systems |
US8528429B2 (en) * | 2010-01-20 | 2013-09-10 | Babcock & Wilcox Power Generation Group, Inc. | System and method for stabilizing a sensor |
WO2011143240A1 (en) * | 2010-05-10 | 2011-11-17 | Zolo Technologies, Inc. | Time-synchronized tdlas measurements of pressure and temperature in a gas turbine engine |
US8689536B2 (en) * | 2010-11-30 | 2014-04-08 | General Electric Company | Advanced laser ignition systems for gas turbines including aircraft engines |
EP2587154A1 (en) | 2011-10-24 | 2013-05-01 | Alstom Technology Ltd | Method for data acquisition from a combustion process |
US9335046B2 (en) * | 2012-05-30 | 2016-05-10 | General Electric Company | Flame detection in a region upstream from fuel nozzle |
US9435690B2 (en) * | 2012-06-05 | 2016-09-06 | General Electric Company | Ultra-violet flame detector with high temperature remote sensing element |
US10392959B2 (en) | 2012-06-05 | 2019-08-27 | General Electric Company | High temperature flame sensor |
US20140075954A1 (en) * | 2012-09-14 | 2014-03-20 | General Electric Company | Methods And Systems For Substance Profile Measurements In Gas Turbine Exhaust |
US9134199B2 (en) * | 2013-06-24 | 2015-09-15 | General Electric Company | Optical monitoring system for a gas turbine engine |
KR102291864B1 (en) | 2013-12-20 | 2021-08-23 | 온포인트 테크놀로지스, 엘엘씨 | Method and Apparatus for Monitoring Port Blockage for TDLAS Measurements in Harsh Environments |
CN105444201B (en) | 2014-09-26 | 2018-11-13 | 通用电气公司 | The method and its system of burning optimization |
US9773584B2 (en) | 2014-11-24 | 2017-09-26 | General Electric Company | Triaxial mineral insulated cable in flame sensing applications |
WO2017094965A1 (en) * | 2015-12-04 | 2017-06-08 | 인천대학교 산학협력단 | Device for diagnosing combustion state of gas turbine |
US10196927B2 (en) * | 2015-12-09 | 2019-02-05 | General Electric Company | System and method for locating a probe within a gas turbine engine |
US10196922B2 (en) * | 2015-12-09 | 2019-02-05 | General Electric Company | System and method for locating a probe within a gas turbine engine |
CN106017725B (en) * | 2016-05-26 | 2019-07-09 | 中国人民解放军战略支援部队航天工程大学 | A kind of measuring device suitable for Combustion Flow Field gas 2-d reconstruction |
US10392117B2 (en) * | 2016-09-23 | 2019-08-27 | General Electric Company | Icing condition detection using instantaneous humidity sensing |
FR3063809B1 (en) * | 2017-03-08 | 2019-03-22 | Safran Aircraft Engines | METHOD FOR NON-DESTRUCTIVE CONTROL OF A CARTER BY COLORIMETRY |
US10241036B2 (en) * | 2017-05-08 | 2019-03-26 | Siemens Energy, Inc. | Laser thermography |
GB201901320D0 (en) | 2019-01-31 | 2019-03-20 | Rolls Royce Plc | Gas turbine engine |
WO2023043639A1 (en) * | 2021-09-14 | 2023-03-23 | Micro-Combustion, Llc | System including cavitation impeller and turbine |
Family Cites Families (72)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3778170A (en) | 1972-11-02 | 1973-12-11 | Gen Electric | Borescope guide tube |
DE2730508A1 (en) | 1977-07-06 | 1979-01-25 | Bbc Brown Boveri & Cie | Contactless gap gauge for moving machine components - uses modulated light beam and pulse width detector to sense variation |
US4360372A (en) * | 1980-11-10 | 1982-11-23 | Northern Telecom Limited | Fiber optic element for reducing speckle noise |
US4573761A (en) * | 1983-09-14 | 1986-03-04 | The Dow Chemical Company | Fiber-optic probe for sensitive Raman analysis |
SE453017B (en) * | 1985-06-13 | 1988-01-04 | Opsis Ab Ideon | SET AND DEVICE FOR DETERMINING PARAMETERS FOR GASFUL SUBSTANCES PRESENT IN THE BURNING PROCESSES AND OTHER PROCESSES AT HIGH TEMPERATURE |
US4659195A (en) * | 1986-01-31 | 1987-04-21 | American Hospital Supply Corporation | Engine inspection system |
JPS62261037A (en) * | 1986-05-07 | 1987-11-13 | Hitachi Ltd | Cars optical apparatus |
US4712888A (en) * | 1986-08-04 | 1987-12-15 | Trw Inc. | Spatial light modulator systems |
US4915468A (en) * | 1987-02-20 | 1990-04-10 | The Board Of Trustees Of The Leland Stanford Junior University | Apparatus using two-mode optical waveguide with non-circular core |
US4741586A (en) * | 1987-02-20 | 1988-05-03 | The Board Of Trustees Of The Leland Stanford Junior University | Dynamic coupler using two-mode optical waveguides |
JPH0239145U (en) * | 1988-09-09 | 1990-03-15 | ||
US4989979A (en) * | 1989-01-17 | 1991-02-05 | Board Of Regents, The University Of Texas System | Optical fiber sensors with full common-mode compensation and measurand sensitivity enhancement |
US6016255A (en) * | 1990-11-19 | 2000-01-18 | Dallas Semiconductor Corp. | Portable data carrier mounting system |
US4980763A (en) * | 1989-06-12 | 1990-12-25 | Welch Allyn, Inc. | System for measuring objects viewed through a borescope |
US5042905A (en) * | 1990-06-15 | 1991-08-27 | Honeywell Inc. | Electrically passive fiber optic position sensor |
CA2112480A1 (en) * | 1992-04-28 | 1993-11-11 | Toshiya Hikami | External modulator for optical communication |
US5798840A (en) * | 1992-08-05 | 1998-08-25 | The Aerospace Corporation | Fast optical absorption tomography apparatus and method |
WO1994011708A1 (en) * | 1992-11-06 | 1994-05-26 | Martin Marietta Corporation | Interferometric optical sensor read-out system |
JPH0656759U (en) * | 1993-01-14 | 1994-08-05 | 石川島播磨重工業株式会社 | CARS laser measuring device |
US5448071A (en) * | 1993-04-16 | 1995-09-05 | Bruce W. McCaul | Gas spectroscopy |
US5396506A (en) * | 1993-12-09 | 1995-03-07 | United Technologies Corporation | Coupled multiple output fiber laser |
US5515158A (en) * | 1994-02-01 | 1996-05-07 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Retroreflection focusing schlieren system |
US5627934A (en) * | 1994-08-03 | 1997-05-06 | Martin Marietta Energy Systems, Inc. | Concentric core optical fiber with multiple-mode signal transmission |
DE19503929A1 (en) * | 1995-02-07 | 1996-08-08 | Ldt Gmbh & Co | Color imaging systems |
US5621213A (en) * | 1995-07-07 | 1997-04-15 | Novitron International Inc. | System and method for monitoring a stack gas |
US5748325A (en) * | 1995-09-11 | 1998-05-05 | Tulip; John | Gas detector for plural target zones |
EP0766080A1 (en) | 1995-09-29 | 1997-04-02 | FINMECCANICA S.p.A. AZIENDA ANSALDO | System and method for monitoring combustion and pollutants by means of laser diodes |
GB2309317A (en) * | 1996-01-17 | 1997-07-23 | Univ Southampton | Optical fibre device |
US5841546A (en) * | 1996-03-01 | 1998-11-24 | Foster-Miller, Inc. | Non-contact spectroscopy system and process |
JPH09257582A (en) * | 1996-03-21 | 1997-10-03 | Osaka Gas Co Ltd | Method and auxiliary tool for measuring light |
US5717209A (en) * | 1996-04-29 | 1998-02-10 | Petrometrix Ltd. | System for remote transmission of spectral information through communication optical fibers for real-time on-line hydrocarbons process analysis by near infra red spectroscopy |
US5828797A (en) * | 1996-06-19 | 1998-10-27 | Meggitt Avionics, Inc. | Fiber optic linked flame sensor |
US5993194A (en) * | 1996-06-21 | 1999-11-30 | Lemelson; Jerome H. | Automatically optimized combustion control |
US5774610A (en) * | 1996-07-08 | 1998-06-30 | Equitech Int'l Corporation | Fiber optic probe |
US6787758B2 (en) * | 2001-02-06 | 2004-09-07 | Baker Hughes Incorporated | Wellbores utilizing fiber optic-based sensors and operating devices |
US6016372A (en) | 1997-10-16 | 2000-01-18 | World Precision Instruments, Inc. | Chemical sensing techniques employing liquid-core optical fibers |
US5960129A (en) * | 1997-12-22 | 1999-09-28 | Bayer Corporation | Method and apparatus for detecting liquid and gas segment flow through a tube |
EP0988521A1 (en) * | 1998-04-14 | 2000-03-29 | Instrumentarium Corporation | Sensor assembly and method for measuring nitrogen dioxide |
US7398119B2 (en) * | 1998-07-13 | 2008-07-08 | Childrens Hospital Los Angeles | Assessing blood brain barrier dynamics or identifying or measuring selected substances, including ethanol or toxins, in a subject by analyzing Raman spectrum signals |
US6160255A (en) | 1998-10-05 | 2000-12-12 | The United States Of America As Represented By The Secretary Of The Army | Laser-based photoacoustic sensor and method for trace detection and differentiantion of atmospheric NO and NO2 |
EP1137928B1 (en) * | 1998-11-11 | 2005-04-06 | The University of Manchester | Chemical species distribution and mixture monitoring |
US6304692B1 (en) * | 1999-09-03 | 2001-10-16 | Zolo Technologies, Inc. | Echelle grating dense wavelength division multiplexer/demultiplexer with two dimensional single channel array |
US20020031737A1 (en) * | 2000-03-10 | 2002-03-14 | American Air Liquide, Inc. | Method for continuously monitoring chemical species and temperature in hot process gases |
US6455851B1 (en) * | 2000-03-28 | 2002-09-24 | Air Instruments And Measurement, Inc. | Spectroscopic remote sensing exhaust emission monitoring system |
CN1195202C (en) | 2000-09-15 | 2005-03-30 | 饶云江 | Integrated optical fibre strain and temp sensor device |
US6519385B1 (en) * | 2000-09-27 | 2003-02-11 | The Boeing Company | Method and apparatus for controllably positioning an optical fiber to introduce a phase shift |
US6473705B1 (en) * | 2000-10-10 | 2002-10-29 | General Electric Company | System and method for direct non-intrusive measurement of corrected airflow |
US20020158202A1 (en) * | 2001-01-08 | 2002-10-31 | Webber Michael E. | Laser-based sensor for measuring combustion parameters |
US6766070B2 (en) * | 2001-04-27 | 2004-07-20 | The United States Of America As Represented By The Secretary Of The Navy | High power fiber optic modulator system and method |
US6640199B1 (en) * | 2001-10-24 | 2003-10-28 | Spectral Sciences, Inc. | System and method for optically determining properties of hot fluids from the spectral structure of emitted radiation |
JP3616070B2 (en) * | 2002-04-30 | 2005-02-02 | 三菱重工業株式会社 | Gas temperature non-contact measuring device |
US20030210398A1 (en) | 2002-05-13 | 2003-11-13 | Robert Augustine | System and method for controlling a light source for cavity ring-down spectroscopy |
US7618825B2 (en) * | 2002-07-12 | 2009-11-17 | Alstom Technology Ltd. | Method for influencing and monitoring the oxide layer on metallic components of hot CO2/H20 cycle systems |
CN1723332B (en) * | 2002-08-30 | 2010-10-27 | 高速传感器有限公司 | Method and apparatus for logging a well using a fiber optic line and sensors |
FR2847670B1 (en) | 2002-11-26 | 2005-06-10 | Sc2N Sa | OPTICAL DETECTOR FOR THE PRESENCE OF GAS BUBBLES IN A LIQUID |
JP2004204787A (en) * | 2002-12-26 | 2004-07-22 | Toyota Central Res & Dev Lab Inc | Controlling device of power generation device |
CN101408459B (en) | 2003-03-31 | 2012-02-15 | 佐勒技术公司 | Method and device for monitoring and controlling combusting course |
US7075629B2 (en) * | 2003-05-12 | 2006-07-11 | Honeywell International Inc. | High temperature pyrometer |
EP1541808A1 (en) * | 2003-12-11 | 2005-06-15 | Siemens Aktiengesellschaft | Turbine component with a heat- and erosion resistant coating |
US7787728B2 (en) * | 2004-03-31 | 2010-08-31 | Zolo Technologies, Inc. | Optical mode noise averaging device |
US7080504B2 (en) * | 2004-07-23 | 2006-07-25 | Northrop Grumman Corporation | Laser augmented turbojet propulsion system |
US7340129B2 (en) * | 2004-08-04 | 2008-03-04 | Colorado State University Research Foundation | Fiber laser coupled optical spark delivery system |
US7324203B2 (en) * | 2005-02-08 | 2008-01-29 | General Electric Company | Method and apparatus for optical detection for multi-phase combustion systems |
US7291856B2 (en) * | 2005-04-28 | 2007-11-06 | Honeywell International Inc. | Sensor and methods for measuring select components in moving sheet products |
US7075653B1 (en) | 2005-04-29 | 2006-07-11 | Heath Consultants Incorporated | Method and apparatus for laser-based remote methane leak detection |
JP5180088B2 (en) | 2005-11-04 | 2013-04-10 | ゾロ テクノロジーズ,インコーポレイティド | Method and apparatus for spectroscopic measurements in a combustor of a gas turbine engine |
US7650050B2 (en) * | 2005-12-08 | 2010-01-19 | Alstom Technology Ltd. | Optical sensor device for local analysis of a combustion process in a combustor of a thermal power plant |
WO2007121032A2 (en) * | 2006-03-23 | 2007-10-25 | The Research Foundation Of State University Of New York | Optical methods and systems for detecting a constituent in a gas containing oxygen in harsh environments |
US7440097B2 (en) * | 2006-06-27 | 2008-10-21 | General Electric Company | Laser plasma spectroscopy apparatus and method for in situ depth profiling |
WO2008121844A1 (en) * | 2007-03-30 | 2008-10-09 | The General Hospital Corporation | System and method providing intracoronary laser speckle imaging for the detection of vulnerable plaque |
US7619742B2 (en) * | 2007-06-28 | 2009-11-17 | Wisconsin Alumni Research Foundation | High-speed spectrographic sensor for internal combustion engines |
US20100147835A1 (en) * | 2008-05-09 | 2010-06-17 | Mulpuri Rao V | Doped Gallium Nitride Annealing |
-
2006
- 2006-11-06 JP JP2008539167A patent/JP5180088B2/en not_active Expired - Fee Related
- 2006-11-06 WO PCT/US2006/060572 patent/WO2007087081A2/en active Application Filing
- 2006-11-06 US US12/092,673 patent/US8544279B2/en active Active
- 2006-11-06 ES ES06850383.8T patent/ES2495719T3/en active Active
- 2006-11-06 EP EP06850383.8A patent/EP1952003B1/en not_active Not-in-force
Non-Patent Citations (2)
Title |
---|
None |
See also references of EP1952003A4 |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8544279B2 (en) | 2005-11-04 | 2013-10-01 | Zolo Technologies, Inc. | Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine |
JP2009042192A (en) * | 2007-08-11 | 2009-02-26 | Okayama Univ | Gas concentration detection device |
WO2009061586A2 (en) * | 2007-10-16 | 2009-05-14 | Zolo Technologies, Inc. | In situ optical probe and methods |
WO2009061586A3 (en) * | 2007-10-16 | 2009-10-15 | Zolo Technologies, Inc. | In situ optical probe and methods |
RU2530686C2 (en) * | 2009-08-10 | 2014-10-10 | Золо Текнолоджиз, Инк. | Reduction of optic signal noise using multi-mode transmitting fibre |
WO2011019755A1 (en) * | 2009-08-10 | 2011-02-17 | Zolo Technologies, Inc. | Mitigation of optical signal noise using a multimode transmit fiber |
KR20120058512A (en) * | 2009-08-10 | 2012-06-07 | 졸로 테크놀러지스, 아이엔씨. | Mitigation of optical signal noise using a multimode transmit fiber |
EP2464846A1 (en) * | 2009-08-10 | 2012-06-20 | Zolo Technologies, Inc. | Mitigation of optical signal noise using a multimode transmit fiber |
KR101716917B1 (en) * | 2009-08-10 | 2017-03-15 | 졸로 테크놀러지스, 아이엔씨. | Mitigation of optical signal noise using a multimode transmit fiber |
AU2010282589B2 (en) * | 2009-08-10 | 2015-06-11 | Onpoint Technologies, Llc | Mitigation of optical signal noise using a multimode transmit fiber |
EP2464846A4 (en) * | 2009-08-10 | 2015-01-21 | Zolo Technologies Inc | Mitigation of optical signal noise using a multimode transmit fiber |
EP2458351A1 (en) * | 2010-11-30 | 2012-05-30 | Alstom Technology Ltd | Method of analyzing and controlling a combustion process in a gas turbine and apparatus for performing the method |
US8825214B2 (en) | 2010-11-30 | 2014-09-02 | Alstom Technology Ltd. | Method of analyzing and controlling a combustion process in a gas turbine and apparatus for performing the method |
US8625098B2 (en) | 2010-12-17 | 2014-01-07 | General Electric Company | System and method for real-time measurement of equivalence ratio of gas fuel mixture |
CN102608067A (en) * | 2010-12-17 | 2012-07-25 | 通用电气公司 | System and method for real-time measurement of equivalence ratio of gas fuel mixture |
FR2969291A1 (en) * | 2010-12-17 | 2012-06-22 | Gen Electric | SYSTEM AND METHOD FOR REAL-TIME MEASUREMENT OF THE WEALTH OF A MIXTURE OF GAS AND FUEL |
US9366621B2 (en) | 2012-04-19 | 2016-06-14 | Zolo Technologies, Inc. | In-furnace retro-reflectors with steerable tunable diode laser absorption spectrometer |
EP3109613A1 (en) * | 2015-06-26 | 2016-12-28 | Rolls-Royce Deutschland Ltd & Co KG | Monitoring system and turbo engine with a monitoring system |
Also Published As
Publication number | Publication date |
---|---|
EP1952003A2 (en) | 2008-08-06 |
WO2007087081A3 (en) | 2008-04-24 |
EP1952003A4 (en) | 2009-04-15 |
JP2009515079A (en) | 2009-04-09 |
JP5180088B2 (en) | 2013-04-10 |
US8544279B2 (en) | 2013-10-01 |
US20080289342A1 (en) | 2008-11-27 |
ES2495719T3 (en) | 2014-09-17 |
EP1952003B1 (en) | 2014-07-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US8544279B2 (en) | Method and apparatus for spectroscopic measurements in the combustion zone of a gas turbine engine | |
US20100171956A1 (en) | Alignment Free Single-Ended Optical Probe and Methods for Spectroscopic Measurements in a Gas Turbine Engine | |
AU2010282589B2 (en) | Mitigation of optical signal noise using a multimode transmit fiber | |
US20080285916A1 (en) | All-Fiber Architecture for an Embedded Flight Sensor for Aeropropulsion Applications | |
KR101331437B1 (en) | Reaction analyzer, recording medium, measurement system, and control system | |
TWI411726B (en) | Zuendkerze fuer eine brennkraftmaschine und betriebsverfahren hierfuer | |
JP2009515079A5 (en) | ||
CN110730903B (en) | Spectrum measuring method, spectrum measuring apparatus, and broadband pulse light source unit | |
US20120136483A1 (en) | Method of analyzing and controlling a combustion process in a gas turbine and apparatus for performing the method | |
US8702302B2 (en) | Hot gas temperature measurement in gas turbine using tunable diode laser | |
JP2010285988A (en) | Optical interrogation sensor for combustion control | |
KR20150042864A (en) | System for remote vibration detection on combustor basket and transition in gas turbines | |
US20130100445A1 (en) | Method for data acquisition | |
WO2000020844A1 (en) | Contaminant identification and concentration determination by monitoring the wavelength of the output of an intracavity laser | |
EP1129335A1 (en) | Contaminant identification and concentration determination by monitoring the intensity of the output of an intracavity laser | |
JP5336982B2 (en) | Gas detection device and fire detection device | |
WO2009061586A2 (en) | In situ optical probe and methods | |
JP5285553B2 (en) | Gas detection device and fire detection device | |
US20220357196A1 (en) | Measuring device comprising a connecting optical fibre and a measuring equipment for instrumentation of an aeronautical system, and an aeronautical system comprising such a measuring device | |
US20220136974A1 (en) | Systems and methods for stochastically modulated raman spectroscopy | |
JP2023533541A (en) | Laser heterodyne combustion efficiency monitor and related methods |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
ENP | Entry into the national phase |
Ref document number: 2008539167 Country of ref document: JP Kind code of ref document: A |
|
WWE | Wipo information: entry into national phase |
Ref document number: 12092673 Country of ref document: US |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2006850383 Country of ref document: EP |