Abstract: Embodiments of the invention can provide systems and methods for using a combustion dynamics tuning algorithm with a multi-can combustor. According to one embodiment of the invention, a method for controlling a gas turbine engine with an engine model can be implemented for an engine comprising multiple cans. The method can include obtaining operating frequency information associated with multiple cans of the engine. In addition, the method can include determining variation between operating frequency information of at least two cans. Furthermore, the method can include determining a median value based at least in part on the variation. Moreover, the method can include inputting the median value to an engine model, wherein based at least in part on the median value, the engine model determines an engine control action. In addition, the method can include outputting a control command to implement the engine control action.

Abstract: A method of detecting onset of a gas turbine condition, such as compressor stall, includes receiving data indicative of an operating parameter of a compressor of the gas turbine. The method also includes performing a wavelet transformation on the data to generate wavelet transformed data. The wavelet transformation is configured to affect a processing characteristic regarding a performance of the wavelet transformation. Features indicative of onset of the gas turbine condition in the wavelet transformed data are then identified to provide an indication for controlling the gas turbine to prevent compressor stall from occurring. A system for detecting onset of compressor stall in a gas turbine includes a sensor for providing data indicative of an operating parameter of the compressor and a processor for performing a wavelet transform on the data to identify features of the optimized wavelet transformed data indicative of onset of stall.

Abstract: A gas turbine which can detect ignition in a combustor regardless of startup conditions of the gas turbine, such as the hot startup or the cold startup. An ignition detecting method for the gas turbine comprises the steps of calculating a difference between the exhaust temperature detected at a particular time before outputting of an ignition command for a combustor and the exhaust temperature detected after the outputting of the ignition command, and determining that the combustor is ignited, when the calculated difference is not less than a predetermined value. As an alternative, the method includes a step of determining that the combustor is ignited, when a change amount or rate of the exhaust temperature exceeds a predetermined value in a predetermined period from the outputting time of the ignition command.

Abstract: Control logic, and a method implemented by the control logic, compensates for mismatched inter turbine temperatures between two gas turbine engines and displays a biased inter turbine temperature (ITT) reading to the pilot without jeopardizing the need to be properly informed of the health of all engines and the relationship engine temperature compared to the maximum allowed temperature. A temperature compensation value is added to the lower inter turbine temperature to thereby increase the ITT to a value that is substantially equal to the higher ITT value. As a result, any potential nuisance or distraction that the flight crew may experience from displaying the mismatch is eliminated.

Abstract: Continuous engine monitoring with regard to gas turbine engines is difficult particularly when the engine is utilized for propulsion of an aircraft. Nevertheless, by use of transfer passages 4 to an arrangement located within the tail cone 9 of an engine, it is possible through a transparent test cell 6 and appropriate heating to generate sufficient infra red radiation as well as incandescent visible light for detectors 11, 16 to determine various constituent parts of the gas flow. Thus a photo detector 11 can provide through electrical signals, the proportion of soot/smoke particles in the gas flow through their incandescence, whilst use of filters 17 for particular spectral lines in an infra red radiation spectrum will allow detectors 16 to provide an indication through an electrical signal the proportion and presence of other constituents such as NO, CO and unburnt hydrocarbons in an exhaust gas flow.

Abstract: A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with the fuel nozzle for observing combustor flame characteristics. The optical sensor array includes a plurality of sapphire rods positioned to be close enough to the combustor flame to oxidize soot deposits thereon.

Abstract: A method, system and software for reducing combustion chamber to chamber variation in a multiple-combustion chamber turbine system comprising sensing dynamic combustion pressure tones emitted from combustion chambers in a multiple combustion chamber turbine and determining a combustion chamber stratification index for the combustion chambers from the dynamic combustion pressure tones emitted for the combustion chambers to record and/or tune combustion chamber performance variations in the multiple-chamber combustion turbine system.

Abstract: A premix burner is disclosed, with a swirl generator which delimits a conical swirl space and provides at least two conical part shells which are arranged, offset to one another, along a burner axis, mutually enclose in each case air inlet slits running longitudinally with respect to the burner axis and have in combination a conically widening premix burner outer contour having a maximum outside diameter which narrows axially into a region with a minimum outside diameter. At least one conical part shell provides, in the region between the maximum and the minimum outside diameter, a reception unit which deviates from the conically widening premix burner outer contour and locally elevates the premix burner outer contour radially outward and which has a maximum radial extent which is dimensioned smaller than half the maximum outside diameter of the premix burner outer contour.

Abstract: Method and arrangement for providing and controlling a gas turbine (1) at least one turbine (11, 20, 20?), at least one compressor (2, 5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in the airflow path. The gas turbine includes devices (8) for direct measurement of the air mass flow at a position upstream of the combustion chamber in the airflow path, with the aim of regulating the quantity of fuel that is delivered to the combustion chamber (16) on the basis of the measured air mass flow.

Abstract: A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is located within the fuel nozzle for observing combustion conditions within the combustor.

Abstract: A wear determination device for determining vibration in a turbine engine component to reduce wear in a turbine engine. The wear determination device may be capable of measuring vibrations in a turbine engine component. The vibration measurement may be used to determine vibrations in a turbine engine to identify wear locations and sources of wear. The wear determination device may be configured such that multiple locations in a turbine engine may be monitored on a single turbine engine by moving the wear determination device from location to location.

Abstract: A device for indicating a residual power margin of aircraft turbine engines includes a measuring stage associated with at least one turbine engine of an aircraft to measure a number of first parameters related to a power output of the engine; a calculating unit associated with the measuring unit to calculate at least one second parameter indicating the power output of the engine on the basis of the first parameters; and a display. The display includes a power scale having at least one reference indicator indicating an operating limit of the engine; and at least one cursor cooperating with the power scale and the reference indicator to simultaneously display a current value of the second parameter and an available power margin of the engine.

Abstract: A method of monitoring a physical parameter comprises receiving a sensor signal representative of an actual value from each of a plurality of sensors. The method further comprises calculating confidence value for each sensed value and a weighted average of actual values of the sensor signal by weighting each sensed value by the respective confidence value. The weighted average is used to determine a corresponding value of the sensed parameter.

Abstract: A method and apparatus for monitoring the exhaust path of a gas turbine engine for the presence of unwanted flames downstream from the main combustion chamber(s). The system is comprised of an Electro-Optics Module containing sensors and associated processing electronics as well as collection and transmitting optics, which relay the radiant energy generated by a flame event to the sensors. The information generated by the sensors is directly related to the time based intensity of the flame event, which can suggest problems associated with the condition of combustion related engine components. This information can then be used by the engine owner/operator to assess the condition of the engine and determine the more efficient required maintenance schedule.

Abstract: In a control system for a gas turbine engine that uses the outlet pressure of the turbine as an importation control parameter, when the high pressure sensor for detecting the outlet pressure of the turbine is found to be faulty, it is determined if an estimated value of the outlet pressure of the compressor is normal or not, and substitute the output value of the high pressure sensor with the estimated value if the estimated value is normal and with the inlet pressure of the fan or a value proportional thereto if the estimated value is not normal. Thereby, the control system is given with such a substitute value for the output of the high pressure sensor in case of a failure of the high pressure sensor that would prevent any abrupt changes in the behavior of the engine and allow the engine to be operated in a stable manner.

Abstract: The gas turbines of the present invention have multiple combustion chambers, and within each chamber are multiple fuel nozzles. Each nozzle has its own fuel control valve to control the fuel flowing to the nozzles. To minimize the pressure drop through the fuel control valves, multiple manifolds are employed. Each manifold supplies at least one fuel nozzle in multiple combustion chambers with fuel. The fuel control valves are mounted on the manifolds such that the weight of the fuel control valves and nozzles are carried by the manifolds, not the multiple combustion chambers. A plurality of thermocouples for measuring exhaust gas from said multiple combustion chambers are employed to sense gas exhaust temperature. In carrying out the methods of the present invention for tuning a gas turbine, it is essential to note that the most efficient gas turbine is one which has the least nitrous oxides, the least amount of unburned hydrocarbons, and the least amount of carbon monoxide for a specified energy output.

Abstract: A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.

Abstract: A method for identifying combustion characteristics of a plurality combustion chambers in a gas turbine, the method including: supplying fuel to the combustion chambers at a predetermined fuel rate; sensing combustion dynamic pressure in said plurality of combustion chambers and generating dynamic pressure signals representative of the dynamic pressure in each of said combustion chambers, wherein the dynamic pressure signals provide information regarding the dynamic pressure at a plurality of frequencies; segmenting the signals into a plurality of predefined frequency bands; determining a characteristic value for each of the segmented signals, and identifying an order of combustion chambers based on the characteristic value.

Abstract: Applicant's Differential-Pressure Torque Measurement System generates the torque signal from a differential gas pressure measured across the power turbine. The gas pressure differential is measured by using two pressure taps, the first tap taking the pressure reading of the expanding gas as the gas travels from the gas-generating turbine to the power turbine of the engine and the second tap taking the pressure reading of the gas as it escapes the engine through the exhaust port. The differential between the two pressure readings is determined. The pressure differential is then input to a processor which processes it in a pre-determined fashion along with the rotational speed signal of the power turbine, initial pressure and the temperature measurements of the air as the air is initially inlet into the engine. The result of the processing are various engine parameter indications including the torque.

Abstract: The invention relates to a system for driving an accessory, such as a fuel pump or an oil pump in a turboengine, said system comprising an electric motor and further comprising an air turbine associated with said electric motor. Said air turbine is suitable for being fed with a flow of air taken from a compressor of said turboengine and contributing to driving the accessory. The system also includes a valve for controlling the flow of air taken from the compressor, which valve is in the closed position while the turboengine is starting.

Abstract: A turbine plant includes a steam turbine, a gas turbine connected to the steam turbine, a generator, and an analyzing apparatus. The steam turbine includes a high pressure steam turbine, an intermediate pressure steam turbine, and a low pressure steam turbine. The turbine plant is adapted to be driven by a selected one of natural gas and oil. The analyzing apparatus collects estimates of the steam turbine output based on the inlet steam pressure of the intermediate steam turbine with a correction value. The correction value is calculated including the influence of the difference between the gas fuel case and the oil fuel case. The analyzing apparatus estimates a gas turbine output by calculating the difference between the estimated steam turbine output and the total output of the turbine plant. The gas turbine is operated using the estimated gas turbine output.

Abstract: A method for determining an estimated operating parameter for a gas turbine including the steps of: determining an estimated operating parameter using an algorithm have an input from a sensor, wherein the algorithm includes a trim factor; determining a first trim factor based on a comparison of the first estimated operating parameter and the output of the sensor when a condition of the sensor is in a first mode, and during a subsequent determination of the estimated operating parameter, applying the first trim factor to subsequently determine the estimated operating condition if the condition of second sensor is in a second mode.

Abstract: A method to ventilate a rotary machine housed in a compartment having a ventilation air inlet and air exhaust, a variable speed ventilation fan and a temperature sensor, wherein the method includes: sensing a temperature level of the rotary machine; applying the sensed machine temperature level to a controller for the fan; drawing ventilation flow through the compartment and over the machine; determining whether the sensed machine temperature level is above a desired temperature level of the rotary machine, wherein the desired temperature level is determined by the controller, and the controller setting an operational condition of the fan to increase the ventilation flow through the compartment if the sensed machine temperature level is above the desired temperature level.

Abstract: A method of determining the temperature inside a combustion liner without making a direct measurement of the actual temperature. The technique is based on a measurement of the frequency of one of the transverse acoustic modes occurring inside the combustion chamber. The frequency is determined from the transverse geometric dimensions of the combustion chamber and the speed of sound in the gas inside the combustion chamber. The speed of sound in the gas is known from thermodynamics to be a function of gas temperature and gas properties. Thus, from a measurement of the resonant frequency and knowing the combustor dimensions and gas properties, the temperature can be determined with accuracy.

Abstract: A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

Abstract: A gas turbine plant includes a combustion section, a turbine section, an exhaust section, a temperature detecting unit, and a monitoring unit. The combustion section combusts fuel using air to generate combustion gas. The turbine section is driven with the combustion gas from the combustion section. The exhaust section is connected to the turbine section to exhaust the combustion gas from the turbine section. The temperature detecting unit is provided in the exhaust section to measure a temperature of the combustion gas. The monitoring unit generates a warning signal based on a tolerable level and data corresponding to a temporal change of the temperature measured by the temperature detecting unit to indicate an extraordinary state of the gas turbine plant.

Abstract: A system is disclosed for adjusting a gas turbine firing temperature control algorithm and combustion reference temperature algorithms based on exhaust gas temperature, turbine pressure ratio and compressor discharge temperature for water content in the air entering the compressor differing from the design water content of ambient air. The water content in the ambient air is calculated by the control system from measured data from a dry bulb temperature sensor and a wet bulb temperature or humidity sensor.

Abstract: A gas turbine plant includes a combustion section, a turbine section, an exhaust section, a temperature detecting unit, and a monitoring unit. The combustion section combusts fuel using air to generate combustion gas. The turbine section is driven with the combustion gas from the combustion section. The exhaust section is connected to the turbine section to exhaust the combustion gas from the turbine section. The temperature detecting unit is provided in the exhaust section to measure a temperature of the combustion gas. The monitoring unit generates a warning signal based on a tolerable level and data corresponding to a temporal change of the temperature measured by the temperature detecting unit to indicate an extraordinary state of the gas turbine plant.

Abstract: A fuel gas processed and preheated in a processing unit (6) is burned in a gas turbine unit or in a boiler plant. A continuously operating detector (9) for determining the condensate content in the processed fuel gas is arranged in a line (5) connecting the processing unit (6) with the burner immediately before the burner. This detector (9) is connected to an alarm device (10) and to a shut off device (11).

Abstract: A gas turbine plant includes a combustion section, a turbine section, an exhaust section, a temperature detecting unit, and a monitoring unit. The combustion section combusts fuel using air to generate combustion gas. The turbine section is driven with the combustion gas from the combustion section. The exhaust section is connected to the turbine section to exhaust the combustion gas from the turbine section. The temperature detecting unit is provided in the exhaust section to measure a temperature of the combustion gas. The monitoring unit generates a warning signal based on a tolerable level and data corresponding to a temporal change of the temperature measured by the temperature detecting unit to indicate an extraordinary state of the gas turbine plant.

Abstract: An anti-condensation device for a flame sensor (10) of a combustion chamber (12), wherein the sensor (10) is disposed outside the combustion chamber (12) and determines the presence of the combustion flame by means of an aperture (14) provided in a wall of the chamber (12); the device comprises at least two tubular structures (22, 24), one of which (24) surrounds the other (22) at least partially, an annular space in which air flows being provided between these two structures (22, 24).

Abstract: A system and a method for detecting gas turbine engine hot section condition using temperature measurements during engine operation. The system comprises a sensing unit for sensing a temperature distribution across a hot combustion gas stream generated by a gas turbine engine combustor. A signal processor receives temperature signals from the sensing unit and generates a combustor malfunction signal when the difference between a maximal temperature and a minimal temperature of the sensed temperature distribution is greater than a predetermined acceptable delta value.

Abstract: A system is disclosed for adjusting a gas turbine firing temperature control algorithm and combustion reference temperature algorithms based on exhaust gas temperature, turbine pressure ratio and compressor discharge temperature for water content in the air entering the compressor differing from the design water content of ambient air. The water content in the ambient air is calculated by the control system from measured data from a dry bulb temperature sensor and a wet bulb temperature or humidity sensor.

Abstract: A gas turbine engine (40) having an active combustion control system (54) including a sensor element (44) positioned proximate the combustion chamber (46) as part of a sensor assembly (84) including a spring-action bellows (74). The sensor assembly is installed through an opening (69) in the casing (48) of the engine to make contact with the combustor wall (62). The bellows is compressed from its resting position by tightening mounting bolts (70) against a mounting flange (66) of the sensor assembly. The spring action of the bellows ensures contact between the sensing assembly and the combustor wall in spite of differential thermal growth between the casing and the combustor. The sensor element may be replaced by simply removing the mounting bolts without further disassembly of the engine.

Abstract: A dynamic pressure probe includes a holder body having a first passage therein adapted to receive a pressure signal, a pressure sensor including at least a pressure sensing portion located within a sleeve seated within a pressure sensor housing portion, the sleeve engaged with a wall of the housing portion; the pressure sensor including a diaphragm having one face exposed to a pressure chamber within the sleeve between the pressure sensor and the wall; wherein an aperture in the wall of the housing connects the pressure chamber to the first passage; and wherein the first passage continues axially beyond the aperture in a flow direction an acoustic damping coil wound about a vertical axis.

Abstract: Use of an optical fiber for the direct receipt of heat radiation for transmission to a remote pyrometer is enabled by the provision of an apertured, contaminant free compartment in the component being heated, and aligning the heat receiving end of the optical fiber with the aperture so as to receive radiated heat from within the compartment.

Abstract: A gauge for measuring heat flux, especially heat flux encountered in a high temperature environment, is provided. The gauge includes at least one thermocouple and an anisotropic pyrolytic graphite body that covers at least part of, and optionally encases the thermocouple. Heat flux is incident on the anisotropic pyrolytic graphite body by arranging the gauge so that the gauge surface on which convective and radiative fluxes are incident is perpendicular to the basal planes of the pyrolytic graphite. The conductivity of the pyrolytic graphite permits energy, transferred into the pyrolytic graphite body in the form of heat flux on the incident (or facing) surface, to be quickly distributed through the entire pyrolytic graphite body, resulting in small substantially instantaneous temperature gradients. Temperature changes to the body can thereby be measured by the thermocouple, and reduced to quantify the heat flux incident to the body.

Abstract: A mounting device for mounting an optical sensor to a combustor basket of a combustion gas turbine engine includes a base, an alignment member, and a clamp. The base is mounted over an access hole formed in the combustor basket and is formed with a spherical socket. The alignment member carries the optical sensor and includes a ball that is adjustably received in the socket. During alignment of the alignment member, a laser or other directed light source is applied to the end of the optical sensor. The laser delivers a laser beam that shines out of the optical sensor and permits the alignment member and the optical sensor to be properly aligned. The clamp selectively applies a non-rotational clamping force to the ball of the alignment member to clamp the alignment member in a given orientation with respect to the base.

Abstract: A flameout detection system for an engine that facilitates detection of flameout in the engine in a cost-effective and reliable manner is described. A method implemented by the device includes the steps of detecting a rate of change of gas generator speed, also described as engine deceleration rate, and declaring a flameout if a deceleration rate of the engine is greater than a pre-determined threshold.