Abstract: A method for tuning a gas turbine engine includes performing a sensitivity step process on a tuning parameter. An operating parameter is monitored. The gas turbine is operating in a first operational state and the operating parameter has an initial condition. The tuning parameter is selected for adjustment. The tuning parameter is adjusted by a predefined amount. The adjustment includes applying an incremental bias adjustment to a fuel flow fraction schedule. The gas turbine engine transitions to a second operational state, wherein the operating parameter has an adjusted condition. The adjusted condition and the initial condition of the operating parameter are applied to a cost function. It is then determined that the cost function results in a cost function value indicative of a decreased cost. The incremental bias adjustment and the cost function value is written to a bias look-up table and are associated with the selected tuning parameter.

Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of first vanes radially arrayed about a central axis of the injector and a plurality of second vanes radially arrayed about the central axis of the injector and disposed radially inward of the plurality of first vanes. A plurality of fuel injection holes are disposed nearer to a trailing edge than to a leading edge of the second vanes for injecting fuel into compressed air passing through over the second vanes. The trailing edge of each of the second vanes includes a non-planar profile configured to induce turbulence in the compressed air to thereby mix the fuel with the compressed air and reduce the surfaces on which undesirable flame anchoring may occur.

Abstract: A method for tuning a gas turbine engine includes performing a sensitivity step process on a tuning parameter. An operating parameter is monitored. The gas turbine is operating in a first operational state and the operating parameter has an initial condition. The tuning parameter is selected for adjustment. The tuning parameter is adjusted by a predefined amount. The adjustment includes applying an incremental bias adjustment to a fuel flow fraction schedule. The gas turbine engine transitions to a second operational state, wherein the operating parameter has an adjusted condition. The adjusted condition and the initial condition of the operating parameter are applied to a cost function. It is then determined that the cost function results in a cost function value indicative of a decreased cost. The incremental bias adjustment and the cost function value is written to a bias look-up table and are associated with the selected tuning parameter.

Abstract: A method for extending an operating window of an operating mode of a gas turbine engine includes monitoring operating conditions of the gas turbine engine. The gas turbine engine is prevented by the method from transitioning from the first operating mode up to a second operating mode. A bulk temperature demand of the gas turbine engine is adjusted by a predefined amount to generate a first biased bulk temperature demand. The adjustment includes applying a first incremental bias to a bulk flame temperature schedule. The operation of the gas turbine engine is then adjusted based on the first biased bulk temperature demand. The monitored operating conditions are analyzed to determine whether one of the operating conditions has reached a threshold value.

Abstract: A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.

Abstract: A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.

Abstract: Methods and systems for processing a signal indicative of at least one operating condition of a gas turbine engine to remove noise associated therewith are provided. The method and systems receive a signal from one or more sensors operably coupled to a gas turbine engine, retrieves one or more known system parameters and a previously determined average signal, and processes the signal using the system parameter and the previously determined average signal to remove noise therefrom. In some of the described methods and systems, the processed signal is then compared to predetermined upper and lower limits, and, if the processed signal exceeds the limits, at least one component of the gas turbine engine, such as a fuel-flow split, is adjusted in an effort to bring the signal back within the limits.

Abstract: Methods and systems for processing a signal indicative of at least one operating condition of a gas turbine engine to remove noise associated therewith are provided. The method and systems receive a signal from one or more sensors operably coupled to a gas turbine engine, retrieves one or more known system parameters and a previously determined average signal, and processes the signal using the system parameter and the previously determined average signal to remove noise therefrom. In some of the described methods and systems, the processed signal is then compared to predetermined upper and lower limits, and, if the processed signal exceeds the limits, at least one component of the gas turbine engine, such as a fuel-flow split, is adjusted in an effort to bring the signal back within the limits.

Abstract: The present invention discloses a fuel nozzle assembly and method for axially staging fuel injection. The fuel nozzle assembly comprises a plurality of vanes connected to a core, with an annular ring connectedly surrounding the plurality of vanes. Fuel is directed through the core and then through the vanes and is injected at different axial planes generally perpendicular to an oncoming air stream to obtain a broad spectrum of gas residence time between the point of fuel injection and the flame.

Abstract: Methods and systems for determining that a sensor, such as a pressure sensor, that provides feedback on one or more conditions of a gas turbine is deficient are provided. The amplitude of measurements from the sensor may be monitored in different frequency ranges in order to detect certain abnormal conditions of the gas turbine that require attention by the control system in one frequency range, and also, concurrently and/or separately, detect a sensor deficiency in another frequency range prior to actual failure of the sensor, at which time the failure may otherwise be noticeable in the first frequency range. This permits better detection of deficient sensors during operation of the gas turbine.

Abstract: The present invention discloses a novel apparatus and way for directing a supply of compressed air into a fuel nozzle assembly for mixing with a fuel source. The apparatus comprises a fuel nozzle assembly having a plurality of coaxial tubes and radially-extending swirler vanes for directing a supply of fuel to a mixing tube. Compressed air is directed to flow in a primarily axial direction by passing through a hemispherically-shaped dome portion at an air inlet region of the fuel nozzle assembly. The hemispherically-shaped dome includes a plurality of openings for directing air into the fuel nozzle assembly in a direction having a radial and axial component.

Abstract: Methods and systems for determining that a sensor, such as a pressure sensor, that provides feedback on one or more conditions of a gas turbine is deficient are provided. The amplitude of measurements from the sensor may be monitored in different frequency ranges in order to detect certain abnormal conditions of the gas turbine that require attention by the control system in one frequency range, and also, concurrently and/or separately, detect a sensor deficiency in another frequency range prior to actual failure of the sensor, at which time the failure may otherwise be noticeable in the first frequency range. This permits better detection of deficient sensors during operation of the gas turbine.

Abstract: The present invention discloses a novel apparatus and way for directing a supply of compressed air into a fuel nozzle assembly for mixing with a fuel source. The apparatus comprises a fuel nozzle assembly having one or more coaxial flow dividers and radially-extending swirler vanes for directing a supply of fuel to a mixing tube. Compressed air is directed to flow in a primarily axial direction by passing through one or more coaxial flow dividers spaced axially and radially about the air inlet region of the fuel nozzle assembly so as to form a non-uniform radial distribution of compressed air to the inlet region of the fuel nozzle assembly.

Abstract: The present invention discloses a fuel nozzle assembly and method for axially staging fuel injection. The fuel nozzle assembly comprises a plurality of vanes connected to a core, with an annular ring connectedly surrounding the plurality of vanes. Fuel is directed through the core and then through the vanes and is injected at different axial planes generally perpendicular to an oncoming air stream to obtain a broad spectrum of gas residence time between the point of fuel injection and the flame.

Abstract: The present invention discloses a novel apparatus and way for directing a supply of compressed air into a fuel nozzle assembly for mixing with a fuel source. The apparatus comprises a fuel nozzle assembly having a plurality of coaxial tubes and radially-extending swirler vanes for directing a supply of fuel to a mixing tube. Compressed air is directed to flow in a primarily axial direction by passing through a hemispherically-shaped dome portion at an air inlet region of the fuel nozzle assembly.

Abstract: The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels.

Abstract: An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine.

Abstract: The present invention discloses a novel way of controlling a gas turbine engine to reduce emissions levels when demand for power from the gas turbine engine is reduced. The operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide are kept within acceptable levels.

Abstract: A system and way for controlling a gas turbine engine in the event of a partial or full load rejection from a generator is disclosed. Upon detection of a partial or full load rejection, the fuel flow of the combustor is directed to a secondary circuit of a secondary fuel nozzle to maintain a flame in a downstream chamber of the combustor. By maintaining the flame in the downstream chamber while the engine speed is controlled, the recovery process to a load condition avoids use of spark ignition system and flame detectors in the upstream chamber.

Abstract: A tuning process is provided for monitoring fuel properties of a fuel being consumed by a gas turbine (GT) engine, and for dynamically tuning the GT engine as a function of changes to the monitored fuel properties. Initially, readings are taken from the GT engine during a reference calibration, or commissioning, and utilized to calculate an initial-pressure-drop reference value. The tuning process during commercial operation takes post-calibration readings from the GT engine to calculate a fuel property parameter, which represents a heating value of the fuel. Specifically, the fuel property parameter is calculated by deriving a corrected-pressure-drop dynamic value as a function of pressure and temperature readings of the fuel at a point upstream of a combustor and pressure drops across fuel nozzles that introduce the fuel into the combustor, and solving a ratio of the dynamic value and the reference value.