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: 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: The present invention discloses a novel apparatus and way for controlling combustion dynamics in a premix combustion system. The apparatus comprises a hemispherical dome assembly with a plurality of dome dampers having a predetermined damper volume and air supply with the damper in fluid communication with the combustion chamber. The dome dampers are pressurized with a volume of air to dampen pressure waves received from the combustion chamber. One or more combustor frequencies can be targeted through use of the present invention.

Abstract: The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture.

Abstract: A system and method for improving the cooling to a portion of a combustion liner of a gas turbine combustor is disclosed. The combustion liner is cooled by supplying air through a plurality of cooling holes arranged in axially spaced rows in an upper and lower portion of the liner. The cooling holes are spaced accordingly so as to direct additional cooling flow to an area of the combustion liner not receiving sufficient flow due to maldistributions of air from the compressor discharge.

Abstract: A tuning process is provided for dynamically tuning a gas-turbine (GT) engine to correct for flashback events without directly measuring occurrences of the flashback events at the GT engine. Initially, readings are taken that measure low-frequency dynamics at the GT engine. A determination of whether flashback criteria are met by an instantaneous signal that quantifies a detected spike within the measured low-frequency dynamics is carried out, where the flashback criteria include the following: identifying the spike overcomes a multiple of an average of the low-frequency dynamics measured over a predefined period of time; and identifying the spike overcomes a preestablished minimum amplitude. Upon the spike meeting the flashback criteria, a count is added to a running record of spikes, which is compared to an alarm limit. If the alarm limit is triggered, action(s) are invoked to address the flashback events, such as adjusting fuel-flow splits of the GT engine.

Abstract: The present invention discloses a novel apparatus and method for operating a gas turbine combustor having a structural configuration proximate a pilot region of the combustor which seeks to minimize the onset of thermo acoustic dynamics. The pilot region of the combustor includes a generally cylindrical extension having an outlet end with an irregular profile which incorporates asymmetries into the system so as to destroy any coherent structures.

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: The present invention discloses a novel apparatus and way for controlling combustion dynamics in a premix combustion system. The apparatus comprises a hemispherical dome assembly with a plurality of dome dampers having a predetermined damper volume and air supply with the damper in fluid communication with the combustion chamber. The dome dampers are pressurized with a volume of air to dampen pressure waves received from the combustion chamber. One or more combustor frequencies can be targeted through use of the present invention.

Abstract: A system and method for improving the cooling to a portion of a combustion liner of a gas turbine combustor is disclosed. The combustion liner is cooled by supplying air through a plurality of cooling holes arranged in axially spaced rows in an upper and lower portion of the liner. The cooling holes are spaced accordingly so as to direct additional cooling flow to an area of the combustion liner not receiving sufficient flow due to maldistributions of air from the compressor discharge.

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 novel and improved swirler assembly for use in a combustion liner of a gas turbine engine is disclosed. The swirler assembly is removable and sized to provide an improved assembly, repairability, and fit-up in the combustion liner. The swirler assembly includes a premix tube, premix swirler and a plurality of axially spaced mounting blocks for receiving removable fasteners for securing the swirler assembly to the combustor.

Abstract: A novel and improved combustion liner for use in a gas turbine engine is provided in which the premixer assembly is removably fastened to the combustion liner. Apparatus and method for removably securing the premixer assembly to the combustion liner is provided. A combustor dome plate, swirler assembly and inlet ring basket are coupled together by a plurality of removable fasteners in order to increase accessibility to portions of the combustion liner for inspection and repair processes.

Abstract: A system and method are provided for altering the natural frequency of a dome plate portion of a premixer assembly of a gas turbine combustor. The plate assembly has a dome plate with a central pilot mixer and a plurality of extension tabs extending radially outward from the pilot mixer. A plurality of radially extending struts are secured to the extension tabs in order to alter the natural frequency of the dome plate.

Abstract: A tuning process is provided for dynamically tuning a gas-turbine (GT) engine to correct for flashback events without directly measuring occurrences of the flashback events at the GT engine. Initially, readings are taken that measure low-frequency dynamics at the GT engine. A determination of whether flashback criteria are met by an instantaneous signal that quantifies a detected spike within the measured low-frequency dynamics is carried out, where the flashback criteria include the following: identifying the spike overcomes a multiple of an average of the low-frequency dynamics measured over a predefined period of time; and identifying the spike overcomes a preestablished minimum amplitude. Upon the spike meeting the flashback criteria, a count is added to a running record of spikes, which is compared to an alarm limit. If the alarm limit is triggered, action(s) are invoked to address the flashback events, such as adjusting fuel-flow splits of the GT engine.

Abstract: The present invention discloses a novel apparatus and method for operating a gas turbine combustor having a structural configuration proximate a pilot region of the combustor which seeks to minimize the onset of thermo acoustic dynamics. The pilot region of the combustor includes a generally cylindrical extension having an outlet end with an irregular profile which incorporates asymmetries into the system so as to destroy any coherent structures.

Abstract: The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture.

Abstract: The present invention discloses a novel apparatus and method for a mixing fuel and air in a gas turbine combustion system. The mixer helps to mix fuel and air while being able to selectively increase the fuel flow to a shear to a shear layer of a pilot flame in order to reduce polluting emissions. The mixer directs a flow of air radially inward into the combustion system and includes two sets of fuel injectors within each radially-oriented vane. A first plurality of fuel injectors operate independent of a second plurality of fuel injectors and the second plurality of fuel injectors are positioned to selectively modulate the fuel flow to the shear layer of the resulting pilot flame.