Abstract: A method for manufacturing and heat treating a component formed from an alloy or superalloy. The component may be part of a gas turbine engine, such as an airfoil of a gas turbine engine turbine, or a combustor fuel nozzle, that includes internal cooling passages. At least part of the component is formed from the alloy or superalloy using an additive manufacturing process. The method includes determining an incipient melting point range and a recrystallization temperature of the alloy or superalloy. The component is then heated to at least the recrystallization temperature and within the incipient melting point range for a predetermined time, and ultimately cooled.

Abstract: The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.

Abstract: Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.

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 sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion, and a transition portion, the compressible seal regulates airflow passing through the compressible seal via a plurality of openings and/or axially extending slots.

Abstract: A method for manufacturing and heat treating a component formed from an alloy or superalloy. The component may be part of a gas turbine engine, such as an airfoil of a gas turbine engine turbine, or a combustor fuel nozzle, that includes internal cooling passages. At least part of the component is formed from the alloy or superalloy using an additive manufacturing process. The method includes determining an incipient melting point range and a recrystallization temperature of the alloy or superalloy. The component is then heated to at least the recrystallization temperature and within the incipient melting point range for a predetermined time, and ultimately cooled.

Abstract: The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.

Abstract: Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.

Abstract: The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.

Abstract: The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion, and a transition portion, the compressible seal regulates airflow passing through the compressible seal via a plurality of openings and/or axially extending slots.

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 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: The present invention relates to a self actuating rotary dust valve particularly for discharging dust from an engine air cleaner. The rotary dust valve includes a valve body having an inlet port, an outlet port and a rotor chamber interposed therebetween. A rotary dust ejection member is enclosed in the rotor chamber and supported for rotation about a fixed axis. A plurality of fin members are provided angularly spaced about and secured to the hub member. Adjacent pairs of the fin members define at least one dust pocket therebetween to receive dust from the air cleaner to be ejected. The rotor chamber and the fin members are cooperatively shaped and configured to maintain a continuous air lock closure. The dust valve is operable by any of: gravity and vibration to rotate and thereby to discharge the dust buildup through the outlet port or alternately by other drive means.

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.

Abstract: A modular cyclone precleaner system includes one or more standardized and reusable modular cyclone blocks configured in parallel. The modular cyclone blocks are provided as components designed for reuse across differing precleaner systems for potentially different precleaner applications, providing standardized component building blocks and reducing manufacturing cost. The modular cyclone blocks are designed to be selectively combinable to provide a cyclone precleaner system having the required gas flow characteristics and particulate removal capabilities required for any given precleaner application. The precleaner system includes a housing that is sized for at least one given precleaner application and adapted to supportively receive the selectively combined modular cyclone blocks for the application.

Abstract: The present invention relates to a self actuating rotary dust valve particularly for discharging dust from an engine air cleaner. The rotary dust valve includes a valve body having an inlet port, an outlet port and a rotor chamber interposed therebetween. A rotary dust ejection member is enclosed in the rotor chamber and supported for rotation about a fixed axis. A plurality of fin members are provided angularly spaced about and secured to the hub member. Adjacent pairs of the fin members define at least one dust pocket therebetween to receive dust from the air cleaner to be ejected. The rotor chamber and the fin members are cooperatively shaped and configured to maintain a continuous air lock closure. The dust valve is operable by any of: gravity and vibration to rotate and thereby to discharge the dust buildup through the outlet port or alternately by other drive means.

Abstract: A modular cyclone precleaner system includes one or more standardized and reusable modular cyclone blocks configured in parallel. The modular cyclone blocks are provided as components designed for reuse across differing precleaner systems for potentially different precleaner applications, providing standardized component building blocks and reducing manufacturing cost. The modular cyclone blocks are designed to be selectively combinable to provide a cyclone precleaner system having the required gas flow characteristics and particulate removal capabilities required for any given precleaner application. The precleaner system includes a housing that is sized for at least one given precleaner application and adapted to supportively receive the selectively combined modular cyclone blocks for the application.