Abstract:
The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.
Abstract:
The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle.
Abstract:
The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a conical liner support supporting the liner.
Abstract:
Additive manufacturing techniques may be utilized to construct effusion plates. Such additive manufacturing techniques may include defining a configuration for an effusion plate having one or more internal cooling channels. The manufacturing techniques may further include depositing a powder into a chamber, applying an energy source to the deposited powder, and consolidating the powder into a cross-sectional shape corresponding to the defined configuration. Such methods may be implemented to construct an effusion plate having one or more channels with a curved cross-sectional geometry.
Abstract:
Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.
Abstract:
An object includes an annular outer body having an end and an interior surface; a first annular inner body disposed inside the annular outer body, the first annular inner body having an exterior surface defining a first annular passage with the interior surface of the annular outer body. The first annular passage includes a first plurality of outlets formed on the end of the annular outer body, the first annular passage receiving a coolant and discharging the coolant adjacent the end of the annular outer body. The object also includes a second annular inner body disposed inside the first annular inner body, the second annular inner body defining a second annular passage with the first annular inner body. Further, the object includes a third annular inner body disposed inside the second annular inner body, with the third annular inner body defining a third annular passage with the second annular inner body; and a fourth annular passage opposite and surrounded by the third annular passage. The object further includes a plurality of suspension elements connecting the interior surface of the annular outer body to the exterior surface of the first annular inner body, each suspension element including a first end connected to a first position on the first inner annular body and a second end connected to a second position on the annular outer body, wherein each first position is angularly circumferentially offset from each second position; and each suspension element is configured to substantially rigidly locate a position of the annular outer body relative to the first annular inner body in axial and lateral directions while permitting controlled deflection in a radial direction wherein the first position of each suspension element is angularly circumferentially offset to provide an imbalanced suspension capable of addressing an imbalanced loading, wherein each suspension element has an at least partially tear-shaped cross-section, and each of the second annular passage, the third annular passage, and the fourth annular passage includes a plurality of outlets formed through the annular outer body, adjacent the end, each of the plurality of outlets for each of the second annular passage, the third annular passage, and the fourth annular passage delivering a gas or fuel adjacent the end of the annular outer body.
Abstract:
An object includes an annular outer body having an end and an interior surface; a first annular inner body disposed inside the annular outer body, the first annular inner body having an exterior surface defining a first annular passage with the interior surface of the annular outer body. The first annular passage includes a first plurality of outlets formed on the end of the annular outer body, the first annular passage receiving a coolant and discharging the coolant adjacent the end of the annular outer body. The object also includes a second annular inner body disposed inside the first annular inner body, the second annular inner body defining a second annular passage with the first annular inner body. Further, the object includes a third annular inner body disposed inside the second annular inner body, with the third annular inner body defining a third annular passage with the second annular inner body; and a fourth annular passage opposite and surrounded by the third annular passage. The object further includes a plurality of suspension elements connecting the interior surface of the annular outer body to the exterior surface of the first annular inner body, each suspension element including a first end connected to a first position on the first inner annular body and a second end connected to a second position on the annular outer body, wherein each first position is angularly circumferentially offset from each second position; and each suspension element is configured to substantially rigidly locate a position of the annular outer body relative to the first annular inner body in axial and lateral directions while permitting controlled deflection in a radial direction wherein the first position of each suspension element is angularly circumferentially offset to provide an imbalanced suspension capable of addressing an imbalanced loading, wherein each suspension element has an at least partially tear-shaped cross-section, and each of the second annular passage, the third annular passage, and the fourth annular passage includes a plurality of outlets formed through the annular outer body, adjacent the end, each of the plurality of outlets for each of the second annular passage, the third annular passage, and the fourth annular passage delivering a gas or fuel adjacent the end of the annular outer body.
Abstract:
An object includes an annular outer body having an interior surface; and an annular inner body disposed inside the annular outer body, the annular inner body having an exterior surface defining an annular passage with the interior surface of the annular outer body. A plurality of suspension elements connects the interior surface of the annular outer body to the exterior surface of the annular inner body, each suspension element configured to substantially rigidly locate a position of the annular outer body relative to the annular inner body in axial and lateral directions while permitting controlled deflection in a radial direction. Each suspension element has an at least partially tear-shaped cross-section.
Abstract:
A micro-mixer nozzle for use in a combustor of a combustion turbine engine, the micro-mixer nozzle including: a fuel plenum defined by a shroud wall connecting a periphery of a forward tube sheet to a periphery of an aft tubesheet; a plurality of mixing tubes extending across the fuel plenum for mixing a supply of compressed air and fuel, each of the mixing tubes forming a passageway between an inlet formed through the forward tubesheet and an outlet formed through the aft tubesheet; and a wall mixing tube formed in the shroud wall.
Abstract:
The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.