Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A blocker is provided at an outlet portion of each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes and/or the radially inner subset of air/fuel mixing tubes to form a flame anchoring surface.

Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A static air plenum surrounds each of the air/fuel mixing tubes to thermally isolate the air/fuel mixing tube from the respective fuel manifold.

Abstract: A combustor of a gas turbine engine is provided with a first injector and a second injector. The first injector surrounds a combustion liner and is positioned at a downstream end of a flow sleeve. A dome plate is positioned to receive a fuel/air mixture from the first injector and turn it 180 degrees to enter a combustion zone formed within the combustion liner. The second injector is positioned radially inward of the combustion liner at an inlet end of the combustion zone and receives only compressed air from the first injector. The second injector includes a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes.

Abstract: An inner shroud block component for a gas turbine. The inner shroud block has a radially inward facing surface with an abradable material applied thereto. The abradable material includes a zone of ridges that extend radially inwardly from the radially inward facing surface to minimize the clearance between the inner shroud block and the blade tip of a turbine blade. The abradable material may be ceramic and may be abraded by the blade tip if contact occurs between the blade tip and the inner shroud block. The zone of ridges extend along the radially inward facing surface in parallel to a direction of rotation of the turbine blade.

Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. Each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes includes a substantially quadrilateral cross-sectional profile, and each of the air/fuel mixing tubes of the radially inner subset of air/fuel mixing tubes includes a substantially circular cross-sectional profile.

Abstract: A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner diameter to an outer diameter and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a hollow airfoil including a plurality of cavities positioned in the airfoil, an insert positioned in one or more of the plurality of cavities of the hollow airfoil, a plurality of cover plates, at least one of which is positioned at one of the inner diameter and at the outer diameter, and a plurality of impingement pans, at least one of which is positioned at one of the inner diameter and at the outer diameter.

Abstract: A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner diameter to an outer diameter and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a hollow airfoil including a plurality of cavities positioned in the airfoil, an insert positioned in one or more of the plurality of cavities of the hollow airfoil, a plurality of cover plates, at least one of which is positioned at one of the inner diameter and at the outer diameter, and a plurality of impingement pans, at least one of which is positioned at one of the inner diameter and at the outer diameter.

Abstract: A turbine blade for a gas turbine engine. The turbine blade includes an airfoil having a tip cavity. The tip cavity has a floor bounded by a wall. A pocket opening is formed in the wall proximate a trailing edge of the turbine blade. A passageway communicates cooling medium from an internal cooling circuit to a cooling hole formed in part through the floor and in part through the trailing edge.

Abstract: A turbine blade for a gas turbine engine. The turbine blade includes an airfoil having a tip cavity. The tip cavity has a floor bounded by a wall. A pocket opening is formed in the wall proximate a trailing edge of the turbine blade. A passageway communicates cooling medium from an internal cooling circuit to a cooling hole formed in part through the floor and in part through the trailing edge.

Abstract: An inner shroud block component for a gas turbine. The inner shroud block has a radially inward facing surface with an abradable material applied thereto. The abradable material includes a zone of ridges that extend radially inwardly from the radially inward facing surface to minimize the clearance between the inner shroud block and the blade tip of a turbine blade. The abradable material may be ceramic and may be abraded by the blade tip if contact occurs between the blade tip and the inner shroud block. The zone of ridges extend along the radially inward facing surface in parallel to a direction of rotation of the turbine blade.

Abstract: A turbine blade for a gas turbine engine. The turbine blade includes a cooling path for a coolant, routing the coolant through an internal cooling cavity and out through a plurality of cooling holes formed proximate a trailing edge of the turbine blade. Each of the cooling holes including a diffusing region designed so that a coolant does not separate from a radially inward sidewall of the diffusing region.

Abstract: An inner shroud block component for a gas turbine. The inner shroud block has a surface with a plurality of wells formed therein. An array of protuberances extend away from a base surface of each of the wells. The array of protuberances produces convective cooling of the inner shroud block, resulting in increased cooling of the inner shroud block and better part life. The increased cooling capacity also allows the turbine to operate at higher temperatures, which results in additional power generation.

Abstract: A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner platform to an outer platform and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a plurality of vanes attached to the inner and outer platforms and the inner platform having an attached first and second endfaces and a flow surface surrounding opposing ends of a vane of the plurality of vanes, the flow surface terminating circumferentially at the first and second endfaces and terminating axially at forward and aft edges, and the inner platform may include a platform corner portion comprising the flow surface attached to the first endface at the forward edge and attached to the second endface at the aft edge.