Abstract: A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity. The at least one outlet opening is located in an upper surface of the angelwing. The at least one cooling passage receives pressurized cooling air channeled from the inner wheelspace, such that the pressurized cooling air is channeled into the at least one inlet opening and discharged from the at least one outlet opening.

Abstract: Embodiments of the present application include a gas turbine assembly. The gas turbine assembly may include a solid wheel, a turbine aft shaft, and an aft joint connecting the solid wheel to the turbine aft shaft. The turbine assembly also may include a cover plate positioned between the solid wheel and the turbine aft shaft. The cover plate may be configured to direct a flow of compressor extraction fluid inboard through the aft joint and out the turbine aft shaft.

Abstract: A system and method of cooling a radially outer surface of a rotor wheel post of a turbine wheel and a rotor wheel space between a turbine bucket and a rotor wheel post, including a turbine bucket having at least one cooling passage that extends between an inner cooling channel of the turbine bucket and an outer surface of a shank portion of the turbine bucket that directly faces a radially upper surface of the rotor wheel post, and using the cooling passage to direct cooling flow towards the radially upper surface of the rotor wheel post.

Abstract: Embodiments of the present application include a gas turbine assembly. The gas turbine assembly may include a solid wheel, a turbine aft shaft, and an aft joint connecting the solid wheel to the turbine aft shaft. The turbine assembly also may include a cover plate positioned between the solid wheel and the turbine aft shaft. The cover plate may be configured to direct a flow of compressor extraction fluid inboard through the aft joint and out the turbine aft shaft.

Abstract: A system for cooling an angelwing coupled to a rotor blade in a gas turbine engine is provided. An angelwing coupled to a shank of a rotor blade includes at least one cooling passage extending from at least one inlet opening coupled in flow communication with a gas turbine engine inner wheelspace to at least one outlet opening coupled in flow communication with a gas turbine engine outer rotor/stator cavity. The at least one outlet opening is located in an upper surface of the angelwing. The at least one cooling passage receives pressurized cooling air channeled from the inner wheelspace, such that the pressurized cooling air is channeled into the at least one inlet opening and discharged from the at least one outlet opening.

Abstract: A system for operating a gas turbine includes a controller configured to: receive input from a plurality of sensors that sense parameters of the gas turbine during operation; run a first model of the operation of the gas turbine from one or more of the parameters; determine one or more unmeasured variables of the operation from the first model; run a second model of process variables from one or more of the sensed parameters and one or more of the unmeasured variables; determine differences between the process variables and associated boundaries; and adjust one or more effectors of the gas turbine to maintain a predetermined margin between the process variables and hardware physical limits.

Abstract: A method for assembling a rotor assembly for use with a turbine engine. The method includes providing at least two rotor blades that each include a shank extending between a dovetail and a platform. The shank includes at least one cover plate that extends inwardly from the platform towards the dovetail. An airfoil extends outwardly from the platform. A first rotor blade is coupled to a rotor disk. A second rotor blade is coupled to the rotor disk, such that a cavity is defined between the first and second rotor blades, and such that a seal path is defined between a first rotor blade cover plate and a second rotor blade cover plate.

Abstract: Apparatus for controlling an amount of cooling air provided to a wheelspace of a turbine section of a gas turbine includes a sensor that senses a temperature of the wheelspace and provides a sensed temperature signal. The apparatus also includes a processor, responsive to the sensed temperature signal, that determines if the temperature of the wheelspace exceeds a desired value. If the temperature of the wheelspace exceeds the desired value, the processor activates an actuator control signal to control movement of a cooling air control valve to allow a greater amount of cooling air sourced from a compressor section of the gas turbine or from a cooling air cooler which receives air from the compressor section of the gas turbine to flow to the wheelspace, thereby cooling the temperature of the wheelspace.