Abstract: A steam cycle system includes a heat recovery steam generator (HRSG) which receives exhaust gases, a steam turbine coupled to the HRSG which receives a first steam flow generated by the HRSG, and a condenser which condenses a second steam flow output by the steam turbine. The condenser includes a plurality of heat exchanger tubes, a fan, and a steam collection header. The system includes one or more sensors which measure one or more properties of the steam flow. The system includes a closed-loop controller communicatively coupled to the one or more sensors. The controller receives data from the one or more sensors, determines a flow rate of the second steam flow through the steam header using the one or more sensors, calculates whether the flow rate of the steam is within a threshold, and adjusts one or more operating parameters of the fan.

Abstract: A gas turbine engine propulsion system and method of assembling such is disclosed. The gas turbine engine propulsion system comprises a gas turbine engine that includes a fan flow path. The fan flow path may extend from the fan inlet to the rear exhaust outlet of the bypass flow path. A portion of the fan flow path, proximal to the fan, is non-axisymmetric. The non-axisymmetric portion may be upstream or downstream of the fan.

Abstract: The present disclosure is directed to a bundled tube type fuel nozzle assembly. The fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band that extends between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the fuel plenum. Each tube of the plurality of tubes includes an inlet defined along an outer surface of the forward plate and an outlet defined downstream from the inlet. The forward plate defines a plurality of fuel inlet slots that is in fluid communication with the fuel plenum. Each fuel inlet slot extends radially outwardly with respect to an axial centerline of the fuel plenum body along the outer surface of the forward plate.

Abstract: A gas turbine system includes a gas turbine engine configured to combust a fuel and produce an exhaust gas. An exhaust duct assembly is coupled to the gas turbine engine and is configured to receive the exhaust gas. An absorption chiller is fluidly coupled to the exhaust duct assembly and is configured to receive a take-off stream of the exhaust gas. The absorption chiller is configured to use the take-off stream to drive at least a portion of an absorption cooling process to generate a cooled take-off stream of exhaust gas. The exhaust duct assembly is configured to receive the cooled take-off stream of exhaust gas from the absorption chiller and to mix the cooled take-off stream with exhaust gas present within the exhaust duct assembly to cool the exhaust gas.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The annular body extends through the combustor wall and at least partially defines a quench aperture along a centerline through the combustor wall. The shell defines a first cooling aperture radially outwards of the annular body relative to the centerline and is configured to direct air to impinge against a portion of the annular body between the heat shield and the shell.

Abstract: A stationary gas turbine having at least one at least partially annular gas supply line, which is supported by a retainer, wherein the gas turbine has in the interior thereof a main flow direction of the working fluids, and wherein the retainer has at least one floor retainer supported against the floor and a face retainer attached to the housing of the gas turbine on the side opposite the floor retainer, and wherein both the floor retainer and the face retainer support the gas supply line against motion both in the main flow direction and perpendicularly thereto, wherein the face retainer has a spring system, which in particular compensates the change in the extent of the housing during operation of the gas turbine.

Abstract: A thrust reverser assembly for a gas turbine engine including a core engine, a nacelle surrounding at least a portion of the core engine defining a bypass duct between the nacelle and the core engine where an outer door movable between a stowed position and a deployed position extends outwards from the nacelle and a blocker door movable between a stowed position and an deployed position extends into an airflow conduit defined by the bypass duct to deflect air outwards.

Abstract: Various embodiments of the invention can include a portable power system with multiple power generation modes and mode based adjustable drag configuration. Embodiments of the invention include a system with an adjustable inlet ram air inlet, a ram air powered section (e.g. a ram air powered turbine with an adjustable ram air inlet), a fuel powered section, e.g., jet fuel powered auxiliary power unit, which is used when insufficient ram air is present or a power surge requires augmented power generation, and a generator section selectively coupled with the ram air powered section and the fuel powered section.