Abstract: A system for heating fuel in a combined cycle gas turbine includes a fuel heat exchanger downstream from a turbine outlet, and the fuel heat exchanger has an exhaust gas inlet, an exhaust gas outlet, a fuel inlet, and a fuel outlet. A first exhaust gas plenum has a first exhaust gas inlet connection between the turbine outlet and a heat exchanger and a first exhaust gas outlet connection upstream from the exhaust gas inlet. A second exhaust gas plenum has a second exhaust gas inlet connection downstream from at least a portion of the heat exchanger and a second exhaust gas outlet connection upstream from the exhaust gas inlet.

Abstract: Embodiments are directed to a ventilation unit configured to exhaust drawn-in air from an enclosure, and a detection unit integrated with the ventilation unit and configured to detect a vapor. Embodiments are directed to a collection mechanism configured to collect liquid, a detection unit configured to sample vapor emitted from the liquid of the collection mechanism, and a ventilation unit integrated with the detection unit and configured to exhaust the vapor subsequent to the vapor having been sampled by the detection unit.

Abstract: An approach for utilizing fuel gas to purge a dormant fuel gas circuit is disclosed. In one aspect, there is a fuel gas supply that supplies fuel to fuel gas circuits. Gas control valves, each coupled to one of the fuel gas circuits control the flow of fuel gas thereto from the fuel gas supply. A fuel purge system selectively purges fuel gas circuits from the fuel gas circuits that are dormant with fuel gas from the fuel gas supply.

Abstract: A system is provided and includes first and second water supplies at first and second relatively high and low temperatures, respectively, a heat exchanger, coupled to the water supplies, through which fuel and relative amounts of the water supplies at the first and second temperatures flow for fuel heating and a controller, operably interposed between the water supplies and the heat exchanger, to select and/or modulate the relative amounts of the water supplies permitted to flow through the heat exchanger to heat the fuel to a temperature based on a heating requirement to meet a modified wobbe index (MWI) rating.

Abstract: The present application provides a gas turbine engine system for combusting a flow of fuel. The gas turbine engine system may include a combustor and a fuel system for providing the flow of fuel to the combustor. The fuel system may include a fuel heat exchanger so as to provide the flow of fuel to the combustor at a substantially constant temperature.

Abstract: An apparatus, a system and a method by which fuel gas to drive a heat source is heated are provided. The apparatus includes a first gas passage by which at least a portion of the fuel gas is transported from an inlet to an outlet, the outlet being fluidly coupled to the heat source, a plurality of heat pipes in thermal communication, at respective first ends thereof, with the portion of the fuel gas transported by the first gas passage, and a heating element, fluidly coupled to the heat source to receive exhaust of the heat source, through which respective second ends of the heat pipes extend to be in position to be heated by the exhaust.

Abstract: The present application provides a gas turbine engine system for combusting a flow of fuel. The gas turbine engine system may include a combustor and a fuel system for providing the flow of fuel to the combustor. The fuel system may include a fuel heat exchanger so as to provide the flow of fuel to the combustor at a substantially constant temperature.

Abstract: A turbine includes: a plurality of turbine blades arranged within a casing, the arrangement including a clearance between tips of the blades and the casing; a plurality of manifolds disposed proximate to the casing opposite the clearance, wherein each of the manifolds includes a plurality of impingement holes in the surface thereof; a source of clearance information; and a source of cooling air for supplying cooling air through a plurality of flow control devices to selected ones of the manifolds according to the clearance information. A system and a method are also provided.

Abstract: An ejector for a turbine engine is described herein. The ejector may include a variable geometry motive nozzle and a variable geometry mixing tube positioned downstream of the variable geometry motive nozzle.

Abstract: A mount includes a mounting bolt attached to a casing; an internal bushing that engages the casing at a distal end of the internal bushing; and an external bushing that engages a manifold and engages the internal bushing. The internal bushing is adjustable with respect to the external bushing thereby allowing the manifold to be adjustable with respect to the casing.

Abstract: An ejector comprising a motive inlet, a motive nozzle separably secured to the motive inlet, a suction chamber about the motive nozzle, a suction fluid inlet to the suction chamber, a mixing tube in fluid communication with the suction chamber and the motive nozzle, a diffuser in fluid communication with the mixing tube and distal the suction chamber and the motive nozzle, and an outlet from the diffuser is provided. A nozzle comprising at least two concentric arc nozzle portions is also provided. An ejector comprising a mixing tube including a flexible layer adapted to compress or stretch, thereby allowing a mixing tube diameter to change is further provided.

Abstract: A fuel delivery system for a combustion turbine engine, comprising: a fuel line having a fuel compressor and parallel branches downstream of the fuel compressor: a cold branch that includes an after-cooler; and a hot branch that bypasses the after-cooler; a rapid heating value meter configured to measure the heating value of the fuel from the fuel source and transmit heating value data relating to the measurements; means for controlling the amount of fuel being directed through the cold branch and the amount of fuel being directed through the hot branch; and a fuel-mixing junction at which the cold branch and the hot branch converge; wherein the fuel-mixing junction resides in close proximity to a combustor gas control valve.

Abstract: A system is provided and includes first and second water supplies at first and second relatively high and low temperatures, respectively, a heat exchanger, coupled to the water supplies, through which fuel and relative amounts of the water supplies at the first and second temperatures flow for fuel heating and a controller, operably interposed between the water supplies and the heat exchanger, to select and/or modulate the relative amounts of the water supplies permitted to flow through the heat exchanger to heat the fuel to a temperature based on a heating requirement to meet a modified wobbe index (MWI) rating.

Abstract: A impingement cooling system for heavy duty turbines that includes a manifold affixed to a casing of the heavy-duty turbine, wherein the manifold includes a plurality of impingement holes in the surface of the manifold and a blower that provides air flow across the plurality of impingement holes of the manifold to cool the casing of the heavy-duty turbine to control the clearance between a tip of a turbine blade and a shroud of the heavy-duty turbine.

Abstract: An ejector for a turbine engine is described herein. The ejector may include a variable geometry motive nozzle and a variable geometry mixing tube positioned downstream of the variable geometry motive nozzle.

Abstract: A mount includes a mounting bolt attached to a casing; an internal bushing that engages the casing at a distal end of the internal bushing; and an external bushing that engages a manifold and engages the internal bushing. The internal bushing is adjustable with respect to the external bushing thereby allowing the manifold to be adjustable with respect to the casing.

Abstract: An ejector comprising a motive inlet, a motive nozzle separably secured to the motive inlet, a suction chamber about the motive nozzle, a suction fluid inlet to the suction chamber, a mixing tube in fluid communication with the suction chamber and the motive nozzle, a diffuser in fluid communication with the mixing tube and distal the suction chamber and the motive nozzle, and an outlet from the diffuser is provided. A nozzle comprising at least two concentric arc nozzle portions is also provided. An ejector comprising a mixing tube including a flexible layer adapted to compress or stretch, thereby allowing a mixing tube diameter to change is further provided.

Abstract: An apparatus, a system and a method by which fuel gas to drive a heat source is heated are provided. The apparatus includes a first gas passage by which at least a portion of the fuel gas is transported from an inlet to an outlet, the outlet being fluidly coupled to the heat source, a plurality of heat pipes in thermal communication, at respective first ends thereof, with the portion of the fuel gas transported by the first gas passage, and a heating element, fluidly coupled to the heat source to receive exhaust of the heat source, through which respective second ends of the heat pipes extend to be in position to be heated by the exhaust.

Abstract: A turbine includes: a plurality of turbine blades arranged within a casing, the arrangement including a clearance between tips of the blades and the casing; a plurality of manifolds disposed proximate to the casing opposite the clearance, wherein each of the manifolds includes a plurality of impingement holes in the surface thereof; a source of clearance information; and a source of cooling air for supplying cooling air through a plurality of flow control devices to selected ones of the manifolds according to the clearance information. A system and a method are also provided.

Abstract: A impingement cooling system for heavy duty turbines that includes a manifold affixed to a casing of the heavy-duty turbine, wherein the manifold includes a plurality of impingement holes in the surface of the manifold and a blower that provides air flow across the plurality of impingement holes of the manifold to cool the casing of the heavy-duty turbine to control the clearance between a tip of a turbine blade and a shroud of the heavy-duty turbine.