Abstract: An inlet bleed heat system in a gas turbine includes a compressor discharge extraction manifold that extracts compressor discharge air, an inlet bleed heat manifold receiving the compressor discharge air, and a plurality of acoustic dispersion nozzles disposed at an output end of the inlet bleed heat manifold that reduce a velocity of the compressor discharge air in the inlet bleed heat manifold. Noise is generated from the shearing action between the surrounding atmosphere and air jets from orifices. When the air jet velocity is slowed using, for example, a multi-stage ejector/mixer, noise can be abated.

Abstract: In a gas turbine power plant, pressurized fuel gas undergoes pressure reduction and gas expansion before being provided to a gas turbine. Condensations, which can damage the turbine, can form as the fuel gas cools when the fuel gas undergoes the pressure reduction and expansion. An electric startup heater is used to superheat the fuel gas to substantially prevent the condensations from forming. The electric startup heater includes band heaters wrapped externally to a fuel gas pipe to heat the fuel gas from outside in. Compared to conventional heaters which provide superheating through internal heating elements, the electric startup heater reduces costs and provides increased safety, flexibility, operational efficiency and ability to adapt to varying fuel gas characteristics.

Abstract: A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections.

Abstract: A method includes blending a first fuel with a second fuel in a ratio to produce a third mixed fuel. The first fuel has a first heating value, the second fuel has a second heating value, and the third mixed fuel has a third heating value. In addition, the first heating value is different than the second heating value. The method also includes feedforward controlling the third heating value of the third mixed fuel via prediction and correction of a fuel flow rate of the first and/or second fuels to adjust the ratio of the first and second fuels based at least in part on a comparison between a measurement and a target for the third heating value.

Abstract: A turbomachine system includes a compressor having a compressor intake and a compressor extraction outlet, and an inlet system fluidly connected to the compressor intake and the compressor extraction outlet. The inlet system includes a plenum having a first end portion that extends to a second end portion through an intermediate portion. The inlet system also includes a heating system having a plurality of conduits extending horizontally through the intermediate portion of the plenum and arranged in a vertical relationship. Heated air from the compressor extraction outlet passes through the plurality of conduits and raises a temperature of ambient air passing through the plenum and into the compressor intake.

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 method for recovering energy from bleed air from a compressor of a gas turbine is provided. The method includes directing bleed air from a compressor of a gas turbine into a cooling unit. The bleed air is compressed air from the compressor, and the bleed air is not directed into a combustion chamber of the gas turbine. The method also includes cooling the bleed air within the cooling unit. The method further includes expanding the cooled bleed air within a turbo-expander to generate power.

Abstract: An ejector system and method of operation for combining high and low pressure fluid flow streams is disclosed. A nozzle chamber communicates with a high pressure fluid flow stream and a suction chamber communicates with a low pressure fluid flow stream. The outlet of the nozzle chamber exit into the suction chamber and include multiple nozzles such that the high pressure flow stream exits the nozzle chamber in multiple flow streams having multiple surface areas for interlayer drag between the flows. The low pressure fluid flow stream is entrained by the high pressure fluid flow streams exiting the multiple nozzles to define an intermediate pressure flow stream.

Abstract: A thermal management system includes: a turbine assembly including an inlet housing, a compressor in fluid communication with the inlet housing, a power turbine in fluid communication with the compressor, and an exhaust assembly in fluid communication with the power turbine; and at least one heat pipe having a first portion disposed in thermal communication with the inlet housing and a second portion disposed in thermal communication with the exhaust assembly, the at least one heat pipe configured to transfer thermal energy from the exhaust assembly to at least one of input gas entering the inlet housing and at least one component of the inlet housing.

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 turbomachine includes a compressor having an intake portion and an outlet portion. The compressor compresses air received at the intake portion to form a compressed airflow that is passed from the outlet portion. The turbomachine also includes an intercooler operatively connected downstream from the compressor. The intercooler includes a plurality of heat pipes that are configured to extract heat from the compressed airflow.

Abstract: A combined cycle power plant includes a steam turbine section having an inlet section and an outlet section. The steam turbine section passes steam from the inlet section toward the outlet section. The combined cycle power plant also includes a condenser fluidly connected to the outlet section of the steam turbine section. The condenser includes a plurality of heat pipes configured to extract latent heat from steam passing from the steam turbine section to form condensed water.

Abstract: Disclosed is a turbomachine including at least one exhaust pathway along which exhaust is directed and released to ambient and at least one exhaust processor capable of removing regulated substances from the exhaust. One or more ambient air inlets are located at the at least one exhaust pathway upstream of the at least one exhaust processor. The at least one exhaust pathway is configured such that ambient air is capable of being urged into the at least one exhaust pathway through the one or more ambient air inlets by an acceleration of the exhaust along the at least one exhaust pathway. The ambient air urged into the at least one exhaust pathway reduces a temperature of the exhaust to increase effectiveness of the at least one exhaust processor. Further disclosed is a method for releasing turbomachine exhaust to ambient.

Abstract: A fuel moisturization sensor system is disclosed. The fuel moisturization sensor system includes a first light source configured for emitting light through a fuel and moisture flow path at a first wavelength, wherein the first wavelength is at least partially absorbable by the moisture when in a vapor phase and substantially not absorbable by the fuel, and a second light source configured for emitting light through the fuel and moisture flow path at a second wavelength, wherein the second wavelength is preferentially scattered by moisture when in a liquid phase and substantially not absorbed by the fuel or by the moisture when in a vapor phase, a detector system configured to detect light transmitted through the flow path at the first and second wavelengths and to generate a first data signal corresponding to the transmission at the first wavelength and a second data signal corresponding to the transmission at the second wavelength.

Abstract: An apparatus for supplying water to a misting system for an inlet of a gas turbine, includes a diversion of heated feedwater from a loop and to a pump, the pump providing high-pressure feedwater to the misting system. A combined cycle power plant and a method for supplying water are provided.

Abstract: A system is provided for directing air from plural compressor ports to provide cooling and/or sealing air to an associated turbine site. A first flow from a pressure stage of the compressor has a first pressure and temperature. A second flow from another pressure stage of the compressor has a second pressure and temperature. The first and second pressures/temperatures are different. An ejector has two inlets for receiving the first and second flows, and output for combining the first and second flows into a third flow. The pressure and temperature of the third flow are different from the first and second pressures and temperatures. A bypass line is connected between the first flow and the third flow, and provides a bypass flow. A mixer combines the bypass flow and the third flow into a fourth flow. The fourth flow has a pressure and temperature intermediate the pressure and temperature of the bypass flow and the third flow. The mixer comprises inner and outer sections.