A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A compressor section includes, among other things, a tie shaft assembly including a shaft and one or more projections extending radially outward from the shaft. The projections are configured to redirect air communicated from between the one or more rotor stages and the shaft.

A control system for a gas turbine includes a controller. The controller includes a processor configured to access an operational parameter associated with the gas turbine. The processor is configured to calculate a bias based on the operational parameter, wherein the bias indicates an amount of change in a temperature of an oxidant entering a compressor of the turbine to reach a reference temperature. The processor is further configured to control the temperature of the oxidant based on the bias to improve power output of the gas turbine.

By using a combustion flue gas (18) from a power turbine (16), a high-pressure secondary compressed air (12C) is subjected to heat exchange in a first heat exchange unit (19A) of an exhaust heat recovery device (19), and by using resultant heat-exchanged flue gas (18A), a low-pressure primary compressed air (12A) is subjected to heat recovery in a second heat exchange unit (19B) of a saturator (31). Then, a primary compressed air (12B) that has been subjected to heat recovery in the second heat exchange unit (19B) is introduced into a secondary air compressor (22) to increase the pressure of the air, and then the high-pressure air is subjected to heat recovery in the first heat exchange unit (19A), producing a secondary compressed air (12D). The secondary compressed air (12D) is introduced into a combustor (14) and combusted using fuel.

A system includes a gas turbine system having a heat recovery steam generator (HRSG), a compressor, an intercooler, and a steam turbine. The HRSG is configured to receive an exhaust gas, heat a first working fluid with the exhaust gas, and route the first working fluid to the steam turbine, where the steam turbine is configured to extract energy from the first working fluid, and where the intercooler is configured to receive a compressed air from the compressor of the gas turbine engine and to cool the compressed air to a first controllable temperature determined by engine controls with a second working fluid having a second controllable temperature suitable for cooling the compressed air to the first controllable temperature determined by the engine controls. The system also includes a first feed heater of a distillation system, where the first feed heater is configured to receive the mixture and the second working fluid such that the second working fluid sinks heat to the mixture. The system also includes a first-effect vessel of the distillation system. The first-effect vessel is configured to receive the mixture from the first feed heater and to receive the first working fluid from the steam turbine, such that the first working fluid sinks heat to the mixture.

Systems and methods for reducing the pressure of a first pressurized fluid, thereby reducing the temperature of the pressurized fluid, and utilization of the reduced-pressure and temperature fluid to cool a second fluid. Such an approach can enable a reduction in the size and weight of a hydraulic system, utilize waste energy in a system, and/or minimize electrical power requirements of a system, among other benefits.

A multi-stage intercooled compressor for a gas turbine engine, including multiple stages of rotating blades and cooling stator vanes, a cooling stator vane including an outer wall that defines an internal coolant fluid passage and has a length along a centerline from a leading edge to a trailing edge of the outer wall, and an internal flow divider wall disposed within the internal passage and extending along the centerline to divide the internal coolant fluid passage into an inflow pathway and an outflow pathway.

A gas turbine engine includes a main compressor section having a high pressure compressor with a downstream discharge, and upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the main compressor section. The tap passes the tapped air through a heat exchanger and then to a cooling compressor compressing air downstream of the heat exchanger. The cooling compressor delivers compressed air into the turbine section. An accessory gear box drives the cooling compressor. An intercooling system for a gas turbine engine is also disclosed.

A system includes a gas turbine system having a turbine combustor, a turbine driven by combustion products from the turbine combustor, and an exhaust gas compressor driven by the turbine. The exhaust gas compressor is configured to compress and supply an exhaust gas to the turbine combustor. The gas turbine system also has an exhaust gas recirculation (EGR) system. The EGR system is configured to recirculate the exhaust gas along an exhaust recirculation path from the turbine to the exhaust gas compressor. The system further includes a main oxidant compression system having one or more oxidant compressors. The one or more oxidant compressors are separate from the exhaust gas compressor, and the one or more oxidant compressors are configured to supply all compressed oxidant utilized by the turbine combustor in generating the combustion products.

A propulsion system for an aircraft includes a hydrogen fuel system supplying hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from an exhaust gas flow and includes a plurality of spiral passages disposed within a collector. The spiraling passages generate a transverse pressure gradient to direct water out of the exhaust gas flow toward the collector.