A gas mixing device for a moving object including a discharge flow path that discharges an exhaust gas from a gas turbine engine. The discharge flow path includes a tubular portion, a communication passage that allows an inside of the tubular portion and the gas turbine engine to communicate with each other, and a plurality of guide portions that extend radially inward from the tubular portion and guide the cooling gas to a radially central portion of the tubular portion. The plurality of guide portions are spaced from each other in a circumferential direction of the tubular portion, and the extended end portions of the plurality of guide portions are spaced from each other.

An air supply and conditioning system for an inlet system of a gas turbine includes an air processing unit having an inlet configured to receive compressed air from a compressor of the gas turbine. The air processing unit includes a heat exchanger that is downstream from the inlet. A vortex cooler is disposed downstream from the inlet of the air processing unit. The vortex cooler is in fluid communication with the heat exchanger and with an outlet of the air processing unit. The system further includes a self-cleaning filter that is disposed within a duct of the inlet system. The self-cleaning filter is in fluid communication with at least one of the outlet of the air processing unit or an outlet of the vortex cooler.

An extraction impeller for an axial compressor includes first vanes having an elongated S-shape arranged on the surface of an impeller body. The first vanes extend radially from an outer flow inlet edge of the body to a flow outlet hub centered on the surface at the rotation axis. A radially inner end of each of the first vanes connects at the flow outlet hub in a direction perpendicular to a rotation axis. Second vane(s) are arranged between adjacent first vanes, and third vanes are arranged between second vanes and between first vanes and second vanes. Second vanes are radially longer than third vanes. The impeller extracts air from the axial compressor and forms an axial flow with reduced vortex whistle. When used in an axial compressor of a gas turbine system, the impeller reduces flow unsteadiness.

A cooling system for a gas turbine is disclosed comprising a vortex tube defining a body having an inlet port connectable to a compressor to receive compressed fluid. The vortex tube is configured to separate flow of the compressed fluid into a cold stream and a hot stream. The cooling system further includes a fluidic oscillator in fluid communication with the vortex tube, the first end of which is connected to a cold stream outlet port of the vortex tube to receive the cold stream. The fluidic oscillator is configured to generate at least two oscillator jets of the cold stream, operating at different oscillation frequencies, to produce biaxial pulsating flow oscillations onto a surface of at least one gas turbine blade of the gas turbine. A more efficient cooling system will result from the proposed cooling system's increased cooling impinging surface area and significantly reduced cooling fluid temperature differential.

A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.

A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature.