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.

Embodiments are provided for a cooling fan that has a vortex tube, an air turbine, and one or more fan blades. The vortex tube is capable of being supplied with compressed air and splitting the compressed air into a cold stream and a hot stream. The cold stream can spins said air turbine with attached fan blades, causing said fan blades to spin and blow cold air.

An apparatus and method for assembling an inducer assembly for inducing a rotation on an airflow passing within a turbine engine. The inducer assembly can provide a volume of fluid from a compressor section to a turbine section of the engine. The inducer assembly can include the combination of separate segments to form an annular inducer.

A gas turbine engine includes a first zone and a second zone downstream from the first zone. A buffer system can communicate a buffer cooling air to at least the first zone. A bleed source can communicate a bleed air to the second zone.

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.

A swirler tube is disclosed. A swirler is provided comprising a flange defining a first surface, a tube extending away from the first surface, a flow surface defined by a flange inner surface and a tube inner surface, the flange inner surface having an inlet diameter, and a metering feature disposed on the flow surface, wherein the metering feature is integral to the tube, the metering feature have a metering feature diameter that is less than the inlet diameter.

The present disclosure generally relates to separating solid particles from an airflow in a gas turbine engine. A separator includes a plurality of vortex chambers arranged about a longitudinal axis of the gas turbine engine, each vortex chamber having a clean air outlet at a first end, a dirty outlet at a second end, and an air inlet transverse to the vortex chamber located at the first end. The separator also includes a sealable collection chamber in fluid communication with the dirty outlet of the each of the plurality of vortex chambers.

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 gas turbine engine component includes a body defining a cooling airflow passage thereat configured for directing a cooling airflow therethrough. A plurality of turbulators are positioned at at least one passage wall of the cooling airflow channel. Each turbulator of the plurality of turbulators includes a plurality of facets extending outwardly from a central portion. A gas turbine engine includes a combustor and a plurality of gas turbine engine components positioned in fluid communication with the combustor. Each component includes a body defining a cooling airflow passage thereat configured for directing a cooling airflow therethrough. A plurality of turbulators are located at at least one passage wall of the cooling airflow channel, each turbulator of the plurality of turbulators including a plurality of facets extending outwardly from a central portion.

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.