A fan includes a hub and a plurality of fan blades. The hub has an axle center. The fan blades are disposed around the hub. Each of the fan blades has a bent portion, and the bent portions of the fan blades are extended along a surrounding direction surrounding the axle center. The hub is welded with the bent portion of each of the fan blades along the surrounding direction. As a result, the number of fan blades is maximized, the strength is simultaneously ensured to be enough, and the advantages of effectively enhancing the fan characteristics are achieved.

A fan guard assembly having an improved structure for providing improved performance and an outdoor unit having the same are provided. The fan guard assembly includes: a front panel having an outlet; and a fan guard including a hub provided at the outlet to directly fix a fan motor assembly and a rib connecting between the hub and the front panel. Further, the outdoor unit includes: a cabinet; a bell mouth provided in the cabinet; a fan guard provided at an outlet of the bell mouth; and a fan motor assembly fixed to the fan guard.

A blisk fan is provided for a turbine engine propulsion system. The blisk fan includes a hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades extending radially outward from the hub to define a fan leading edge tip diameter. Each of the blades has a first vibratory mode at a natural frequency, which is greater than a first fan order and less than a second fan order at the maximum rotational speed. The compression system preferably has a balance factor of the compression system between 1.9 and 3.2.

An air conditioning system for an aircraft is provided. The air conditioning system includes a first rotating component and a second rotating component. The first rotating component includes a compressor and a turbine. The compressor pressurizes a first medium. The first turbine receives a mixture of a second medium and a pressurized form of the first medium. The second rotating component includes a fan.

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

An air cycle machine is provided. The air cycle machine can be included an environmental control system of an aircraft. The air cycle machine can include a turbine comprising a plurality of inlet gas flow paths, a compressor driven by the turbine from a shaft, and a fan driven by the turbine from the shaft.

A fan motor includes a motor including a stationary portion and a rotating portion arranged to rotate about a rotation axis extending in a vertical direction; an impeller including a plurality of blades, and arranged to rotate together with the rotating portion; a housing arranged to house the motor and the impeller therein; and a plurality of lead wires each of which is connected to the motor and is arranged to extend radially outward. The housing includes a tubular portion being tubular, and arranged to extend from an inlet side to an outlet side along the rotation axis, and house at least a portion of the impeller therein; a flange portion arranged to project radially outward from at least a portion of the tubular portion; a lead wire outlet defined in at least a portion of the tubular portion, and arranged to pass through the tubular portion in a radial direction; and a vertical groove arranged to be in communication with the lead wire outlet, and arranged to pass through the flange portion in an axial direction. The flange portion includes a first restricting portion arranged to extend toward the tubular portion. At least one of the lead wires is drawn radially outward through the lead wire outlet, and is held in the vertical groove radially inside of the first restricting portion.

A stage of a fan for a gas turbine engine may include a rotor blade and a stator vane disposed aft of the rotor blade. A baffle may be coupled to the stator vane. The baffle may define a secondary airflow path from aft of the stator vane to forward of the rotor blade. The baffle may further define the secondary airflow path from aft of the stator vane to forward of the stator vane.

An abrasive tip comprises an additive, the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

An abrasive tip comprises an additive layer having an additive; the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.