Pratt-Whitney Canada Corp

Marco P Convertini

Ernest Adique

Piotr Szczesnowicz

Harinath Bodugutla Venkata

Shervin Aslani Amoli

Gas turbine engines include fan, compressor, combustor, and turbine sections. An electric machine assembly includes a rotating component comprising a plurality of airfoils and a plurality of first electric machine elements, with each airfoil including a respective first magnetic material electric machine element. A housing is arranged radially outward from the airfoils and includes a circumferential slot. A second electric machine element is arranged within the circumferential slot in the form of a circumferential winding arranged radially outward from the rotating component. A control system is electrically connected to the second electric machine element. Rotation of the rotating component causes the first electric machine elements to generate a magnetic flux and induce a current within the second electric machine element and the control system is configured to distribute the induced current to at least one of a storage device or electrical components of the gas turbine engine.

Electromagnetic inducer for gas turbine rotating turbomachinery

A gas turbine engine includes a fan operable for delivering air into a bypass duct. The fan is also operable for delivering air into a core engine housing. The core engine housing encloses a compressor, a combustor and a turbine section. The core engine housing has an upstream end defining a separation point between the bypass duct and the core engine housing. An air separation device is adjacent the upstream end. The air separation device includes a baffle and an opposed louver. The baffle and louver together are structured for defining an airflow path to guide air adjacent the upstream end with a radially outward and axially downstream components. There are baffle ribs on the baffle facing opposed louver ribs on the louver, with at least some of the louver ribs being circumferentially offset from the baffle ribs.

Gas turbine engine bypass louver and baffle rib design

A stator assembly for an aircraft engine, has: vanes distributed about a central axis, a vane having: an airfoil extending from a first end to a second end along a span and from a leading edge to a trailing edge along a chord, the airfoil having a pressure side and a suction side opposed to the pressure side; a slot within the airfoil, the slot extending in a direction having a component along the chord, the slot located between the pressure side and the suction side; a port at the leading edge, the port fluidly communicating with the slot and with the gaspath; a mass located within the slot, the mass movable within the slot to shift a center of gravity of the vane in a chordwise direction; and a biasing member biasing the mass in a direction opposite a pressure force generated by the flow of fluid.

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Vaughan, Canada

Marco P Convertini