Pratt-Whitney Canada Corp

Mateusz Ożóg

Richard Ivakitch

Omer Abdul Wahab

Amir Masoud Tahvilian

An assembly is provided for an aircraft motor. This assembly includes a bearing, a stationary structure and a flexible support. The bearing extends circumferentially around an axis. The stationary structure circumscribes the bearing. The flexible support is arranged radially between and radially engages the bearing and the stationary structure. The flexible support includes a first ring, a second ring, a plurality of bridges and a plurality of first ribs. The bridges are arranged circumferentially about the axis. Each of the bridges extends radially between and is connected to the first ring and the second ring. The first ribs are arranged circumferentially about the axis and interspersed with the bridges. Each of the first ribs projects radially out from the first ring towards the second ring. Each of the first ribs is connected to the first ring and is disengaged from the second ring.

Flexible support for aircraft motor bearing

An assembly is provided for an aircraft motor. The assembly includes a bearing, a stationary structure and a flexible support. The bearing extends circumferentially around an axis. The stationary structure circumscribes the bearing. The flexible support is arranged radially between the bearing and the stationary structure. The flexible support includes an inner ring, an outer ring, a bridge, an open first channel and an open second channel. The inner ring radially engages the bearing. The outer ring radially engages the stationary structure. The bridge projects radially out from the inner ring to the outer ring. The bridge extends circumferentially about the inner ring. The open first channel extends axially into the flexible support from a first side of the flexible support to the bridge. The open second channel extends axially into the flexible support from a second side of the flexible support to the bridge.

A method of operation is provided during which fuel is delivered to a powerplant using a fuel system. The powerplant and the fuel system are arranged onboard an aircraft. The fuel system includes a first fuel reservoir and a second fuel reservoir. The first fuel reservoir contains a quantity of the fuel. At least some of the quantity of the fuel contained in the first fuel reservoir is transferred into the second fuel reservoir when a fault is identified associated with the first fuel reservoir.

Transferring fuel between fuel reservoirs of an aircraft fuel system

An aircraft engine, comprising: a first wall and a second wall defining a gaspath between the first wall and the second wall, the gaspath extending around a central axis, each of the first wall and the second wall having a gaspath side facing the gaspath and an opposed side facing away from the gaspath; struts circumferentially distributed around the central axis, the struts extending across the gaspath, a strut of the struts having an airfoil including a leading edge, a trailing edge, a first end secured to the first wall, and a second end secured to the second wall; and protrusions extending from a baseline surface of the opposed side of the first wall, the protrusions increasing a thickness of the first wall, a protrusion of the protrusions overlapping a location where the leading edge or the trailing edge meets the gaspath side of the first wall.

Aircraft engine struts with stiffening protrusions

An aircraft engine includes an air inlet duct and at least one strut having a leading edge and a trailing edge. The at least one strut extends across at least part of the air inlet duct and has a strut passage. The trailing edge has one or more edge contours, each defining a contour edge wall recessed from a baseline surface of the trailing edge. The one or more edge contours have a recessed tap in fluid communication with the strut passage.

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Hucisko, Poland

Mateusz Ożóg