Pratt-whitney Canada Corp

Ion Dinu

Mohammed Ennacer

Michael R Mark

Eduardo David Hawie

Sri Sreekanth

René Paquet

Douglas Maccaul

Eduardo Hawie

A hybrid powerplant is provided for an aircraft. This hybrid powerplant includes a housing, an electric machine, a machine fluid circuit, a heat engine and a geartrain. The housing includes a machine containment zone and an engine compartment outside of the machine containment zone. The electric machine is arranged within the machine containment zone. The machine fluid circuit services the electric machine. The machine fluid circuit extends in the machine containment zone and is arranged outside of the engine compartment. The heat engine is arranged within the engine compartment. The geartrain is operatively connected to the electric machine and the heat engine.

Containment zone for an electric machine in a hybrid powerplant for an aircraft

A hybrid powerplant is provided for an aircraft. This aircraft hybrid powerplant includes a housing, an electric machine, a heat engine and a geartrain. The housing includes a containment zone located within the housing. The electric machine is arranged within the containment zone. The heat engine is arranged partially or completely within the housing and outside of the containment zone. The geartrain is arranged partially or completely within the housing and partially or completely outside of the containment zone. The electric machine, the heat engine and the geartrain are operatively interconnected.

A turbine shroud segment has a body extending axially between a leading edge and a trailing edge and circumferentially between a first and a second lateral edge. Upstream and downstream plenums are defined in the body. The upstream plenum has a plurality of cooling inlets. The downstream plenum has a plurality of cooling outlets. A flow constricting slot extends across the body between the first and second lateral edges. The flow constricting slot fluidly connects the downstream plenum to the upstream plenum.

Turbine shroud cooling

The gas turbine engine can have a gas path extending in serial flow communication across a compressor, a combustion chamber, and a turbine, the turbine having at least one multistage turbine section having a front toward the combustion chamber and a rear opposite the front, a plenum radially outward of the gas path, and a plurality of aperture sets interspaced from one another between the front and the rear, the aperture sets providing fluid flow communication from the plenum to the gas path, and a cooling air path having an outlet fluidly connected to the plenum at the rear of the plenum.

Gas turbine engine and cooling air configuration for turbine section thereof

A gas turbine engine combustor is described which includes outer and inner annular combustor liners formed of sheet metal. The exit duct circumscribes an annular combustor exit and defines a combustion gas path. The exit duct includes a large exit duct having an annular forged metal section which is butt welded at an upstream end to the outer combustor liner to form a first annular joint. The annular forged metal section is fixed at a downstream end to an annular sheet metal wall to form a second annular joint. Methods of forming and of repairing a gas turbine engine combustor are also disclosed.

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Candiac, Canada

Ion Dinu