General Electric Company

John Paul Petrowicz

Walter Jackson Tingle

Timothy Joseph Higgins

A method for assembling a turbine engine including a compressor is disclosed. The method includes coupling an inlet including an inertial particle separator (IPS) and a first surface that is defined using a segment angle, to a gas turbine engine, and coupling the first surface substantially flush against a fuselage of an aircraft to reduce drag.

Segmented inertial particle separators and methods of assembling turbine engines

An engine starting system is provided for an aircraft gas turbine engine having a fan, compressor, combustor, high pressure turbine joined to the compressor by a core shaft, and a low pressure turbine joined to the fan by a fan shaft. A fluid assist pump is operatively joined to the fan shaft, and a fluid assist motor is operatively joined to the core shaft and the assist pump. The assist pump and motor are selectively engaged so that windmilling of the fan during aircraft flight powers the assist pump to in-turn power the assist motor to accelerate the core shaft to a minimum speed for allowing restarting of the engine in flight.

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Rowley, MA, United States of America

John Paul Petrowicz