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An in-flight starting mechanism for a gas turbine engine in a propeller type aircraft propulsion system wherein the propeller is driven by a free power turbine rotor rotatable independently of the gasifier rotor of the engine. The starting mechanism includes an inner race, an outer race and a plural

An in-flight starting mechanism for a gas turbine engine in a propeller type aircraft propulsion system wherein the propeller is driven by a free power turbine rotor rotatable independently of the gasifier rotor of the engine. The starting mechanism includes an inner race, an outer race and a plurality of rollers in pockets in the outer race. The rollers are centrifugally biased out of engagement with an inner race surface of the inner race when both the free power and gasifier rotors are driven normally in the forward or propelling direction. The pockets are evenly spaced around the inner race so that at least some of the rollers are moved by gravity against the inner race surface when the rotors are substantially stopped as occurs when the engine is shutdown in flight and the propeller feathered. Thereafter, as the propeller is unfeathered and the energy extracted from the passing airstream drives the free power turbine rotor in the forward direction, the inner race surface energizes the rollers to wedge between the inner and outer races to effect a positive connection between the rotors whereby the gasifier rotor is backdriven by the propeller to initiate engine restart.

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In an aircraft propulsion gas turbine engine including a source of hot gas motive fluid, a first rotor rotatable by said hot gas motive fluid in a propelling direction about a main axis of said engine and having a compressor portion, a second rotor rotatable by said hot gas motive fluid about said m

In an aircraft propulsion gas turbine engine including a source of hot gas motive fluid, a first rotor rotatable by said hot gas motive fluid in a propelling direction about a main axis of said engine and having a compressor portion, a second rotor rotatable by said hot gas motive fluid about said main axis in said propelling direction independently of said first rotor and drivingly connected to a variable pitch aircraft propeller, said second rotor having a feathered condition corresponding to a feathered condition of said propeller wherein a moving airstream imparts substantially no energy to said propeller and a plurality of progressively more unfeathered conditions corresponding to progressively more unfeathered positions of said propeller characterized by progressively increasing energy transfer between said moving air stream and said propeller so that said moving air stream rotates said second rotor in said propelling direction as said propeller moves from said feathered position through said plurality of unfeathered positions, an in-flight starting mechanism comprising: a ring-like inner race rotatable as a unit with one of said first and said second rotors and having a cylindrical inner race surface, a ring-like outer race around said inner race rotatable as a unit with the other of said first and said second rotors and having an inside surface facing said inner race surface, means on said outer race defining a plurality of pockets in said inside surface opening toward and circumferentially spaced around said inner race surface, a plurality of rolling elements disposed in respective ones of said pockets each moveable between a first position in said pocket remote from said inner race surface and corresponding to an off condition of said starting mechanism and a second position wedged between said outer race and said inner race surface and corresponding to an on condition of said starting mechanism, each of said rolling elements being centrifugally biased to said first position when each of said first and said second rotors is rotated in said propelling direction by said hot gas motive fluid at speeds corresponding generally to an idle speed of said engine, and means on said outer race and on said inner race operative to move said rolling elements from said first positions to said second positions in response to rotation of said second rotor in said propelling direction after each of said first and said second rotors is substantially stopped whereby said second rotor is drivingly connected to said first rotor through said rolling elements so that said second rotor in said unfeathered conditions is operative to backdrive said first rotor.