Abstract: An engine system for starting a gas turbine engine includes a starter coupled to the gas turbine engine and configured to provide torque to the gas turbine engine; and a controller coupled to the starter and configured to evaluate an engine system parameter and to select from a plurality of start modes for starting the gas turbine engine based on the engine system parameter.

Abstract: An engine system for starting a gas turbine engine includes a starter coupled to the gas turbine engine and configured to provide torque to the gas turbine engine; and a controller coupled to the starter and configured to evaluate an engine system parameter and to select from a plurality of start modes for starting the gas turbine engine based on the engine system parameter.

Abstract: Engines and methods for operating the engines are provided. The engine includes a means for limiting overspeed in flow communication with a turbine section flowpath, wherein the means for limiting overspeed is adapted to block a first portion of an airflow received along a first direction vector from flowing into an exhaust section flowpath and to redirect a second portion of the airflow received along the first direction vector or a portion of the blocked first portion of the airflow to flow along another direction vector that is closer to parallel with a longitudinal axis than the first direction vector.

Abstract: A radial inflow particle separator includes a pair of axially and radially spaced curvilinear walls cooperatively defining a circumferential flow path leading radially inwardly and axially to an engine. Preferably, the particle separator is employed with a turbine engine which is operated at times in an environment laden with dust and particulate matter. Such an environment is typically encountered by a turbine engine of a helicopter, or off-road vehicle. The particle separator provides dust and particulate control features including aero-inertial, particle trajectory, particle boundary-rebound, and scavenge flow tailoring to achieve a dust and particulate separation efficiency as good as or better than the best conventional axial-flow particle separators. This particle separation effectiveness is achieved in a radial inflow particle separator which is smaller and lighter in weight than axial flow devices, and which packages advantageously with the essential structures of a turbine engine.

Abstract: A pusher turboprop engine is provided with an interior exhaust duct structure which directs the hot turbine gases through and out of the engine nacelle and around the rear spinner which surrounds the propeller hub. The spinner supports blade-shaped shields which protect the roots of the propeller blades from the hot exhaust gasses.