An aircraft is disclosed, the aircraft having a fuselage having a centerline, and a wing extending from the fuselage and having a leading edge and a trailing edge. Additionally, the aircraft includes an engine mounted to the wing and having a rotating output shaft, and a propeller operably coupled to the output shaft and generating a rotating flow field to define a propeller wake when the propeller is rotated by the rotating output shaft. The propeller is located forward of the leading edge of the wing, so the propeller wake flows over the wing forming localized areas of effectively increased angle of attack generating a corresponding increased wing loading, with the wing having corresponding localized areas of reduced chord length to neutralize the otherwise increased wing loading. A method of countering the aerodynamic effects of propeller wake acting on a wing is also disclosed.

A hybrid electric turboprop includes a propeller, a thermal engine, an electric motor, a gearbox, and an air inlet. The propeller is configured to rotate about a propeller axis and includes a plurality of blades extending radially outwardly from the propeller axis such that, as the propeller is rotated about the propeller axis, the plurality of blades define a substantially circular blade path area centered about the propeller axis and having a radius. The gearbox couples both the thermal engine and the electric motor to the propeller to enable each of the thermal engine and the electric motor to drive rotation of the propeller about the propeller axis. The air inlet defines an opening. A radial distance is defined from the propeller axis to a location within the opening. The radial distance is equal to or less than 60% of the radius.

An engine collar, aircraft, and method of installing an engine in an aircraft are provided. The engine collar includes a first engine collar piece, including a first portion of a ring, a second engine collar piece, including a second portion of a ring, and a plurality of splice plates joining the first engine collar piece to the second engine collar piece; where each of the first engine collar piece and the second engine collar piece have two engine isolation mounting points and a plurality of attachment points for connecting the engine collar to a plurality of engine supports.

A propulsion system for an aircraft includes an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor about an axis. The turbine engine includes a core flowpath, a bypass flowpath, a fan section and an engine core. The engine core includes a compressor section, a combustor section and a turbine section. The core flowpath extends through the compressor section, the combustor section and the turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The inlet is next to and downstream of the fan section. The bypass flowpath extends outside of and along the engine core from an inlet into the bypass flowpath to an exhaust from the bypass flowpath. The inlet is next to and downstream of the fan section. The engine core is arranged axially between the fan section and the open propulsor rotor.

An apparatus includes an engine and an accessory gearbox. The engine is positioned on a top side of an aircraft. The accessory gearbox is mounted with an airframe of the aircraft remote from the engine, wherein the accessory gearbox is drivingly connected to the engine.

An engine collar, aircraft, and method of installing an engine in an aircraft are provided. The engine collar includes a first engine collar piece, including a first portion of a ring, a second engine collar piece, including a second portion of a ring, and a plurality of splice plates joining the first engine collar piece to the second engine collar piece; where each of the first engine collar piece and the second engine collar piece have two engine isolation mounting points and a plurality of attachment points for connecting the engine collar to a plurality of engine supports.

An apparatus includes an engine and an accessory gearbox. The engine is positioned on a top side of an aircraft. The accessory gearbox is mounted with an airframe of the aircraft remote from the engine, wherein the accessory gearbox is drivingly connected to the engine.

An aircraft propulsion system includes a propulsion section and a turbine engine. The propulsion section includes an open propulsor rotor and an open guide vane structure. The turbine engine is configured to drive rotation of the open propulsor rotor. The turbine engine includes an engine core, an inlet section, an exhaust section and a flowpath. The engine core includes a compressor section, a combustor section and a turbine section with the turbine section disposed axially between the compressor section and the open propulsor rotor. The inlet section includes a flowpath inlet. The exhaust section includes a flowpath exhaust. At least a portion of the exhaust section is disposed axially between the open propulsor rotor and the open guide vane structure. The flowpath extends from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust.

A gas turbine includes two unducted propellers, a main channel, a compression stage located in the main channel, the main channel supplying the compression stage with air, a cooling channel extending from a cooling inlet opening into the main channel, the cooling inlet being located upstream of the compression stage with reference to a direction of flow of the air through the gas turbine, a heat exchanger located in the cooling channel, an ejection channel opening into the main channel and into the cooling channel so that air passing through the ejection channel ventilates the heat exchanger, and a variable bleed valve that adjust an air flow rate in the ejection channel.

A powerplant assembly includes an engine, a turbocompressor, and an overspeed protection valve. The engine includes an air intake and an engine exhaust. The turbocompressor includes a compressor section, a turbine section, and a rotational assembly. The rotational assembly includes a turbocompressor shaft, a bladed compressor rotor of the compressor section, and a turbine rotor of the turbine section. The engine and the turbocompressor form a gas flow path. The gas flow path extends from the compressor section to the air intake, through the engine, and from the engine exhaust to the turbine section. The overspeed protection valve forms a portion of the gas flow path. The overspeed protection valve is positionable in an open state and a closed state.