Abstract: A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.

Abstract: The present disclosure relates generally a gas turbine engine and a rotor therefor. The rotor may include a symmetric rim thereon to prevent the propagation of induced vibratory responses. The rim may have one or more sloping surfaces to prevent the re-attachment of boundary layer flow.

Abstract: An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis.

Abstract: A gas turbine engine has a nose cone with a nose cone upstream end and an inlet housing including a plurality of separate flow paths at a housing upstream end which is downstream of the nose cone upstream end. The inlet housing includes a mixing portion downstream of the housing upstream end which mixes airflow from the separate flow paths, such that the airflow is generally around 360 degrees of a rotational axis of the gas turbine engine. A rotor and a turbine drive a shaft to drive the rotor with the shaft including a bearing mounted at a location downstream of the nose cone upstream end.

Abstract: The present disclosure relates generally a gas turbine engine and a rotor therefor. The rotor may include a symmetric rim thereon to prevent the propagation of induced vibratory responses. The rim may have one or more sloping surfaces to prevent the re-attachment of boundary layer flow.

Abstract: An airfoil includes a blade having a pocket recess therein and one or more features disposed within the pocket recess. The one or more features are configured to disrupt pressure oscillations within the pocket recess. In another embodiment, a blade is disclosed having a first wall and a second wall. The first wall is disposed on a suction side of the blade and the second wall is disposed on a pressure side of the blade. The second wall is connected to the first wall at a leading edge of the blade. Together the first wall and the second wall form a portion of a pocket recess and the pocket recess is disposed asymmetrically with respect to a camber line of the blade.

Abstract: An example auxiliary power unit (APU) exhaust silencer includes cooling features to protect the outer skin and other components from heat generated by gases passing through an exhaust duct. Cooling air flow through a cooling air passage in thermal contact with the exhaust silencer carries heat away from other nearby components and the aircraft skin.

Abstract: An exhaust silencer assembly for use with an auxiliary power unit includes an eductor and a discharge pipe. The eductor is disposed downstream of the auxiliary power unit and has an entrance opening at a forward axial end thereof. The entrance opening is configured to receive exhaust airflow from the auxiliary power unit. The discharge pipe extends from the auxiliary power unit and communicates with the exhaust silencer assembly downstream of the entrance opening of the eductor.

Abstract: An airfoil includes a blade having a pocket recess therein and one or more features disposed within the pocket recess. The one or more features are configured to disrupt pressure oscillations within the pocket recess. In another embodiment, a blade is disclosed having a first wall and a second wall. The first wall is disposed on a suction side of the blade and the second wall is disposed on a pressure side of the blade. The second wall is connected to the first wall at a leading edge of the blade. Together the first wall and the second wall form a portion of a pocket recess and the pocket recess is disposed asymmetrically with respect to a camber line of the blade.

Abstract: An airfoil includes a blade having a leading edge, a trailing edge, a pressure side, a suction side, a tip, and a scoop. The scoop extends along the tip of the blade. The scoop comprises a difference in a radial height of the blade from a pressure side to a suction side of the blade. The radial height of the blade at the pressure side is less than the radial height of the blade at the suction side.

Abstract: An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis.

Abstract: An exhaust silencer assembly for use with an auxiliary power unit includes an eductor and a discharge pipe. The eductor is disposed downstream of the auxiliary power unit and has an entrance opening at a forward axial end thereof. The entrance opening is configured to receive exhaust airflow from the auxiliary power unit. The discharge pipe extends from the auxiliary power unit and communicates with the exhaust silencer assembly downstream of the entrance opening of the eductor.

Abstract: A turbine apparatus comprises a rotor with a hub section defined about a rotational axis and a plurality of blades attached to the hub section. The plurality of blades comprises a first group having a first angular spacing in a first circumferential sector of the rotor, and a second group having a second angular spacing in a second circumferential sector of the rotor. The first angular spacing is different from the second angular spacing, and the rotor blades are asymmetric about the rotational axis.

Abstract: A gas turbine engine comprises: a combustor with an aft end exhaust nozzle that discharges along an axis of the combustor; an eductor with a housing that circumscribes the combustor that has a sideward eductor inlet that intakes generally normal to the combustor axis and an aft end eductor outlet that circumscribes the combustor exhaust nozzle and exhausts along the combustor axis; and an eductor distribution shield mounted within the eductor housing between the eductor inlet and the combustor with a deflection surface that deflects the intake of the eductor inlet around the combustor.

Abstract: An example auxiliary power unit (APU) exhaust silencer includes cooling features to protect the outer skin and other components from heat generated by gases passing through an exhaust duct. Cooling air flow through a cooling air passage in thermal contact with the exhaust silencer carries heat away from other nearby components and the aircraft skin.

Abstract: A gas turbine engine comprises: a combustor with an aft end exhaust nozzle that discharges along an axis of the combustor; an eductor with a housing that circumscribes the combustor that has a sideward eductor inlet that intakes generally normal to the combustor axis and an aft end eductor outlet that circumscribes the combustor exhaust nozzle and exhausts along the combustor axis; and an eductor distribution shield mounted within the eductor housing between the eductor inlet and the combustor with a deflection surface that deflects the intake of the eductor inlet around the combustor.