A spinner for a gas turbine engine may include a substantially-flat inner surface having frustoconical geometry. A flange having semi-toroidal geometry may extend from the spinner with an inner curved surface of the flange being tangential to the inner surface. A mating portion may extend substantially tangentially from the inner curved surface of the flange and configured for fastening to a fan hub.

A spinner for a gas turbine engine may include a substantially-flat inner surface having frustoconical geometry. A flange having semi-toroidal geometry may extend from the spinner with an inner curved surface of the flange being tangential to the inner surface. A mating portion may extend substantially tangentially from the inner curved surface of the flange and configured for fastening to a fan hub.

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by reducing or eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more bayonet flanges, two or more apertures defined by a flange forming an annular hub mating surface of the nose cone and configured to receive an fastener therethrough, and one or more pilot flanges.

Systems and methods of coupling a nose cone to a turbine machine. Nose cone assembly weight and coupling difficulty are each reduced by reducing or eliminating the number of bolts used to mount the nose cone to the turbine machine, as well as the support or retaining ring. The disclosed nose cone comprises a plurality of hub mounting elements including one or more bayonet flanges, two or more apertures defined by a flange forming an annular hub mating surface of the nose cone and configured to receive an fastener therethrough, and one or more pilot flanges.

A lock for securing a nosecone having first threading to an inlet case having second threading and for use with a gas turbine engine having an axis includes an annular ring designed to be positioned about the first threading. The lock also includes a tab extending radially from the annular ring, and having a ramped circumferential end and an angled circumferential end such that the ramped circumferential end passes over a detent of the inlet case in response to the nosecone being fastened to the inlet case and the angled circumferential end engages with the detent to resist unfastening of the nosecone from the inlet case.

A lock for securing a nosecone having first threading to an inlet case having second threading and for use with a gas turbine engine having an axis includes an annular ring designed to be positioned about the first threading. The lock also includes a tab extending radially from the annular ring, and having a ramped circumferential end and an angled circumferential end such that the ramped circumferential end passes over a detent of the inlet case in response to the nosecone being fastened to the inlet case and the angled circumferential end engages with the detent to resist unfastening of the nosecone from the inlet case.

A fairing ring for a bladed wheel is disclosed. The fairing ring includes an annular wall extending axially, the wall presenting a plurality of notches extending axially, each notch being configured to receive a leading edge or a trailing edge of a blade.

A fairing ring for a bladed wheel is disclosed. The fairing ring includes an annular wall extending axially, the wall presenting a plurality of notches extending axially, each notch being configured to receive a leading edge or a trailing edge of a blade.

An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.