Disclosed here are systems for detachable airframe components including detachable nose cones, propeller assemblies and motors. In some example embodiments, the assemblies include a nose cone with a connection receiver, a motor assembly with a rotatable section, where the rotatable section includes torque arms configured to secure with the nose cone connection receiver, and a propeller assembly, configured to connect to the nose cone.

A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

Disclosed here are systems for detachable airframe components including detachable nose cones, propeller assemblies and motors. In some example embodiments, the assemblies include a nose cone with a connection receiver, a motor assembly with a rotatable section, where the rotatable section includes torque arms configured to secure with the nose cone connection receiver, and a propeller assembly, configured to connect to the nose cone.

Disclosed here are systems for detachable airframe components including detachable nose cones, propeller assemblies and motors. In some example embodiments, the assemblies include a nose cone with a connection receiver, a motor assembly with a rotatable section, where the rotatable section includes torque arms configured to secure with the nose cone connection receiver, and a propeller assembly, configured to connect to the nose cone.

An aircraft propulsion system comprises an engine, a propeller drive shaft drivingly engaged with the engine, a propeller for propelling an aircraft and a fan driving cooling air along a flow path in thermal communication with the engine. The engine may be an internal combustion engine or other engine type having heat rejection requirements and the fan may facilitate cooling of the engine. The propulsion system may have a pusher configuration.

The invention relates to a protection dish (32) for a counterbore formed in an aircraft mechanical part, said protection dish (32) having an axial cross-section about an axis (A) having substantially the shape of a U, and comprising a substantially annular wall (34) of axis (A) and a substantially cylindrical rim (36) of axis (A) connected to an outer periphery of said substantially annular wall (34). The invention is characterised in that said dish (32) is configured to be deformed in response to an axial stress (F) of a determined intensity applied on the substantially annular wall (34) thereof from a first state, wherein the substantially cylindrical rim (36) has a first transverse dimension (E) relative to axis (A), to a second state, wherein the substantially annular wall (34) being deformed, the cylindrical rim (36) has a second transverse dimension (E′) relative to the axis (A) that is greater than the first transverse dimension (E) along a transverse direction (T) determined relative to axis (A).

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

A gas turbine engine including: a tail cone; a low pressure compressor; a low pressure turbine; a low speed spool interconnecting the low pressure compressor and the low pressure turbine; and an electric generator located within the tail cone, the electric generator being operably connected to the low speed spool; a structural support housing at least partially enclosing the electric generator, the structural support housing being located within the tail cone; and a temperature control device located within the tail cone between the structural support housing and the tail cone, wherein the temperature control device is in thermal communication with at least one of the structural support housing and the tail cone.