A fan blade device includes a plurality of main fan blades and extension fan blades. Each main fan blade includes a main fan blade body arranged obliquely, a plurality of first protrusions, and at least one engaging groove. Each extension fan blade includes an extension fan blade body arranged obliquely and having a top surface that is contiguously flush with a top surface of the main fan blade body of a respective main fan blade, a plurality of second protrusions respectively abutting against the first protrusions of the respective main fan blade, and at least one engaging piece engaging the at least one engaging groove of the respective main fan blade.

Platform for an aircraft turbo machine fan rotor, the platform being configured to be secured to a fan disc between two adjacent fan blades. The platform further including a longitudinal wall defining an aerodynamic external face. The wall includes a honeycomb structure interposed between two skins which are respectively an internal skin and an external skin, with the external skin defining the aerodynamic external face.

An impeller for a centrifugal turbomachine includes: a hub having a small-diameter portion positioned at a first end portion in an axial direction and a large-diameter portion positioned at a second end portion in the axial direction, the large-diameter portion having a greater diameter than the small-diameter portion; and a blade having a first edge positioned at an axial-directional position of the small-diameter portion and a second edge positioned at an axial-directional position of the large-diameter portion, the blade being disposed on an outer peripheral surface of the hub. The impeller is configured such that, when a first radial-directional cross section is a cross section of the impeller at an axial-directional position passing a tip of the first edge, at least a part of the first radial-directional cross section in a blade-height range of 50% or more is inclined downstream in a rotational direction of the impeller with respect to a radial direction.

A propulsor is described in which rotation of the frustum of a right circular cylinder generates thrust. Variants of this basic geometrical shape are also described that enable multiple means for propelling fluid past the propulsor.

A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes fan blades defining a fan diameter. The heat exchanger module is in communication with the fan assembly by an inlet duct, and the heat exchanger module further includes radially-extending hollow vanes arranged in a circumferential array, with a channel extending axially between hollow vanes. Each hollow vane accommodates at least one heat transfer element to transfer heat from a first fluid contained within the or each heat transfer element to a corresponding vane airflow passing through the hollow vane and over a surface of the or each heat transfer element. Each hollow vane further includes a flow modulator configured to regulate airflow in proportion to total airflow entering the heat exchanger module in response to a user requirement.

Disclosed is a compact egg-shaped propeller, including an outer shell, an inner shell, and a driving motor unit arranged in the inner shell. The outer shell is detachably connected to the inner shell; the outer shell is egg-shaped; the outer shell is provided with a front cover at a top of the driving motor unit; the outer shell is provided with a jet orifice at a tail portion of the driving motor unit; blades are connected to one side of the driving motor unit close to the front cover; the driving motor unit is connected to a main control compartment; foldable handles are connected to a left side and right side of the main control compartment respectively; and the foldable handles are movably connected to the inner shell. By means of the layout, the gravity center is centered, the structure is compact and simple, and the appearance is simple and beautiful; the blades and the motor are designed in front, and the semi-circular front cover prevents debris and hands from entering; a battery indicator can display current remaining power to a user; a buoyancy block ensures that the whole device does not sink down after a user loosens the hands in water, facilitating search; and when the device is not in use, the handles can be folded, thereby facilitating storage and carrying.

A propeller. The blades of the propeller are characterized by a blade center axis which corresponds to a generator line of a cone to which the blade, or blade thrust surface, conforms. The propeller hub is fixed to the blade at the root, in line with the blade center axis, such that the hub axis and blade center axis lie in the same plane, and the leading edge of the blade is positioned forward (referring to the upstream direction of movement caused by the propeller) of the trailing edge of the blade.

A propeller. The blades of the propeller are characterized by a blade center axis which corresponds to a generator line of a cone to which the blade, or blade thrust surface, conforms. The propeller hub is fixed to the blade at the root, in line with the blade center axis, such that the hub axis and blade center axis lie in the same plane, and the leading edge of the blade is positioned forward (referring to the upstream direction of movement caused by the propeller) of the trailing edge of the blade.

A heat exchanger has a first plurality of passages extending in a first direction and to receive a first fluid and a second plurality of passages extending in a second direction, and to receive a second fluid, and the first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of the first plurality of passages in different locations across the cross-sectional face of the heat exchanger. A gas turbine engine and a method of forming a heat exchanger are also disclosed.