The inner diameter (122) is sloped relative to an engine axis (A) such that a forward portion of the fan nacelle (120) has a smaller inner diameter (122) than an aft portion of the fan nacelle (120). A fan blade spacer (112) is disposed between a radially inward facing surface of...
A gas turbine engine includes a fan forward of a primary flowpath inlet. The fan includes multiple fan blades distributed radially about, and connected to, a hub. A fan nacelle is p
For material reduction, a fan blade made of solid material for a gas-turbine engine is provided in the area of the blade tip with at least one cavity (<B>5</B>) extending from the face of the blade tip. Thus, apart from the aspect of weight saving, the vibration amplitudes and the...
of EP0794264 Gas turbine engine fan blade with a metallic airfoil having a leading edge, a trailing edge, and a radially outer tip, and at least one laser shock peened surface located along the leading edge with a region having deep compressive residual stresses imparted by laser shock peenin...
Each fan blade (20) of a fan blade assembly (12) for a ducted fan gas turbine engine (10) is provided with a key (25) which cooperates with the fan blade root (23) and fan hub (21) to axially lock the fan blade (20) to the fan hub (21). Each key (25) is deformable under...
Fixing system for the fan blade of a gas turbine enginedoi:EP0690203 B1Kenneth Roy BensonNicholas John KemsleyMichael Joseph KingDavid Sydney KnottEP
Fan blade attachment for gas turbine engine The attachment of the blade to the disk of a gas turbine engine includes a sloped deep slot formed in the rim of the disk for accepting the dovetail of the root of he fan or compressor blade allowing the removal of a single blade from th......
A metal leading edge of a turbine fan blade is manufactured by cutting and shaping an elongated metal part. The metal part has front and rear edges extending lengthwise of the part, and has a generally wedge-shaped transverse cross-section with opposite sides diverging from the front edge towar...
A gas turbine engine for an aircraft including: engine core including a turbine; and fan including a plurality of fan blades extending radially from a hub, each fan blade having a leading and trailing edge. Turbine includes a lowest pressure turbine stage having a row of rotor blades each ext...
A fan blade for a gas-turbine engine which comprises a supporting structure (2) in fiber-composite material is enclosed by a sheet-metal enveloping structure (4) only in an area of the a