Abstract: An aircraft engine having a fan, the fan having at least one flutter-resistant blade, the blade having a leading edge (LE), a trailing edge (TE), a midchord (MC), a minimum radial height rhub, a maximum radial height rtip, and a radial extent between rhub and rtip, wherein, at every point along the radial extent of the blade, the blade has a modeshape value V1 for a blade first vibratory mode defined as V 1 = ? D 1 ? LE ? ? D 1 ? MC ? , and wherein, when the engine is operating between its maximum speed and 70% of that maximum speed, at least 80% of the radial extent of the blade has a modeshape value V1 from 0 to 1.5.

Abstract: An aircraft engine having a compressor, the compressor having at least one flutter-resistant blade, the blade having a leading edge (LE), a trailing edge (TE), a midchord (MC), a minimum radial height rhub, a maximum radial height rtip, and a radial extent between rhub and rtip, wherein, at every point along the radial extent of the blade, the blade has a modeshape value V1 for a blade first vibratory mode defined as V 1 = ? D 1 ? LE ? ? D 1 ? MC ? , and wherein, when the engine is operating between its maximum speed and 70% of that maximum speed, at least 80% of the radial extent of the blade has a modeshape value V1 from 0 to 1.5.

Abstract: An aircraft engine having a turbine, the turbine having at least one flutter-resistant blade, the blade having a leading edge (LE), a trailing edge (TE), a midchord (MC), a minimum radial height rhub, a maximum radial height rtip, and a radial extent between rhub and rtip, wherein, at every point along the radial extent of the blade, the blade has a modeshape value V1 for a blade first vibratory mode defined as V 1 = ? D 1 ? LE ? ? D 1 ? MC ? , and wherein, when the engine is operating between its maximum speed and 70% of that maximum speed, at least 80% of the radial extent of the blade has a modeshape value V1 from 0 to 1.5.

Abstract: The blades for a rotor of a gas turbine engine are all manufactured to the same design. However, manufacturing tolerances mean that in practice each individual blade is different to the others. It is proposed to arrange the blades around the circumference of the rotor in a manner that limits excessive stress being induced in the blades due to differences in the vibration response between a given blade and its two neighbouring blades.

Abstract: A bladed disc comprising a disc hub; a set of blades angularly distributed around the disc hub; wherein there is variation in a geometric parameter between the blades. The blades are positioned around the disc hub such that for a majority of pairs of neighbouring blades in the set, an interval between values of the geometric parameter between the blades of the pair is less than 0.5 standard deviations of the geometric parameter for the set of blades.

Abstract: The blades for a rotor of a gas turbine engine are all manufactured to the same design. However, manufacturing tolerances mean that in practice each individual blade is different to the others. It is proposed to arrange the blades around the circumference of the rotor in a manner that limits excessive stress being induced in the blades due to differences in the vibration response between a given blade and its two neighbouring blades.

Abstract: The blades for a rotor of a gas turbine engine are all manufactured to the same design. However, manufacturing tolerances mean that in practice each individual blade is different to the others. It is proposed to arrange the blades around the circumference of the rotor in a manner that limits excessive stress being induced in the blades due to differences in the vibration response between a given blade and its two neighbouring blades.

Abstract: A bladed disc comprising a disc hub 110; a set of blades 120 angularly distributed around the disc hub; wherein there is variation in a geometric parameter between the blades. The blades are positioned around the disc hub such that for a majority of pairs of neighbouring blades in the set, an interval between values of the geometric parameter between the blades of the pair is less than 0.5 standard deviations of the geometric parameter for the set of blades.

Abstract: The blades for a rotor of a gas turbine engine are all manufactured to the same design. However, manufacturing tolerances mean that in practice each individual blade is different to the others. It is proposed to arrange the blades around the circumference of the rotor in a manner that limits excessive stress being induced in the blades due to differences in the vibration response between a given blade and its two neighbouring blades.

Abstract: The blades for a rotor of a gas turbine engine are all manufactured to the same design. However, manufacturing tolerances mean that in practice each individual blade is different to the others. It is proposed to arrange the blades around the circumference of the rotor in a manner that limits excessive stress being induced in the blades due to differences in the vibration response between a given blade and its two neighbouring blades.

Abstract: The blades for a rotor of a gas turbine engine are all manufactured to the same design. However, manufacturing tolerances mean that in practice each individual blade is different to the others. It is proposed to arrange the blades around the circumference of the rotor in a manner that limits excessive stress being induced in the blades due to differences in the vibration response between a given blade and its two neighbouring blades.