Airfoil assembly
AssigneeGeneral Electric Company
InventorsKishore Ramakrishnan, Valeria Andreoli, Trevor Howard Wood
Life of this patent
Estimating the term…
Abstract
An airfoil assembly for a gas turbine engine includes a first blade having a first leading edge and a first trailing edge, and a second blade circumferentially spaced from the first blade where the second blade has a second leading edge and a second trailing edge. The first blade includes a feature formed on the first leading edge where the first blade includes a chord extending from the first leading edge to the first trailing edge. The chord is located radially where a projection of a line normal to an intersection of the chord with the first trailing edge intersects the second leading edge. At least a portion of the feature is radially located at or inboard of the chord.
Claims20
An airfoil assembly for a gas turbine engine, the airfoil assembly comprising:
- a first blade having a first leading edge and a first trailing edge;
- and
- a second blade circumferentially spaced from the first blade, the second blade having a second leading edge and a second trailing edge;
- and
- wherein the first blade includes a feature formed on the first leading edge, wherein the first blade includes a chord extending from the first leading edge to the first trailing edge, the chord located radially where a projection of a line normal to an intersection of the chord with the first trailing edge intersects the second leading edge, and wherein at least a portion of the feature is radially located at or inboard of the chord.
An airfoil assembly for a gas turbine engine, the airfoil assembly comprising:
- a plurality of circumferentially spaced blades, wherein each blade of the plurality of blades includes:
- a leading edge and a trailing edge;
- a pitch change axis;
- and
- a feature formed on the leading edge;
- and
- wherein the feature is formed at a radial location R and having a leading edge location Z relative to the pitch change axis, and wherein the feature is defined having a single portion where d2ZLE/dR2<0.
An airfoil assembly for a turbomachine, the airfoil assembly comprising:
- a turbomachine;
- and
- a fan assembly rotatable by the turbomachine, the fan assembly including an airfoil assembly comprising:
- a first blade having a first leading edge and a first trailing edge;
- and
- a second blade circumferentially spaced from the first blade, the second blade having a second leading edge and a second trailing edge;
- and
- wherein the first blade includes a feature formed on the first leading edge, wherein a chord is defined on the first blade extending from the first leading edge to the first trailing edge, the chord located radially where a projection of a line normal to an intersection of the chord with the first trailing edge intersects the second leading edge, and wherein at least a portion of the feature is radially located at or inboard of the chord.
Dependencies are inferred from the claim text.