Abstract: A method of inspecting components between a pre-coated state and a post-coated state is provided. The method entails providing at least first and second datum points onto the component in the pre-coated state, where each of the at least first and second datum points have a substantially hemi-spherical shape and a center point. The center points of each of the at least first and second datum points are utilized for measurement of a selected portion on the component in the pre-coated state. Then, the component is coated. Next, the center points of each of the at least first and second datum points are utilized for measurement of the selected portion on the component in the post-coated state. The pre-coated state measurements and the post-coated state measurements are then correlated for inspection purposes.

Abstract: A rotor in a gas turbine engine has a rotor body with at least one slot receiving a blade. The blade has an outer surface formed of a first material and an airfoil extending from a dovetail. The dovetail is received in the slot. A grounding element is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The grounding element is in contact with a rotating element that rotates with the rotor and is formed of a third material. The first material is less electrically conductive than the third material. The grounding element and rotating element together form a ground path from the portion of the dovetail into the rotor.

Abstract: A rotor for use in a gas turbine engine has rotor slots receiving a blade. The blades have an airfoil extending from a dovetail, and the dovetail is received by a rotor slot. A spacer is positioned between an inner wall of the dovetail and an outer wall of the slot, and the spacer is formed with a removal slot. A spacer, a gas turbine engine, and a method are also disclosed.

Abstract: A fan section of a gas turbine engine is disclosed. The fan section may comprise a fan having a hub and a plurality of blades extending radially from the hub. The fan section may further comprise a fan case surrounding the fan and an inlet structure located upstream of the fan and defining at least a portion of an airflow path leading to the fan. The inlet structure may have at least one panel removably connected to at least one structural element of the gas turbine engine, and an opening may be exposed when the panel is disconnected from the gas turbine engine. The opening may provide clearance for removal of at least one of the plurality of blades from the hub.

Abstract: A fan assembly is disclosed which includes a rotor having an outer periphery and at least one slot extending radially inwardly through the outer periphery. The slot terminates at a base surface disposed at a radial depth from the outer periphery of the rotor. The fan assembly also includes at least one fan blade that includes an airfoil connected to a root. The root is received in the slot. The root terminates in an inner face having a radial length that is less than the radial depth of the Slot to define a gap between the inner face of the root and the base surface of the slot when the root is bias away to the base surface of the slot. A spacer is disposed within a gap, wherein a spacer is fabricated from a polymer, which may be a composite material such as a polymer embedded with reinforcing materials such as carbon fibers and glass fibers.

Abstract: A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface.

Abstract: A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.

Abstract: A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail, and an airfoil extends radially outwardly from the dovetail. The ribs having a thickness defined as measured from said leading edge toward said trailing edge. The ribs have break-edges at ends of the thickness that extend away from an outer face of the rib.

Abstract: A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. The channels have a termination end adjacent a radially inner end of the ribs. The termination end is formed along a complex fillet with a first radius of curvature formed at the termination end, and a second radius of curvature merging into sides of the ribs. The second radius of curvature is greater than the first radius of curvature.

Abstract: A fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are is also disclosed.

Abstract: A rotor in a gas turbine engine has a rotor body with at least one slot receiving a blade. The blade has an outer surface formed of a first material and an airfoil extending from a dovetail. The dovetail is received in the slot. A grounding element is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The grounding element is in contact with a rotating element that rotates with the rotor and is formed of a third material. The first material is less electrically conductive than the third material. The grounding element and rotating element together form a ground path from the portion of the dovetail into the rotor.

Abstract: A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.

Abstract: A fan blade includes a root including a front surface, a rear surface, a first side surface connected to the front surface and the rear surface, and a second side surface connected to the front surface and the rear surface. The front surface engages the first side surface and the second side surface by one or more blunted surfaces, and the rear surface engages the first side surface and the second side surface by one or more blunted surfaces. A blade extends from the root.

Abstract: A fan rotor includes a fan blade for use in a gas turbine engine includes a sheath formed of a material that is more conductive than a main fan blade body. A grounding element provides a grounding path from the sheath into a rotor receiving the fan blade. A gas turbine engine incorporating the fan blade is also disclosed.

Abstract: A turbine engine component has an airfoil portion with a tip portion and the tip portion has at least one chamfered edge on one side. If desired, the tip portion may have a first chamfered edge on a first side and a second chamfered edge on a second side opposed to the first side. A flattened tip portion may extend between the first and second chamfered edges. A tip treatment may be applied to the flattened tip portion.

Abstract: A fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are is also disclosed.

Abstract: A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail, and an airfoil extends radially outwardly from the dovetail. The ribs having a thickness defined as measured from said leading edge toward said trailing edge. The ribs have break-edges at ends of the thickness that extend away from an outer face of the rib.

Abstract: A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. The channels have a termination end adjacent a radially inner end of the ribs. The termination end is formed along a complex fillet with a first radius of curvature formed at the termination end, and a second radius of curvature merging into sides of the ribs. The second radius of curvature is greater than the first radius of curvature.

Abstract: A blade for a turbine engine having a centerline. The blade comprises: a root section extending at an angle relative to the centerline; and an airfoil section extending from the root section. The root section is directly adjacent said airfoil section. In other words, the blade is neckless. The blade is part of a rotor assembly, and is preferably a fan blade.

Abstract: A blade for a turbine engine having a centerline. The blade comprises: a root section extending at an angle relative to the centerline; and an airfoil section extending from the root section. The root section is directly adjacent said airfoil section. In other words, the blade is neckless. The blade is part of a rotor assembly, and is preferably a fan blade.