Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed.

Abstract: A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge. A rotor and a gas turbine engine are also disclose.

Abstract: An airfoil includes a dovetail root having a base. A grooved slot is disposed in the base and a plurality of root lightening cavities is disposed in the grooved slot.

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract: A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge. A load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.

Abstract: A blade for use in a gas turbine engine has an airfoil and a dovetail. The airfoil extends radially outwardly of the dovetail. An inner surface of the dovetail includes a slot extending along a length of the dovetail between a leading edge and a trailing edge.

Abstract: Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed.

Abstract: A blade of a gas turbine engine includes a blade portion. The blade portion includes a first portion located radially outwardly that is located in a flow path and a second portion located radially inwardly of the first portion that is not located in the flow path. A plurality of external cavities is in the second portion of the blade portion.

Abstract: An airfoil includes a dovetail root having a base. A grooved slot is disposed in the base and a plurality of root lightening cavities is disposed in the grooved slot.

Abstract: A non-ferrous shaft includes multiple non-integral ferrous tooth components, thereby allowing a sensor to detect the shaft speed.

Abstract: A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge. load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.

Abstract: An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.

Abstract: Utilization of certain essentially nonvolatile oligo alkylene glycols and or their mono alkyl ethers, and/or hydroxy esters thereof, in combination with selected, optionally (partially) neutralized, nonvolatile hydroxyl group bearing di/oligoamines, optionally in conjunction with defoamers, water, and/or wetting agents, have been found to produce VOC free, minimally corrosive, highly efficient strippers for coatings, such as paints, printing inks, and floor waxes.

Abstract: Combinations of essentially nonvolatile, unsaturated ethers and/or esters, and small proportions of low glass transition temperature (Tg) latex reins, as replacements for volatile organic compounds (VOCs) as coalescents and optionally reactive amines (as replacements for conventionally employed volatile amines/ammonia neutralizers, respectively), provides economical, low/no VOC-containing acrylic, styrenic copolymer, polyester, polyurethane and vinyl copolymer latex based coatings, paints, and inks; which out/perform their conventional counterparts.

Abstract: An implement is coupled to the forward ends of a pair of loader lift arms through the medium of an attachment assembly comprising a pair of implement carriers respectively vertically pivotally mounted to the pair of loader lift arms by a connector rod that extends through aligned holes provided in lower locations of the carriers, the connector rod being releasably fastened to each of the carriers so that the latter are pivoted in unison by hydraulic cylinders connected between the lift arms and upper locations of the carriers. The attachment assembly further includes a pair of downwardly opening hooks welded to upper locations of the back side of the implement and including arcuate portions respectively receiving cylindrical bars defining upper ends of the pair of carriers. Also fixed to the back side of the implement are a pair of rearwardly projecting, tapered connecting pins that are respectively received in holes provided in mounting plates forming lower forward portions of the carriers.