Abstract: An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive grit particles in a ceramic matrix. The grit particles may be selected from cubic boron nitride (CBN), zirconia, alumina, silicon carbide, diamond and mixtures thereof.

Abstract: An abradable coating for interaction with tips of airfoils (such as vanes or blades of a compressor of a gas turbine engine) includes a metal bond coat thermal, a ceramic layer, and an abradable layer. The ceramic layer on the metal bond coat provides insulation and acts as a fuse that is adapted to spall off upon high rub interaction. The abradable coating on the ceramic layer contacts the tips of the airfoils during operation of the compressor. The abradable coating is sufficiently abradable to roundup the coating by contact with the airfoil tips.

Abstract: A gas turbine engine having an engine casing extending circumferentially about an engine centerline axis; and a compressor section, a combustor section, and a turbine section within said engine casing. At least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is metal having a thin film ceramic coating and the at least one seal member is coated with an abrasive.

Abstract: An air seal for use with rotating parts in a gas turbine engine has a matrix of agglomerated fine hBN (hexagonal boron nitride) powder, the particles of which having a first dimension, and of a fine metallic alloy powder, the particles of which having a second dimension. An hBN (hexagonal boron nitride) powder, the particles of which have a third dimension that is greater than the first dimension, is mixed with the matrix.

Abstract: A longitudinal stack of gas turbine engine rotor disks each include an annular spacer which transmits compressive preloading of the stack to an adjacent disk, the spacer and an annular shoulder on the disk rim defining an annular slot which accommodates the base of a segmented annular blade cluster which shields the rim from some of the heat associated with the flow of working fluid around the disks.

Abstract: A rotor assembly for a gas turbine engine includes a rotor airfoil and a first rotor disk. The rotor airfoil extends along a radial axis. The first rotor disk includes an outer rim, a bore and a web extending between the outer rim and the bore. The first rotor disk is axially offset from the radial axis of the rotor airfoil.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members are tubular in shape and provide a radially extending passage. The anti-vortex members include an outer end having a circumferential side with an opening in fluid communication with the radial passage.

Abstract: A gas turbine rotor is provided with a longitudinal stack of blade supporting disks each including a medial web and a radially outer rim. The disks are spaced from one another by axial gaps. The disks include recesses in the forward and aft major surfaces thereof proximal to the juncture of the webs and rims thereof. Annular spacers received with the recesses in the disks span the axial gaps and provide a load path for the axial compressive preloading of the disks and the transmission of torque along the disk stack.

Abstract: A longitudinal stack of gas turbine engine rotor disks each include an annular spacer which transmits compressive preloading of the stack to an adjacent disk, the spacer and an annular shoulder on the disk rim defining an annular slot which accommodates the base of a segmented annular blade cluster which shields the rim from some of the heat associated with the flow of working fluid around the disks.

Abstract: A seal in a gas turbine engine component between an airfoil with a radial outward end and a seal member adjacent it coated with an abrasive layer having a ceramic component in a matrix of a metal alloy with hexagonal BN. The ceramic component is selected from silica, quartz, alumina, zirconia and mixtures thereof and the metal is selected from nickel, cobalt, copper and iron. The ceramic ranges from about 1% to about 10% and the amount of nickel, cobalt, copper or iron will range from about 30% to about 60% by volume, and the balance is hBN.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: A compressor rotor seal includes a bare radial inward end of a rotor vane in proximity to a rotor surface coated with an abrasive material.

Abstract: An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive grit particles in a ceramic matrix. The grit particles may be selected from cubic boron nitride (CBN), zirconia, alumina, silicon carbide, diamond and mixtures thereof.

Abstract: An abrasive coating for rotor shafts that interact with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating including a metal bond coat layer on the rotor shaft, and an abrasive top coating bond coat layer for contact with vanes during operation of the rotor shaft, the abrasive coating including a plurality of abrasive grit particles in a matrix. the abrasive grit particles are selected from the group consisting of cubic boron nitride (CBN), zirconia, alumina, silicon carbide, diamond and mixtures thereof.

Abstract: A split disk assembly for a gas turbine engine includes a forward disk section and an aft disk section, the aft disk section engageable with the forward disk section to retain a multitude of rotor blades therebetween.

Abstract: An abradable coating for interaction with tips of airfoils (such as vanes or blades of a compressor of a gas turbine engine) includes a metal bond coat thermal, a ceramic layer, and an abradable layer. The ceramic layer on the metal bond coat provides insulation and acts as a fuse that is adapted to spall off upon high rub interaction. The abradable coating on the ceramic layer contacts the tips of the airfoils during operation of the compressor. The abradable coating is sufficiently abradable to roundup the coating by contact with the airfoil tips.

Abstract: A rotor assembly for a gas turbine engine includes a rotor airfoil and a first rotor disk. The rotor airfoil extends along a radial axis. The first rotor disk includes an outer rim, a bore and a web extending between the outer rim and the bore. The first rotor disk is axially offset from the radial axis of the rotor airfoil.

Abstract: An air seal for use with rotating parts in a gas turbine engine has a matrix of agglomerated fine hBN (hexagonal boron nitride) powder, the particles of which having a first dimension, and of a fine metallic alloy powder, the particles of which having a second dimension. An hBN (hexagonal boron nitride) powder, the particles of which have a third dimension that is greater than the first dimension, is mixed with the matrix.