Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a plate and the use of standard fasteners. The plate provides mounting for a nose cone, and the balancing apparatus may be accessed from the front of the assembled engine.

Abstract: A computer-implemented method, apparatus, and computer program product are disclosed for securing node port access in a switched-fabric storage area network. Permitted combinations of fabric port identifiers and node port identifiers are specified. A node port receives a request to access the node port. A node port identifier, which identifies the device that is attempting to access the node port, is determined from the request. A fabric port identifier is determined that identifies a fabric port through which the device transmitted the request. Access to the node port is granted if the fabric port identifier and node port identifier form a permitted combination.

Abstract: A vane assembly for a gas turbine engine including a shroud ring with openings and isolating means isolating a vane extremity within each opening, the isolating means cooperating to form a continuous gas path surface completely covering at least an axial portion of a surface of the shroud ring.

Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined therein about a circumference thereof and vanes extending radially from the shroud with a vane tip in each opening. Isolating means are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining means for restricting movement of the vane tip in an axial direction relative to said shroud.

Abstract: A vane for a vane assembly of a gas turbine engine includes a vane root connected to the airfoil portion opposite a tip thereof. The vane root includes a platform and a button portion interconnecting the platform and the airfoil position. The button portion has relatively blunt leading and trailing ends which respectively protrude beyond leading and trailing edges of the airfoil portion.

Abstract: A compressor vane having a root, a tip and an airfoil portion extending between the root and the tip is disclosed. A grommet is used in conjunction with the vane and has a lip sealingly surrounding a portion of the vane root and a circumferential portion protruding around a perimeter of the lip in engagement with a surface of a platform of the vane root. The circumferential portion has a profile similar to that of the airfoil portion.

Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined therein about a circumference thereof and vanes extending radially from the shroud with a vane tip in each opening. Isolating means are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining means for restricting movement of the vane tip in an axial direction relative to said shroud.

Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a nose cone and the use of standard fasteners. The nose cone is adapted to cooperate with at least one standard fastener to retain the standard fastener to the nose cone to rotationally balance the shaft.

Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a plate and the use of standard fasteners. The plate provides mounting for nose cone, and the balancing apparatus may be accessed from the front of the assembled engine.