Abstract: A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shroud segments, and guide vanes structurally interconnecting the inner and outer shrouds. The guide vanes include a plurality of first guide vanes between and connecting first pairs of the inner and outer shroud segments, and a plurality of second guide vanes between and connecting second pairs of the inner and outer shroud segments. The first and second guide vanes are formed of different first and second materials, respectively, with the first material having lower strength, modulus, and/or density than the second material. The structural interconnection between the inner and outer shrouds is dominated by the second guide vanes.

Abstract: A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shroud segments, and guide vanes structurally interconnecting the inner and outer shrouds. The guide vanes include a plurality of first guide vanes between and connecting first pairs of the inner and outer shroud segments, and a plurality of second guide vanes between and connecting second pairs of the inner and outer shroud segments. The first and second guide vanes are formed of different first and second materials, respectively, with the first material having lower strength, modulus, and/or density than the second material. The structural interconnection between the inner and outer shrouds is dominated by the second guide vanes.

Abstract: A fuel injection system for use with a gas turbine engine includes a plurality of thermally compatible fuel nozzles. Each fuel nozzle includes a delivery system to deliver a fluid supply to the gas turbine engine and a support system for supporting the delivery system. The delivery system is disposed within the support system and is subjected to lower operating temperatures than the support system. The delivery system is fabricated from a material having a coefficient of expansion approximately twice a coefficient of expansion for the material used in fabricating the support system.

Abstract: A plain blank is sized to produce an airfoil. The blank is plastically formed to include a pocket blending smoothly in one side thereof. Leading and trailing edges of the airfoil are benched. And, filler is placed into the pocket to effect an aerodynamic profile for the airfoil.

Abstract: A blade containment structure for turbomachinery, such as a high bypass turbofan engine. The blade containment structure includes a first casing member having a wall that defines an inner containment shell that immediately surrounds the blades of the turbomachine, and a second casing member assembled to the first casing member. The second casing member has a wall that defines an outer containment shell that surrounds the inner containment shell, such that a cavity is defined by and between the inner and outer containment shells. The first casing member is formed from a high-toughness material such as steel or a nickel-base alloy, while the second casing member is formed from a lower-weight and potentially lower-toughness material as compared to the material of the first casing member.

Abstract: A compressor stator includes a plurality of vanes affixed to outer and inner bands. A seal includes a pair of mounting rails disposed in respective hooks in the inner band. A spring is affixed to the inner band in compression with an outboard side of the seal to load the rails in radial engagement with the hooks.

Abstract: A plain blank is sized to produce an airfoil. The blank is plastically formed to include a pocket blending smoothly in one side thereof. Leading and trailing edges of the airfoil are benched. And, filler is placed into the pocket to effect an aerodynamic profile for the airfoil.

Abstract: An interstage seal includes a seal pad attached to a backing strip. A plurality of tab springs are fixedly attached to the outboard side of the strip for engaging an inner band of the supporting stator sector.

Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and a tip, and axially between a leading edge and a trailing edge. The airfoil further includes a pocket disposed in the first side having an elastomeric filler bonded therein. A panel is bonded to the filler along the pocket for allowing differential movement therebetween for damping vibratory response of the airfoil.

Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.

Abstract: A gas turbine engine fan blade includes an airfoil and dovetail having an integral aluminum core and a fatigue resistant reinforcing sheath.

Abstract: An actuation system for variable stator vanes pivotally mounted in a casing includes a plurality of levers joined to the respective vanes. An actuation ring coaxially surrounds the casing adjacent to the levers. A plurality of circumferentially spaced apart ring guides are joined to the casing for guiding circumferential rotation of the ring. Respective slip joints are provided between each of the levers and the actuation ring for varying pivot length of the levers as the ring is rotated for effecting nonlinear vane actuation.

Abstract: A fan blade includes a metal airfoil having first and second opposite sides extending radially between a root and tip, and axially between a leading edge and a trailing edge. The airfoil further includes a plurality of pockets disposed in the first side and separated by corresponding ribs. A filler is bonded in the pocket, and is coextensive with the airfoil first side. Radial and diagonal ribs respectively intersect solely each other for selectively increasing torsional and bending stiffness to increase frequency margin between adjacent torsional and bending resonant modes of vibration.

Abstract: A seating spring is provided for a compressor stator having a radially outer casing with a circumferential casing slot for mounting a plurality of circumferentially adjoining vane sectors at outer bands thereof. The seating spring includes a reaction tab configured to abut the casing at one side of the casing slot. A resilient spring arm is fixedly joined to the reaction tab and is configured to abut a respective one of the outer bands to in-turn bias the one outer band against the casing at an opposite side of the casing slot.

Abstract: A damper which provides both blade to blade and blade to ground damping is described. In one embodiment, the damper includes a retainer and a chicklet. The retainer is secured to a rotor disk by a bolt which extends through an opening in the disk and an opening in the retainer. The retainer includes support flanges which facilitate positioning retainer relative to the disk, and sidewalls (or guides) for limiting movement of the chicklet. The chicklet is movably positioned within the retainer, and movement of the chicklet is limited by sidewalls and a cross wall member of the retainer. The retainer positions the chicklet so that in operation, a contact surface of chicklet makes blade to blade contact with adjacent blades. In operation, centrifugal forces drive the chicklet into contact with the blade platforms. Since the chicklet is in contact with adjacent blades, blade to blade damping is provided.

Abstract: A dome assembly for a multiple annular combustor is disclosed as including an annular dome plate having at least two radial domes, wherein each of the radial domes include a plurality of circumferentially spaced openings therein. A heat shield is positioned within each of the openings, with a threaded forward end located upstream of the dome plate and an aft end located downstream of the dome plate. A retainer nut with threads formed on an annular surface thereof is matingly engagable with the forward end of each heat shield. When the retainer nut is tightened onto the heat shield forward end, the heat shield is mechanically attached to the dome plate. Preferably, at least one centerbody extends axially downstream from either the radially outer or inner side of the aft end. The dome assembly includes a ferrule within each of the dome plate openings for receiving an air/fuel mixer therein, the ferrule having an annular sealing flange extending radially therefrom.

Abstract: An airfoil includes preformed first and second sides joinable together at a bond line extending between first and second opposite edges thereof. The first side includes a first extension having a proximal end forming a first end of the bond line, an intermediate section, and a distal end. The second side includes a second extension extending from the airfoil first edge which is fixedly joinable to the distal end of the first extension. The intermediate section of the first extension is spaced from the airfoil first edge to define therewith a working void so that pressure loading on the intermediate section is carried in part through the bond line first end for diffusion bonding thereof.

Abstract: Metal alloy fan blades reinforced with a metal matrix composite for enhancing stiffness of the fan blades without a significant weight penalty, and which are suitable for use in high bypass turbofan engines. The metal matrix composite is bonded to each fan blade near its root so as to increase stiffness and thereby provide frequency and stability control to the fan blades. As a result, a lower engine weight can be realized by using more fan blades without the need for a part span shroud.

Abstract: Hollow airfoils, such as fan blades, nozzles and struts used in axial flow gas turbine engines, that have improved resistance to impact from foreign objects are disclosed. Relocation of airfoil material is used to preferentially strengthen the airfoil to respond to the stress from the impact of a foreign object. Internal spacers are redistributed toward the leading edge and the material from the skin of the concave side and the convex side is shifted from one side to the other and toward the leading edge of the airfoil where impact stress is greatest.

Abstract: A variable pitch propeller blade system includes a conductive clevis attached to a rotor, a mating non-conductive clevis fastened to a non-conductive propeller blade, a pin journaling through bores in each clevis, joining the clevises to form a hinge joint, and a conductive path along a substantial part of the propeller blade.