Abstract: When A denotes a required oil lower limit amount for one bearing near an oil supply source, and B and C respectively denote a required oil lower limit amount and a safety surplus oil amount for the other bearing away from the source, an amount of oil equal to A+B+C is supplied from the source and a hole diameter and the number of first oil holes are set such that an amount of oil to be supplied to the one bearing is equal to the amount A. Thus, the oil with the amount A can be securely supplied to the one bearing. Also, oil with the sum of the amounts B and C is supplied to the other bearing so that the oil with the amount B can be securely supplied to the other bearing which tends to receive oil insufficiently because of its remoteness from the source.

Abstract: A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.

Abstract: A case assembly includes a plurality of segments, at least one braze joint, and one or more welds. The braze joint connects the plurality of segments together and the one or more welds extend across adjacent segments.

Abstract: A system for detecting deformation of a fan for an aeroengine, the fan including a rotor including plural blades made of composite material including woven fibers. At least one of the fibers in each of the blades is an optical fiber including at least one portion defining a Bragg grating. The system further includes a transceiver connected to the optical fiber and configured to send an optical signal into the optical fiber and to receive an optical signal in response from the optical fiber, and a detector module connected to the transceiver to detect deformation of the fan when the received optical signal presents correlation with a predetermined signature of a damped impact on a blade at a determined speed of rotation. This deformation may be the result of a foreign object impacting against a blade of the fan or may follow from variation in an internal defect.

Abstract: A fuel pump module includes a suction filter, a fuel pump portion having an end part opposing the suction filter, and a holding member allowing the fuel pump portion to rotate around a central axis of the fuel pump portion and restricting the fuel pump portion from moving in an axis direction. A convex part protruding toward the suction filter is defined at the end part of the fuel pump portion. The holding member is positioned between the fuel pump portion and the suction filter and has a concave part, in which the convex part is inserted, such that a clearance is defined between the convex part and the concave part in a radial direction. The convex part has a tip end capable to be in contact with the concave part in the axis direction.

Abstract: An apparatus and method for controlling turbine blade tip clearance is disclosed herein. A blade track assembly can include a blade track carrier having a plurality of slots and rails defined by paths that vary in radial position as a function of circumferential location. An expansion ring can be operably coupled with the slots of the blade track carrier. A plurality of blade track segments can be operably coupled with the expansion ring and engageable with the rails of the blade track carrier such that expansion and contraction of the expansion ring causes radially outward movement and radially inward movement, respectively, of the blade track segments.

Abstract: A turbine blade airfoil (32) with a center of mass (ACM) that is laterally offset from the center of mass (PCM) of a platform (42) to which the airfoil is attached. Respective offsets (da, dp) balance these centers of mass (ACM, PCM) about an attachment plane (64) of the blade root (30), providing balanced centrifugal loading on opposite lobes (51, 52) or other attachment surfaces of the root. The attachment plane (64) may be a plane of bilateral symmetry of the root, and/or it may include an attachment axis (65) that passes through the root center of mass (RCM) along a radius of rotation of the airfoil. The airfoil and platform centers of mass (ACM, PCM) may be dynamically balanced about the attachment axis (65) and/or the attachment plane (64).

Abstract: A device for connecting a front frame of a turbojet engine nacelle to a fan casing includes a locking pin connected to a first assembly flange and a retaining flange that is movably mounted and has at least one opening. In particular, the locking pin has a shank passing through an orifice of a second assembly flange secured to the fan casing. The opening is crossed through by the shank of the locking pin and interacts with an end groove of said locking pin. When the retaining flange is in the unlocking position, the opening has dimensions larger than those of the shank of the locking pin, and when the retaining flange is in the locking position, the opening has dimensions larger than a thickness of the locking pin at its groove but smaller than an overall thickness of the shank of the orifice of the second flange.

Abstract: A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin.

Abstract: A fan housing of a ram air fan assembly is provided including a flange having at least one tab. The at least one tab includes a first portion extending generally perpendicularly from the flange and a second portion extending generally parallel to the flange. A notch is formed by an inclined surface and a curved surface at an intersection between the first portion and the second portion. The second portion is elongated and extends about 0.020 inches beyond a front surface of the first portion.

Abstract: An apparatus includes a disk, an attachment member, and a blade. The disk has an outer surface including a coupling portion. The attachment member has a coupling portion and defines at least a portion of an opening. The coupling portion of the first attachment member is configured to be coupled to the coupling portion of the disk. A portion of the blade is configured to be disposed within the opening when the coupling portion of the attachment member is coupled to the coupling portion of the disk.

Abstract: A pump used in a gasification system, the pump comprises a housing having an inlet and an outlet, a rotor supported within the housing for rotation relative to the housing, the rotor comprising a hub, a plurality of disks spaced apart by sections of the hub, and defining a plurality of transport channels for transporting solid carbonaceous feedstocks for the gasification system, and an interior feedstock facing surface adjacent to the solid carbonaceous feedstocks, wherein at least a portion of the interior feedstock facing surface is coated with a coating.

Abstract: An exemplary nozzle ring has two fastening rings and a plurality of guide vanes, wherein holes are provided in one of the fastening rings for accommodating pins of the guide vanes, and openings are provided in the other fastening ring for accommodating positioning aids on the guide vanes.

Abstract: Wind turbine comprising a rotor having a hub carrying one or more blades, an air intake and a nacelle, the hub being rotatably mounted on a frame and the frame extending forward into the hub, wherein an air flow passage is provided between an inside portion of the hub and the nacelle via at least one first opening to the hub.

Abstract: A pump for pumping a fluid includes a motor, a drive shaft, an impeller, a pump housing having an inlet and an outlet portion, and an extension tube extending between the motor and the pump housing. Preferably, a portion of the fluid to be pumped is contained within the extension tube at a relatively constant level to provide a seal.

Abstract: A rotor assembly having a shaft, a bearing assembly, an impeller and a shroud. The impeller and the bearing assembly are mounted to the shaft, and the shroud is mounted to the bearing assembly so as to cover the impeller.

Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. At least one propeller blade is fixedly attached to both the hub and ring shroud and extends radially therebetween for mutual rotation therewith. At least one stub blade has a first stub end radially spaced from a second stub end. The first stub end is fixedly attached to a selected one of the hub and ring shroud. The second stub end is cantilevered from the first stub end and is radially interposed between the first stub end and the selected one of the hub and ring shroud.

Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.

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: Gas turbine engine blade squealer tips incorporate cooling slots formed in the suction side rail downstream of the leading edge for directing cooling gas flow along an inside edge of the squealer tip pressure side rail. Some embodiments incorporate a tip fin on the suction side rail proximal a cooling slot. Segmented suction side rail embodiments abrade opposing turbine casing abradable surfaces prior to potential contact with the pressure side rail, reducing likelihood of pressure side rail friction heating. During turbine engine operation cooler pressure side rails reduce likelihood of squealer tip erosion.