Provided is a casing 21 for an exhaust turbocharger turbine 2, configured so as to house a turbine rotor 23 to be driven by exhaust gas and form a spiral scroll 22 serving as a path for supplying the exhaust gas to the turbine rotor 23, wherein the scroll 22 includes a first region 222a extending from a spiral origin position 222s to a predetermined angle and a second region 222b extending from the predetermined angle to a spiral end position 222e, with the surface area of an interior wall thereof decreasing from the spiral origin position 222s toward the spiral end position 222e, and the interior wall at the first region 222a has a lower surface roughness than that at the second region 222b.

An apparatus and method of transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.

A qualification system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters. The computer system includes at least one simulated engine model configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, a correlation system configured to correlate variations in the set of parameters for each of the gas turbine engine components with a set of the predicted operations of each gas turbine engine, thereby generating a predictive model based on the variations. The computer system also includes a qualification module configured to generate a qualification formula based on the predictive model. The qualification formula is configured to receive a set of measured parameters of an as-manufactured gas turbine engine component and determine when the as manufactured gas turbine engine component is qualified for inclusion in at least one engine.

A mask includes a masking body including at least a first edge, a second edge, and a third edge, together defining at least part of a perimeter around a first surface and a second opposing surface. A standoff arrangement includes at least one projection extending from the first or second surface of the masking body. The at least one projection is connected to the first or second surface at a location inward from the at least one edge of the masking body, thereby defining a first overhanging portion of the masking body overhanging the at least one projection proximate to the at least one edge of the masking body.

A method of manufacturing a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case and a fan liner, wherein the method comprises: providing a mounting ring configured to extend about an inner circumference of the fan case; providing a gasket at an axial end of the mounting ring, wherein the gasket extends around the inner circumference of the fan case; providing the fan liner at the axial end of the mounting ring with the gasket, wherein the fan liner extends around the inner circumference of the fan case; and heating the fan case assembly so as to cure a resin provided between the fan case and fan liner, wherein the heating causes the mounting ring to expand radially relative to the fan case such that the gasket is brought into engagement with the fan case and unwanted migration of resin away from between the fan case and fan liner is restricted.

A blade for a gas turbine engine, and methods of manufacture of such a blade having a continuous density gradient so that the portion of the blade nearest the rotator shaft is of a higher density than the portion of the blade furthest from the rotator shaft.

A fluid cooler for installation in a bypass duct of a turbofan gas turbine engine and associated methods are provided. The fluid cooler includes an inlet duct, a heat exchanger and an outlet duct. The inlet duct includes an inlet protruding into the bypass duct to receive a portion of the bypass air into the inlet duct. The heat exchanger is in fluid communication with the inlet duct. The heat exchanger facilitates heat transfer between a fluid and the portion of bypass air received into the inlet duct. The heat exchanger defines a general flow direction for the portion of bypass air that is different from the main flow direction of bypass air inside the bypass duct. The outlet duct conveys the portion of bypass air from the heat exchanger back to the bypass duct.

An assembly including a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer skin and the inner skin, and the nacelle panel having a free inner enclosure contiguous with the outer skin, and a member forming a link including one or more degrees of freedom, the member being attached to the nacelle panel solely by one or both of the outer skin and the inner skin, and the member extending facing the free inner enclosure.

A heat shield comprising a base portion, a top portion, and a tapered portion extending between the top portion and the bottom portion is described herein, in accordance with various embodiments. The base portion may comprise a sheet metal bounding a triangular void. The top portion may comprise a sheet metal bounding an ovular void.

Systems and methods are provided for acoustic paneling. One embodiment is a method for fabricating an acoustic panel. The method includes receiving a sheet of thermoplastic paper, stamping/conforming the sheet into rows that each comprise a three dimensional shape, and transforming the sheet into a multi-celled core. Transforming the sheet includes identifying fold lines separating the rows, folding the sheet at the fold lines in a pleat fold, thereby uniting upper surfaces of adjacent rows and uniting lower surfaces of adjacent rows; and compressing the rows of the folded sheet together in the presence of heat, causing adjacent rows to fuse together into cells. The method further includes applying a backing sheet to the core, and applying a facesheet to a surface of the core that includes openings which direct a portion of airflow across the facesheet into the cells, resulting in acoustic control.