An abradable material includes a matrix material defining pockets of fluid. The abradable material also includes an outer surface configured to be coupled to an interior surface of a fan case such that in response to the outer surface being coupled to the fan case, the abradable material is positioned circumferentially about an axis The abradable material also includes an inner surface defining a circumferential ridge and a circumferential groove.

An airfoil body may include a plurality of tubercles along a leading edge of the airfoil body and a plurality of crenulations along a trailing edge of the airfoil body, wherein at least one of a position, a size, and a shape of the plurality of tubercles and the plurality of crenulations varies in a non-periodic fashion. The non-periodic fashion may be according to a Fibonacci function and may mimic the configuration of a pectoral fin of a humpback whale. The tubercles and crenulations may be defined with respect to a pivot point. The spanwise profile, including the max chord trailing edge curvature, may closely follow divine spirals and related Fibonacci proportions. The spanwise chord thickness may vary in a nonlinear pattern. Related methods are also described.

According to one embodiment of this disclosure a core includes a first end and a second end spaced generally opposite from the first end. The core further includes a stacking axis defined between the first end and second end and a first toroidal structure located between the first end and the second end. The first toroidal structure includes a first passage extending through the first toroidal structure in a first direction that is perpendicular to and passes through the stacking axis. The core also includes a second toroidal structure located between the first toroidal structure and the second end. The second toroidal structure includes a second passage extending through the second toroidal structure in a second direction. The first direction and the second direction are oriented along the stacking axis at a non-zero degree angle with respect to each other.

The present disclosure relates to a structure for a rotor for removing bearing oil, including a rotor shaft disposed in a casing of a turbine and an annular oil scattering structure formed between an oil deflector and a bearing supporter on the rotor shaft in a circumferential direction to scatter bearing oil flowing from the bearing supporter toward the oil deflector along a surface of the rotor shaft.

An exhaust gas turbocharger may include a bearing housing and a rotor. The rotor may have a shaft mounted in the bearing housing via two radial bearing bushes. Each radial bearing bush may have an inner surface facing the shaft. The inner surface may have a single chamfer, where the single chamfers of the two radial bearing bushes face one another, or two chamfers, where one of the two chamfers for each of the two radial bearing bushes facing one another are larger than the other of the two chamfers for each of the two radial bearing bushes facing away from one another.

There is provided a seal assembly comprising: a first component and a second component spaced apart from the first component so as to define a passage for the transfer of fluid from an inlet of the seal assembly to an outlet of the seal assembly, wherein the first component comprises a concavity at least partially defining the passage, and wherein no part of the second component extends into the portion of the passage bounded by the concavity.

A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.