A nested lattice structure 29 for use in a damping system includes a first lattice structure 26 including: a first outer passage 30 including a hollow interior 45; a second outer passage 32 including a hollow interior; and an outer node 42 including a hollow interior and forming an intersection of the first outer passage 30 and the second outer passage 32. The nested lattice structure 29 includes a second lattice structure 28 nested within the hollow interior of the first lattice structure 26 including: a first inner passage 44; a second inner passage 46; and an inner node 50 forming an intersection of the first inner passage 44 and the second inner passage 46. Each of the first inner passage 44, the second inner passage 46 and the inner node 50 are nested within the respective first outer passage 30, the second outer passage 32 and the outer node 42.

The invention concerns a turbine exhaust casing (TEC) for a gas turbine engine in which portions of the inner surface of the casing against which exhaust gas flows are provided with recesses extending into the surfaces. The recesses are positioned proximate to the leading edges of struts which extend between an outer shroud and inner hub of the casing.

A grey water treatment system includes a first tank configured to receive grey water via a grey water supply conduit and that comprises an overflow, a second tank configured to store grey water, and at least one transfer conduit configured to at least transfer grey water between the first tank and the second tank. A control is configured to maintain a water level in said first tank sufficiently close to the overflow to allow floating contaminants to pass over the overflow. A method of treating grey water includes: receiving grey water in a first tank of a grey water treatment system; transferring grey water via at least one transfer conduit between the first tank and a second tank of said treatment system; and controlling a water level in said first tank sufficiently close to an overflow of said first tank to allow floating contaminants to pass over the overflow.

An air turbine starter having a housing, a turbine, a drive shaft, and at least one vane. The housing having an inlet, an outlet and a curvilinear flow path extending between the inlet and the outlet. The at last one vane is located within a portion of the curvilinear flow path, and includes an outer wall extending between a root and a tip in a span-wise direction and between a leading edge and a trailing edge in a chord-wise direction. In one aspect, the vane is arranged to define an acute axial angle that is non-constant in the chord-wise or span-wise direction. In another aspect, the vane is arranged to define an acute tangential angle that is non-constant in the chord-wise or span-wise direction.

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

A cooler fan module, having: a fan frame, a fan wheel recess formed in the fan frame, wherein the fan wheel recess is bounded by a frame ring, a motor mount, which is arranged within the fan wheel recess and is mechanically connected to the fan frame by means of struts, a motor, more particularly an electric motor, which is held at least partially in the motor mount, and a fan wheel, which is arranged in the fan wheel recess and is rotationally driven by the motor, wherein the cooler fan module further has a separately formed, annular structure element, which is arranged on the frame ring.

A turbine blade includes a blade body in which a suction side (51) facing one side in a circumferential direction and a pressure side (52) facing the other side in the circumferential direction are connected at a leading edge and a trailing edge; and a shroud provided at a tip which is a radially outer end portion of the blade body. The shroud includes a shroud body having an outer circumferential surface facing radially outward, a front end surface extending to both sides in the circumferential direction with a leading edge side of the blade body as a reference point (P1), a rear end surface extending to both sides in the circumferential direction with a trailing edge side of the blade body as a reference point (P2), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.

A method can comprise: performing a finite element static analysis of an inspected blade of an inspected bladed rotor, the inspected blade having a repair blend profile modeled thereon, the repair blend profile exceeding a threshold repair size; performing a finite element modal analysis of the inspected blade having the repair blend profile; performing a fatigue assessment based on results from the finite element static analysis and the finite element modal analysis, the fatigue assessment including limits based on material properties of the inspected blade, the material properties based on test results at a threshold significance level; and repairing the inspected bladed rotor with the repair blend profile in response to the fatigue assessment meeting a deterministic criteria.

A method of repairing an integrally bladed rotor (IBR) may comprise: performing a vibratory analysis of a rotor module including a first inspected IBR with a potential repair shape for the IBR; determining an undesirable vibratory characteristic of a second inspected IBR in the rotor module; iterating the potential repair shape for the first IBR to eliminate the undesirable vibratory characteristic of the second inspected IBR; and repairing the first IBR with a selected repair shape based on determining the potential repair shape eliminates the undesirable vibratory characteristic.

A turbine assembly can include a turbine housing that defines a longitudinal axis and that includes a first scroll and a first tongue at a first angle about the longitudinal axis and a second scroll and a second tongue at a second angle about the longitudinal axis, where an angular span between the first angle and the second angle is greater than 1 degree and less than 180 degrees; and a first set of vanes and a second set of vanes disposed in the turbine housing, where a vane of the first set of vanes is aligned with the first tongue and a vane of the second set of vanes is aligned with the second tongue.