Abstract: A bearing support is disclosed herein. The bearing support includes a pilot ring encircling an axis. The pilot ring is operable to be substantially-fixed in operation. The bearing support also includes a damper ring operable to receive an outer race of a bearing assembly. The bearing support also includes a fuse pin extending through aligned apertures in the pilot ring and the damper ring to prevent relative radial movement between the pilot ring and the damper ring up to a predetermined amount of loading. The fuse pin is operable to fracture in response to loading beyond the predetermined amount. The bearing support also includes a retainer extending through one of the pilot ring and the damper ring and fixed to the other of the pilot ring and the damper ring. The fuse pin is engaged with at least one of the first and second apertures through a heat shrink fit.

Abstract: A cooling fluid metering system for a turbine blade of a gas turbine engine is disclosed. The cooling fluid metering system may include a cooling channel positioned between a root of a turbine blade and an offset rotor sealing plate for supplying cooling fluids to turbine blades. At one point, a portion of the cooling channel may include a gap between the root and the offset rotor sealing plate. The gap may be sealed with teardrop shaped seal positioned within a teardrop shaped cavity at the gap. The cavity and seal may be positioned such that during operation, the seal is forced radially outward and into the gap, thereby effectively metering cooling fluid flow through the cooling channel.

Abstract: A turbofan engine comprising an annular inner wall surrounding tips of the fan blades, a layer of insulating material surrounding the inner wall, and an outer casing including an annular outer wall surrounding the insulating material and concentric to the inner wall and at least two annular rub elements extending radially inwardly from the outer wall through only part of a radial thickness of the layer of insulating material, at least two of the rub elements being in axial alignment with the blade tips at every point around a circumference of the fan, each rub element having a radially inner end spaced apart from the inner wall and made of a material harder than that of the blades, and a containment fabric layer wrapped around a support structure of the outer wall.

Abstract: A turbine rotor blade with an aft flowing 5-pass serpentine flow cooling circuit in which a first metering hole connect a first root turn formed between the second and third legs to a core support cavity and a second metering hole connects the core support cavity to a second root turn formed between the fourth and fifth legs so that cooling air from the second leg can be discharged directly into the fifth leg while bypassing the third and fourth legs. A seal pin can be secured within the core support cavity to block the bypass cooling flow.

Abstract: A wind turbine blade system that includes blades with an internal airflow path that extends within the blade from a location at the tip of the blade to a location near the base or root of the blade. A ram air turbine positioned inside each of the blades, along the airflow path, the ram air turbine being adapted for generate electricity, and thus the current output may then be connected to an electric load, so that air is ingested at the tip of the blade as each blade rotates.

Abstract: An annulus filler for mounting to a rotor disc of a gas turbine engine bridges the gap between adjacent disc blades. The annulus filler has a lid defining part of an airflow surface for air drawn through the engine; a separate support connectable to the lid and to the rotor disc with an engagement portion of the support extending radially past a substantially adjacent region of the lid; and a retainer configured to interconnect the lid and the support by engaging each engagement portion of the support and adjacent regions of the lid, the retainer defining another part of the airflow surface. The annulus filler can be configured to allow mounting to the rotor disc, where the support is connected to the rotor disc without the lid, and then the lid is mounted to the support such that each engagement portion remains visible from the lid's radially outermost side.