Abstract: During operation, a bladed rotor disk typically experiences out-of-plane vibration which can result in deterioration and/or cracking at the interface between adjacent shrouds of the turbine blades. In an embodiment, slots are formed at the end of a labyrinth seal segment of each shroud. Preloaded spring strips are inserted through the slots to couple adjacent shrouds while preventing the natural frequency of the turbine blades from drifting to the operating speed range and/or providing vibration damping to the untuned blade mode.

Abstract: A thermal bridge forms a connection between a cold side and a hot side that is capable of withstanding a large temperature differential while high-pressure gas (e.g., air) flows between the two sides within an internal passageway. A cold-side region and hot-side region of the thermal bridge may each have a flange with a plurality of holes. The cold-side region may also include a conical fillet with counterbore recesses to provide access to each of the plurality of holes from a low radial position.

Abstract: A speed sensor assembly comprises: a driveshaft with a driveshaft axis, a sensing portion of the driveshaft having an axial bore along the driveshaft axis and multiple axial slots radially spaced around the sensing portion that penetrate through the driveshaft into the axial bore; and at least one electromagnetic sensor with a magnetic circuit proximate the sensing portion of the driveshaft; wherein rotation of the driveshaft causes the slots in the sensing portion to sequentially pass through the magnetic circuit of the electromagnetic sensor, thereby causing a change in the reluctance of its magnetic circuit that induces the electromagnetic sensor to generate an output signal that is representative of the rotational speed of the driveshaft.

Abstract: A speed sensor assembly comprises: a driveshaft with a driveshaft axis, a sensing portion of the driveshaft having an axial bore along the driveshaft axis and multiple axial slots radially spaced around the sensing portion that penetrate through the driveshaft into the axial bore; and at least one electromagnetic sensor with a magnetic circuit proximate the sensing portion of the driveshaft; wherein rotation of the driveshaft causes the slots in the sensing portion to sequentially pass through the magnetic circuit of the electromagnetic sensor, thereby causing a change in the reluctance of its magnetic circuit that induces the electromagnetic sensor to generate an output signal that is representative of the rotational speed of the driveshaft.

Abstract: An airfoil for a gas turbine engine component such as a turbine blade is tuned to move its natural frequency outside of a frequency which will be excited during expected speed range of an associated gas turbine engine. The airfoil is tuned about locations of the anti-nodes in an original airfoil design. The tuning affects only the interfered frequency.