Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.46-0.59 inch (11.8-14.9 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133±15% Hz, a second mode with a frequency of 8542±15% Hz, a third mode with a frequency of 15487±15% Hz, a fourth mode with a frequency of 18774±15% Hz, a fifth mode with a frequency of 24295±15% Hz and a sixth mode with a frequency of 27084±15% Hz.

Abstract: A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis.

Abstract: A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform. The ridge of the disk extends at least partially into the notch of the platform.

Abstract: A sealing system for a gas turbine engine includes an arcuate first ladder seal segment having a central portion, an upstream flange adjoining the central portion, a downstream flange adjoining the central portion opposite the upstream flange, and a plurality of openings. The upstream flange is arranged at an angle ?U greater than 0° and less than 90° relative to a given tangential plane, and the downstream flange is arranged at an angle ?D greater than 0° and less than 90° relative to the given tangential plane.

Abstract: A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis.

Abstract: A sealing system for a gas turbine engine includes an arcuate first ladder seal segment having a central portion, an upstream flange adjoining the central portion, a downstream flange adjoining the central portion opposite the upstream flange, and a plurality of openings. The upstream flange is arranged at an angle ?U greater than 0° and less than 90° relative to a given tangential plane, and the downstream flange is arranged at an angle ?D greater than 0° and less than 90° relative to the given tangential plane.

Abstract: A gas turbine engine system includes a disk and an airfoil. The disk includes a first rail, a second rail, a retention slot located between the first and second rails, and a ridge extending radially outward from the second rail. The airfoil is engaged with the retention slot, and includes a platform with an upstream angled portion, a downstream angled portion, and a notch defined in the platform. The ridge of the disk extends at least partially into the notch of the platform.