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 4.35-4.65 inch (110.5-118.1 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 2.45-2.75 inch (62.2-69.9 mm). The airfoil element includes at least two of a first mode with a frequency of 255±10% Hz, a second mode with a frequency of 818±10% Hz, a third mode with a frequency of 1439±10% Hz, a fourth mode with a frequency of 2035±10% Hz, a fifth mode with a frequency of 3033±10% Hz and a sixth mode with a frequency of 3740±10% Hz.

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 3.45-3.75 inch (87.6-95.3 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 1.55-1.85 inch (39.4-47.0 mm). The airfoil element includes at least two of a first mode with a frequency of 424±10% Hz, a second mode with a frequency of 1401±10% Hz, a third mode with a frequency of 1770±10% Hz, a fourth mode with a frequency of 3336±10% Hz, a fifth mode with a frequency of 3378±10% Hz and a sixth mode with a frequency of 4141±10% Hz.

Abstract: A rotor is provided for a gas turbine engine. The rotor includes a rim that extends transverse to the web. The rim has a rotor spacer arm which defines a coating pocket and a stress relief protrusion opposite the coating pocket.

Abstract: An integrally bladed rotor comprises a hub centered about an axis and having a plurality of blades extending radially outwardly of the axis across a span. Each of the blades includes an airfoil extending between a leading edge and a trailing edge, and having a pressure side and a suction side. The airfoil has a thicker portion at the trailing edge, and at a radially inner portion of the span, and over a limited percentage of the span, such that the thicker portion does not extend beyond 50 percent of the span. An axial distance is defined between the trailing edge and the leading edge. The thicker portion extends for less than 50 percent of the axial distance, and is on the pressure side. A gas turbine engine is also disclosed.

Abstract: A rotor is provided for a gas turbine engine. The rotor includes a rim that extends transverse to the web. The rim has a rotor spacer arm which defines a coating pocket and a stress relief protrusion opposite the coating pocket.