A blade for the fan section of a turbine engine comprising a composite core defining a pressure side and a suction side extending axially between a core leading edge and a core trailing edge defining a chord-wise direction and extending radially between a core root and a core tip defining a span-wise direction and a leading edge strip made of materials with different elasticity and mounted to the core leading edge.

An airfoil 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 3.26-3.56 inch (82.9-90.5 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 1.25-1.55 inch (31.8-39.4 mm). The airfoil element includes at least two of a first mode with a frequency of 32310% Hz, a second mode with a frequency of 47610% Hz, a third mode with a frequency of 100510% Hz, a fourth mode with a frequency of 267010% Hz, a fifth mode with a frequency of 325510% Hz and a sixth mode with a frequency of 762810% Hz.

An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.

A rotating component includes an airfoil section with a free end, the airfoil section being formed of a composite core with a metallic skin and an abrasive coating applied to the free end.

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 2.59-2.89 inch (65.7-73.3 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 1.35-1.65 inch (34.4-42.0 mm). The airfoil element includes at least two of a first mode with a frequency of 224110% Hz, a second mode with a frequency of 359810% Hz and a third mode with a frequency of 621210% Hz.

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 2.59-2.89 inch (65.7-73.3 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 1.46-1.76 inch (37.1-44.7 mm). The airfoil element includes at least two of a first mode with a frequency of 70310% Hz, a second mode with a frequency of 357410% Hz, a third mode with a frequency of 810010% Hz, a fourth mode with a frequency of 945010% Hz, a fifth mode with a frequency of 1111610% Hz and a sixth mode with a frequency of 1162010% Hz.

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 27.5-28.5 inches (699-724 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 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 3410% Hz, a second mode with a frequency of 9010% Hz, a third mode with a frequency of 17810% Hz, a fourth mode with a frequency of 22210% Hz, a fifth mode with a frequency of 30710% Hz and a sixth mode with a frequency of 38910% Hz.

Integrally bladed rotors (IBRs) are described. The IBRs include a central hub, an outer rim defining an outer circumference of the central hub, the outer rim defining a plurality of platforms, a plurality of circumferentially distributed blades, wherein a blade extends from each of the plurality of platforms, a rotor slot arranged between two adjacent blades, wherein the rotor slot is defined by a cut within the outer rim, and a rotor slot insert installed within the rotor slot, the rotor slot insert sized and shaped to fit within the rotor slot and prevent air leakage from a first side of the central hub to a second side of the central hub through the rotor slot during operation of the integrally bladed rotor.

A bearing housing for connecting a bearing to a supporting structure of a gas turbine engine is discussed. The bearing housing has an inner wall and an outer wall radially spaced apart from the inner wall between which an annular space is defined. A device extends from the inner wall toward the outer wall and includes at least a first and a second member in series between the inner and outer walls, the second member having a radial stiffness greater than a radial stiffness of the first member. The device may operate in multiple operating stages, where in a first stage the first member of the device deforms to absorb at least partially a vibration load over a given range of vibration amplitude when the bearing housing deflects, and where in a subsequent second stage the second member of the device increases a total radial stiffness of the assembly of the bearing housing and device over the bearing housing alone.

A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention slots may extend from the first side to the second side of the metallic body. The first composite cover may be coupled to the first side of the metallic body and may include a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body. The second composite cover may be coupled to the second side of the metallic body and may include a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body.