Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Abstract: A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. At least three of the following resonance frequencies are present. A first mode resonance frequency is 2591.5±10% Hz. A second mode resonance frequency is 4675.2±10% Hz. A third mode resonance frequency is 7892.9±10% Hz. A fourth mode resonance frequency is 10098.2±10% Hz. A fifth mode resonance frequency is 14808.2±10% Hz.

Abstract: A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

Abstract: A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. At least three of the following resonance frequencies are present. A first mode resonance frequency is 2591.5±10% Hz. A second mode resonance frequency is 4675.2±10% Hz. A third mode resonance frequency is 7892.9±10% Hz. A fourth mode resonance frequency is 10098.2±10% Hz. A fifth mode resonance frequency is 14808.2±10% Hz.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is loose within the cavity.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

Abstract: A gas turbine engine includes a fan rotatable about an axis, a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a fan drive turbine and a second turbine. The second turbine is disposed forward of the fan drive turbine. The fan drive turbine includes at least three rotors and at least one rotor having a bore radius (R) and a live rim radius (r), and a ratio of r/R is between about 2.00 and about 2.30. A speed change system is driven by the fan drive turbine for rotating the fan about the axis.

Abstract: A seal assembly for a gas turbine engine includes an annular body and a flow-through tube that extends through the annular body. The flow-through tube includes an upstream orifice, a downstream orifice and a tube body that extends between the upstream orifice and the downstream orifice. The tube body establishes a gradually increasing cross-sectional area between the downstream orifice and the upstream orifice.

Abstract: A support for an airfoil includes a trunk and a limb extending from the trunk for distribution within the airfoil.

Abstract: An airfoil attachment according to one example of this disclosure includes an airfoil and a disk supporting the airfoil. Further, there are primary contact surfaces and secondary contact surfaces between the airfoil and the disk. The secondary contact surfaces are not engaged during a normal operating condition.

Abstract: A support for an airfoil includes a trunk and a limb extending from the trunk for distribution within the airfoil.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is loose within the cavity.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

Abstract: A component blending tool assembly, includes a material removing surface that is moved to provide a blended area in a component, the material removing surface having a spherical contour mimicking a predetermined depth ratio of the blended area.

Abstract: A stator for a turbo-machine having a plurality of airfoils extending radially therefrom has a base from which the airfoils depend, and slits disposed in the base, each slit disposed adjacent a pair of airfoils, wherein a first set of adjacent slits and a distance between a second set of adjacent slits varies

Abstract: A rotor stack assembly for a gas turbine engine includes a first rotor assembly and a second rotor assembly axially downstream from the first rotor assembly. The first rotor assembly and the second rotor assembly include a rim, a bore and a web that extends between the rim and the bore. A tie shaft is positioned radially inward of the bores. The tie shaft maintains a compressive load on the first rotor assembly and the second rotor assembly. The compressive load is communicated through a first load path of the first rotor assembly and a second load path of the second rotor assembly. At least one of the first load path and the second load path is radially inboard of the rims.