A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, or Table IX. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.

A fan blade of a gas turbine engine may include a blade body having an inner surface defining a cavity in the blade body. A blade filler may be disposed in the cavity. The blade filler may include a bump integrally formed on a first surface of the blade filler. An adhesive may be formed on the first surface of the blade filler. The first surface of the blade filler may be bonded to a fan blade component.

An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip.

A ceiling fan having a dual redundant motor mounting assembly for suspending a motor comprising a downrod, a hollow motor shaft suspending the motor from the downrod, a retaining pin extending through the hollow motor shaft, and a retaining rod coupled to the retainer pin for redundantly suspending the motor.

A turbine blade airfoil (25, 31R, 31M, 31T, 72) comprising an outer surface shape defined by Cartesian coordinates of successive transverse profiles at radial increments as set forth in Tables 1a to 1k, wherein each table defines a transverse sectional profile characterized by a smooth curve connecting the coordinates, and the surface shape comprises a smooth surface connecting the sectional profiles. The blade may include a tip shroud with edge profiles defined by Cartesian coordinates set forth in Table 2a and 2b. A gusset/fillet may be provided between the blade airfoil and the tip shroud, with a planar diagonal surface over most of a diagonal bracing area of the gusset/fillet.

A turbine blade is provided with at least one cooling channel and a plurality of cooling holes; each cooling hole being provided with an outlet section having an elongated shape along a principal axis; the height of the outlet section, intended as the measure of the maximum dimension of the outlet section along a direction parallel to the main axis, being equal to at least twice the width of the outlet section, intended as the maximum dimension of the outlet section along a direction orthogonal to the main axis.

A ceiling fan or similar air-moving device can include a motor for rotating one or more blades to drive a volume of air about a space. The blade can include a body having an outer surface with a flat top surface and a flat bottom surface, and a side edge. The top surface includes a chamfered portion extending between a flat portion, and the side edge.

A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858±10% Hz; a second mode resonance frequency is 4916±10% Hz; a third mode resonance frequency is 7160±10% Hz; a fourth mode resonance frequency is 10268±10% Hz; a fifth mode resonance frequency is 14235±10% Hz; and a sixth mode resonance frequency is 15088±10% Hz.

A propulsor for a gas turbine engine includes, among other things, a case including a duct disposed along an axis to define a flow path. A rotor includes a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path. A row of guide vanes are situated in the flow path. At least two of the guide vanes extend in the generally radial direction between inner and outer surfaces of the duct, extends in a chordwise direction between a first leading edge and a first trailing edge to define a vane chord dimension (VCD) at a first span position of the corresponding guide vane, and defines a vane circumferential pitch (VCP) at the first span position of the corresponding guide vane and an adjacent one of the guide vanes. The row of guide vanes has a vane solidity (VR) defined as VCD/VCP, the vane solidity (VR) being equal to or less than 1.43.