Disclosed examples include a retrofit fan frame assembly, comprising: a leading edge adjustment component coupleable to an airfoil, the leading edge adjustment component of variable chord length, the variable chord length to increase and then decrease along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and an attachment mechanism configured to couple the leading edge adjustment component to a leading edge of the airfoil.

A stator vane 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, Table IX, Table X, Table XI, or Table XII. 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 component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces.

A housing of an axial fan that allows air to flow in an axial direction includes a frame including, on an inner surface, an air channel through which air flows, stator vanes extending radially inward from the inner surface, a motor housing supported radially inward of the stator vanes, and a motor supported on one axial side of the motor housing. A portion of the stator vanes is provided on a surface on the other axial side of the motor housing.

An airfoil for a gas turbine engine includes a pressure side and a suction side that extends in a radially outward direction from a 0% span position to a 100% span position. The airfoil has a stagger angle defined as an angle between an airfoil chord and a tangential plane normal to an engine longitudinal axis. The airfoil has a relationship between stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle at 100% span is greater than the stagger angle at 50% span.

An apparatus comprises a gas turbine engine having a compressor for increasing a total pressure of a working fluid prior to delivery to a combustor for mixing with fuel. The compressor has a plurality of airfoil members that extend between a first flow surface and a second flow surface. The plurality of airfoil members have a first camber shape at a tip portion that provides a cumulative integral according to the relationship $0.4<\frac{{\int }_0^1\left[{\int }_0^x{\beta }^{\prime }\mathrm{dx}\right]\mathrm{dx}}{{\int }_0^1{\beta }^{\prime }\mathrm{dx}}\le 0.5$
where x is chord location, ${\beta }^{\prime }=\frac{{\beta }_i-\beta }{{\beta }_i-{\beta }_e},$
β.sub.i is inlet metal angle, β.sub.e is exit metal angle, and β is a camber angle at a given chord location.

A fan assembly (10) includes a shrouded fan rotor (18) having a plurality of fan blades (22) extending from a rotor hub (24) and rotatable about a central axis (20) of the fan assembly, and a fan shroud (26) extending circumferentially around the fan rotor (18) and secured to an outer tip diameter of the plurality of fan blades (22). A fan casing (16) encloses the shrouded fan rotor (18). The fan casing (16) defines a fan inlet (30) of the fan assembly and includes an inlet extension (54) at an outer diameter of the fan casing, extending axially upstream of a conventional bell mouth inlet (58), relative to a direction of airflow through the shrouded fan rotor (18).

A part or an assembly of parts of a splitter stage of a turbofan, including a plurality of obstacles including at least one a blade and at least one arm, and a platform from which the obstacles extend, wherein the arm is defined by a skeleton angle having a trailing value on the trailing edge of between 3° and 15°.

A housing (17) of a fan (1) has an inflow-side end surface (2), an outflow-side end surface (16), and a wall ring (15). The wall ring 15 extends in a direction of an axis (12) from one of the end surfaces (2) to the other (16) and adjoins a fan passage. A fan wheel (10) is arranged in the fan passage. A grid (3) is arranged on the inflow-side end surface (2). The grid has a hub (8) positioned centrally in the fan passage. Primary struts (4) extend in the radial direction between the hub (8) and the edge of the fan passage. Secondary struts (6) intersect the primary struts (4).

A stator that has vanes extending between a first end and a second end along a span and from a leading edge to a trailing edge along a chord length, the vanes having a first end portion extending from the first end to about 30% of the span to a first location, a chord ratio of the chord length at the first end to the chord length at the first location greater than or equal to 1.1, a throat ratio of a width of a throat between two adjacent vanes at the first location to a width of the throat at the first end is greater than or equal to 1.3, a sweep angle difference between a maximum sweep angle of the leading edge along the first end portion and a minimum sweep angle of the leading edge along the first end portion is at least 15 degrees.