A gas turbine engine according to an example of the present disclosure includes a fan situated at an inlet of a bypass passage. The fan has a fan diameter, Dfan. A low pressure turbine section is configured to drive the fan and a first compressor section. The low pressure turbine section has a greater number of stages than the first compressor section. The low pressure turbine section has a maximum rotor diameter, Dturb. A ratio of the maximum rotor diameter Dturb divided by the fan diameter Dfan is less than 0.6.

A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.

A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.

A gas turbine engine article includes an article wall that defines a cavity, a cooling passage network embedded between inner and outer portions of the article wall, and at least one conical passage through at least a portion of the inner portion of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, an outlet orifice through the outer portion of the article wall, and an intermediate region of passages that connects the inlet orifice to the outlet orifice. The conical passage has a first end that is proximate the cavity and a second end that opens at the intermediate region of passages.

A coating membrane for a component of a gas-turbine engine includes a solid membrane having a metallic foil or a polymeric film, and having a thickness and at least one kerf extending through the thickness to define a kerf pattern such that the solid membrane can be applied to a compound-curved surface. Also disclosed are a coated component coated with the membrane, and a method for producing a coated component with the membrane.

The present application provides an acoustic nozzle for an inlet bleed heat system using a flow of compressor discharge air. The acoustic nozzle may include an outer casing with an upstream end and a downstream end, an acoustic attenuation medium within the outer casing, a number of exit apertures positioned in the outer casing about the upstream end thereof, an air pipe in communication with the outer casing, and an air chamber positioned within the outer casing about a downstream end thereof and in communication with the air pipe. The air chamber may include a reduced flow area for the flow of compressor discharge air.

A fluid system comprising a surface that is fluid washed in use by a fluid flow travelling substantially parallel to the surface is disclosed. The system has a first port through the surface and a second port through the surface, the first and second ports having respective first and second port inlets that are substantially flush with the fluid washed surface. The first and second port inlets are stacked in a direction parallel to the normal flow of fluid over the fluid washed surface such that the first port is upstream of the second port and fluid travelling closer to the fluid-washed surface entering into the first port tends to entrain fluid travelling further from the fluid-washed surface for entry into the second port.

An airfoil for a gas turbine engine defining a spanwise direction, a root end, a tip end, a leading edge end, and trailing edge end is provided. The airfoil includes: a body extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a sculpted leading edge member attached to the body positioned at the leading edge end of the airfoil, the sculped leading edge member formed at least in part of a metal material and defining a non-linear patterned leading edge of the airfoil.

A damping device for being situated between a housing wall of a housing of a thermal gas turbine and a casing ring is provided. The casing ring includes an area radially internal with regard to a rotation axis of a rotor of the thermal gas turbine and facing rotating moving blades of the gas turbine. The damping device includes at least sectionally a porous damping structure. A method for manufacturing this type of damping device as well as to a thermal gas turbine, in particular an aircraft engine, in which this type of damping device is situated in a housing of the gas turbine between a housing wall and a casing ring are also provided.

Aspects of the disclosure are directed to a brush seal comprising: a bristle pack that includes: a first plurality of bristles, each of the first plurality of bristles having a first dimension, and a second plurality of bristles, each of the second plurality of bristles having a second dimension that is different from the first dimension, where a ratio of the first dimension to the second dimension has a range of 2:1 to 5:1.