A rotor blade attached to a rotor shaft rotatable around an axis includes: a blade body extending in a radial direction with respect to the axis and having a blade-shaped cross section orthogonal to the radial direction; a shroud provided at an end of the blade body on a radial outer side, and a seal fin protruding from the shroud toward an outer circumferential side, and the seal fin includes: a seal fin body extending in a plate shape in a circumferential direction; and a reinforcing portion provided on at least one plate surface of the seal fin body to increase a thickness of the seal fin, the reinforcing portion gradually increasing in dimension in the radial direction toward the center in the circumferential direction.

A rotor disk for a gas turbine engine is disclosed. In various embodiments, the rotor disk includes a rim portion disposed about a central axis; a blade post disposed proximate the rim portion, the blade post having a first branch and a second branch; and a first scallop disposed within the rim portion, between and radially inward of the first branch and the second branch.

Baffles and airfoils for installation within gas turbine engines are provided. The baffles include a baffle side wall extending between a first end and a second end and a baffle divider within the baffle side wall, wherein the baffle divider and the baffle side wall define a first cavity and a second cavity. The first cavity is located at a first side at the first end and the second cavity is located at a second side at the first end and the baffle divider includes a spiral portion such that the first cavity is transitioned toward the second side and the second cavity is transitioned toward the first side.

A rotor disk for a gas turbine engine is disclosed. In various embodiments, the rotor disk includes a rim portion disposed about a central axis; a blade post disposed proximate the rim portion, the blade post having a first branch and a second branch; and a first scallop disposed within the rim portion, between and radially inward of the first branch and the second branch.

An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

There is disclosed wall cooling system 50 having a double-wall geometry. A first wall 55 and a second wall 60 extend over a plan area with the second wall spaced from the first wall by a gap. The first wall 55 has multiple upstanding members 65 spanning the gap and contacting the second wall 60 such that the first and second walls are mechanically and thermally connected. The first wall 55 is shaped so as to provide a two-dimensional array of crests 85 and recesses 90. The crests 85 are spaced from the second wall 60. The first wall 55 has a plurality of through-holes 70 for flow of coolant through the first wall and into the gap. The cooling system 50 is suitable for use in a gas turbine engine 10, for example in the turbine 17, 19.

An assembly for a turbine engine is provided. This turbine engine assembly includes a shell and a heat shield with a cooling cavity between the shell and the heat shield. The heat shield defines a plurality of cooling apertures and an indentation in a side of the heat shield opposite the cooling cavity. The cooling apertures are fluidly coupled with the cooling cavity. The indentation is configured such that cooling air, directed from a first of the cooling apertures, at least partially circulates against the side of the heat shield.

A pressure sensing device with a tubular pressure port including an internal chamfer adjacent to a deflectable diaphragm, and/or a hydrophobic or superhydrophobic coating applied to at least a portion of the tubular pressure port, the internal chamfer, and/or the deflectable diaphragm. The internal chamfer and/or the hydrophobic or superhydrophobic coating are configured at least in part to reduce adhesive forces between condensation and the surface of the tubular pressure port, to reduce the tendency for capillary action to draw condensation towards the deflectable diaphragm, and/or to increase the tendency for capillary action or gravity to draw condensation away from the deflectable diaphragm and out of the tubular pressure port.

An engine component assembly for impingement cooling. The engine component assembly includes an engine first component having a cooled surface. The engine first component having a flow path on one side of the cooled surface. A second component is a disposed adjacent to the engine first component between the flow path and the engine first component, and has a plurality of openings forming an array through the second component. The cooling flow path passes through the plurality of openings to cool the cooled surface. The second component having a surface facing the cooled surface of the engine first component. A plurality of discrete cooling features that have at least one wall that has a curved cross-section extend from the second component surface into a gap between and toward the cooled surface of the engine first component and defining an array.

A combustion engine component is disclosed. The combustion engine component comprises a body that includes a first surface in operative thermal communication with a hot combustion gas, and a second surface in operative fluid communication with a cooling fluid. Also, as disclosed in greater detail below, the second surface includes a first surface contour feature configured to increase a contact angle of a liquid on the second surface.