An engine component for a turbine engine comprising a wall defining an interior and having an outer surface over which flows the combustion airflow. The outer surface defining a first side and a second side extending between an upstream edge and a downstream edge and extending between a root and a tip. At least one cooling conduit provided in the interior and having conduit sidewalls; a set of cooling passages with at least one of the cooling passages in the set comprising: a first cooling passage portion having a surface outlet opening on the surface; a second cooling passage portion, intersecting the first cooling passage portion, and having an inlet fluidly coupled to the cooling conduit and an intermediate outlet fluidly connecting the second cooling passage portion to the first cooling passage at the intersection. The cooling passage comprising at least one fillet.

A system includes a combustor. The combustor has a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end. The combustor wall includes an inner wall portion and an outer wall portion defining an interior of the combustor therebetween. Each of the inner wall portion and outer wall portion extends from the combustor dome to the downstream end of the combustor wall. The combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion. The air cooling passage extends from the upstream end of the combustor wall to the downstream end of the combustor wall.

A hybrid three-layer system is presented. The hybrid three-layer system includes a two-layer composite system and an additively manufactured third layer comprising a lattice structure. The composite layer system includes a metallic substrate, a structured surface, and a thermal protection system. The structured surface may be additively manufactured onto the metallic substrate and includes structured surface features formed to project above the metallic substrate. Each of the structured surface features are separated from adjacent structured surface features by grooves. The thermal protection coating may be thermally sprayed onto the structured surface and is bonded to each of the structured surface features. The lattice structure is in contact with a surface of the metallic substrate of the composite layer system.

Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axially between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the trailing edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.

An endwall may be disposed at one end of a vane assembly. The endwall may comprise an endwall spar and a coversheet on the hot surface of the endwall spar. The endwall may further comprise a cooling fluid channel between the hot surface of the endwall spar and the cold surface of the coversheet. The cooling fluid channel may include a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The cooling fluid outlet may be formed at an angle with the axis of the endwall spar. A plurality of pedestals may be disposed on the hot surface of the endwall spar extending into the cooling channel. The pedestals may be formed at an angle with the axis of the endwall spar to direct a cooling fluid.

Devices for distributing oil from a rolling bearing for an aircraft turbine engine include a rolling bearing including two rings, respectively an inner ring and an outer ring, an oil distribution ring configured to be mounted on a turbine engine shaft, said distribution ring including a first outer cylindrical surface for mounting the inner ring of the bearing, an oil recovery scoop supplying a lubricating circuit of the bearing, and an annular track of a dynamic seal. The distribution ring and the track are formed by a single-piece body, and the lubricating circuit is formed in said body and extends into the distribution ring and the track.

In an embodiment, a method is provided. The method comprises extracting, from an image acquired with a first image-capture device, an image portion having dimensions of an extent of a second image-capture device. The method further comprises normalizing a parameter of the image portion. The method further comprises determining at least one edge of at least one object in the image portion; and generating, in response to the determined at least one edge, an edge map corresponding to the image portion.

A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first passage core. The first passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

A method of assembling a part is provided and includes forming a first section of the part, defining, in the first section, passages with dimensions as small as 0.005 inches (0.127 mm), forming a second section of the part, metallurgically bonding the first and second sections whereby the passages are delimited by the first and second sections and executing the metallurgically bonding without modifying a condition of the passages.

In an embodiment, a method is provided. The method comprises extracting, from an image acquired with a first image-capture device, an image portion having dimensions of an extent of a second image-capture device. The method further comprises normalizing a parameter of the image portion. The method further comprises determining at least one edge of at least one object in the image portion; and generating, in response to the determined at least one edge, an edge map corresponding to the image portion.