Abstract: An exemplary gas turbine engine includes a turbine section positioned about an engine central longitudinal axis. The turbine section includes a component with a platform providing a lip, a rail extending radially from the platform and at an axial location spaced from an outer axial extension of the lip. An inner face of the rail and a surface of the platform at least partially provide a cavity. At least one opening extends from the inner face to an outer face of the rail opposite the inner face to provide fluid communication from the cavity to the lip.

Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform includes a radially outer surface that is attached to the radially inner end of the airfoil. A radially inner side of the platform includes a forward surface and an aft surface. A pocket is recessed into at least one of the forward surface and the aft surface. A cover plate covers the pocket and a seal is attached to the cover plate.

Abstract: A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow, the internal passage including first and second passage sections coupled at a turn section. A baffle includes an elongated body arranged in the second passage section to define a pair of cooling flow paths respectively established along a pair of opposed walls of the elongated body such that the pair of cooling flow paths extend from the turn section along a common length of the second passage section, and a first wedge region extending from the elongated body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the pair of cooling flow paths.

Abstract: Components for gas turbine engines are provided. The components include a platform, a first airfoil extending from the platform, a first cavity located within the first airfoil, the first cavity includes a forward portion and an aft portion separated by a divider, a cover plate attached to the platform on a side opposite the airfoil, wherein a platform cavity is defined between the cover plate and the platform and wherein the first cavity is fluidly connected to the platform cavity through a first cavity inlet, and a first cavity separating rail dividing the platform cavity into a first platform forward cavity and a first platform aft cavity, wherein the first platform forward cavity is fluidly connected to the aft portion of the first cavity and the first platform aft cavity is fluidly connected to the forward portion of the first cavity.

Abstract: A combustor for a gas turbine engine includes a combustor shell having a shell opening therethrough, a combustor panel having a stud attached thereto, the stud extending through the shell opening. The stud includes a standoff to define an intermediate passage between the combustor shell and the combustor panel. A retainer is attached to the stud. A washer surrounds the stud and is positioned between the retainer and the combustor shell. The washer at least partially defines a cooling flow passage configured to direct a cooling airflow through the shell opening to impinge the cooling flow on at least one of the stud or the standoff.

Abstract: Airfoils, shells, and spars are provided. The airfoils include a shell having a first channel and a first engagement element arranged along the first channel and a spar having a second channel and a second engagement element arranged along the second channel and the spar defines an inner cavity. A connector is configured to be installed between and connect the shell and the spar to allow for thermal growth of the shell relative to the spar. The connector has first and second engageable portions connected by a link. The first engageable portion is configured to engage with the shell and the second engageable portion is configured to engage with the spar. When assembled, an outer cavity is formed between the spar and the shell, and the first and second engagement elements and the first and second engageable portions are configured to define an axial flow path through the outer cavity.

Abstract: A component for a gas turbine engine includes a wall portion that includes an interior surface and an exterior surface. At least one cooling circuit is defined by the wall portion and includes a plurality of pedestals that extend across the cooling circuit. A width of the cooling circuit increases or decreases in a downstream direction. At least one cooling fluid inlet extends through the interior surface and is in fluid communication with the cooling circuit. At least one cooling fluid outlet extends through the exterior surface and is in fluid communication with the cooling circuit.

Abstract: A component for a gas turbine engine includes a interleaved structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs. The second multiple of structural rib span segments that extend from the second sidewall, the first multiple of structural rib span segments interleaved with the second multiple of structural rib span segments to form an interleaved structural rib that extends between the first sidewall and the second sidewall.

Abstract: A component for a gas turbine engine. The component includes a first multiple of axial standoff ribs that extend from the first sidewall and a second multiple of axial standoff ribs that extend from the second sidewall. The structural rib that extends between the first multiple of axial standoff ribs and the second multiple of axial standoff ribs.

Abstract: Baffles for gas turbine engines are provided. The baffles include a baffle body extending between a first end and a second end, a chamfered surface formed at at least one corner of the baffle body, wherein the chamfered surface extends from the first end to the second end, and a plurality of baffle holes formed in the chamfered surface.

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a first platform section. The airfoil section defines an internal core cavity for conveying a fluid flow, and a baffle assembly that has a first baffle and a second baffle. The first baffle includes a first baffle body extending in the internal core cavity. The first baffle body defines an internal baffle cavity. The second baffle includes a second baffle body dimensioned to extend from the platform section into the internal baffle cavity such that an outer periphery surface of the second baffle body and an external wall of the airfoil section cooperate to define a first cooling passage that directs cooling flow into the internal baffle cavity.

Abstract: A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.

Abstract: A gas turbine engine component includes an airfoil defined by a leading edge, a trailing edge, a pressure sidewall, and a suction sidewall. An internal cavity extends radially through the airfoil and is partially defined by an inner surface of the pressure sidewall and an inner surface of the suction sidewall. A baffle is disposed within the internal cavity, and includes a baffle wall conformal with adjacent surfaces of the internal cavity, a divider separating a forward chamber and an aft chamber, and a plurality of orifices extending through the baffle wall at the forward chamber. At least one axial rib is disposed between the baffle wall and the internal cavity, and is positioned at a discrete spanwise location of the airfoil.

Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.

Abstract: An airfoil for a gas turbine engine includes axial flow and radial flow cooling circuits defined within an airfoil body. A baffle disposed in spaced relation to an inner surface of the airfoil has a plurality of impingement cooling holes configured to direct a cooling fluid at an inner surface of the airfoil body and an axial extent from the leading edge defined by an aft wall, with the axial extent being substantially constant between the inner and outer end walls and defined by a plane perpendicular to an engine axis. A first radially-extending rib is angled with respect to the baffle to define a first passage between the first rib and the baffle that tapers in cross-sectional area between the inner end wall and the outer end wall, becoming larger in cross-sectional area in a direction of cooling fluid flow through the first passage.

Abstract: A gas turbine engine component comprises a body having a leading edge and a trailing edge. At least one internal channel is formed within the body, wherein the channel includes an inlet to direct cooling flow into the body. At least one cast slot is formed in the trailing edge. At least one drilled filmhole is formed in the trailing edge, wherein the cast slot and drilled filmhole direct flow from the internal channel to an external location from the body. A gas turbine engine, a method of manufacturing a gas turbine engine component, and a method of controlling flow in a gas turbine engine component.