Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.

Abstract: A diffuser case for a gas turbine engine including: a pre-diffuser; a diffuser case defining a dump region, an inner plenum, and an outer plenum, the pre-diffuser being fluidly connected to the inner plenum and the outer plenum through the dump region; a tangential onboard injector module fluidly connected to the inner plenum through inlet orifice located in the diffuser case proximate an aft end of the inner plenum; and an inlet extender initiating at the inlet orifice of the tangential onboard injector module, extends through the inner plenum, and terminates at a distal end proximate the pre-diffuser.

Abstract: An airfoil has a pressure side wall and a suction side wall circumferentially spaced apart from the pressure side wall. Each radially extends between a root region and a tip region, and each axially extends between a leading edge and a trailing edge. The airfoil also has a gusset, a squealer pocket, and a tip pocket. The gusset extends between the pressure side wall and the suction side wall. The squealer pocket is formed in the tip region and is disposed between the leading edge, the gusset, the pressure side wall, and the suction side wall. The tip pocket is formed in the tip region and is spaced apart from the squealer pocket. The tip pocket is disposed between the trailing edge, the gusset, the pressure side wall, and the suction side wall.

Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.

Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.

Abstract: A diffuser case for a gas turbine engine including: a pre-diffuser; a diffuser case defining a dump region, an inner shroud, and an outer shroud, the pre-diffuser being fluidly connected to the inner shroud and the outer shroud through the dump region; a tangential onboard injector module fluidly connected to the inner shroud through inlet orifice located in the diffuser case proximate an aft end of the inner shroud; and an inlet extender initiating at the inlet orifice of the tangential onboard injector module, extends through the inner shroud, and terminates at a distal end proximate the pre-diffuser.

Abstract: Components for gas turbine engines are provided. The components include a hot external wall that is exposed to hot gaspath air when installed within a gas turbine engine, and an interior impingement wall, wherein the interior impingement wall defines a feed cavity and at least one impingement cavity is defined between the impingement wall and the external wall. The impingement wall includes a plurality of impingement holes that fluidly connect the feed cavity to the at least one impingement cavity, the external wall includes a plurality of film holes that fluidly connect the at least one impingement cavity to an exterior surface of the external wall, and wherein the only source of cooling air within the at least one impingement cavity is the feed cavity.

Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.

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: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.

Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.

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 includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.

Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.

Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.