Abstract: A gas turbine engine case structure includes: a case wall having an inner surface and an outer surface; at least one fuel inlet; circumferentially-distributed fuel injectors protruding inward from the case wall and having an outlet; a fuel plenum fluidically between the at least one fuel inlet and the fuel injectors and configured so that each inlet of the at least one inlet is coupled to feed multiple of the fuel injectors; and a fuel inlet conduit fluidically between the fuel inlet and the fuel plenum. The inlet conduit has a forward inlet and is held spaced from the case wall at multiple longitudinally-spaced locations.

Abstract: A gas turbine engine case structure includes the unitary combination of: a case wall having an inner surface and an outer surface; at least one fuel inlet; circumferentially-distributed fuel injectors protruding inward from the case wall and having an outlet; a fuel plenum fluidically between the at least one fuel inlet and the fuel injectors and configured so that each inlet of the at least one inlet is coupled to feed multiple of the fuel injectors; and a fuel inlet conduit fluidically between the fuel inlet and the fuel plenum. The inlet conduit has a forward inlet and is held spaced from the case wall at multiple longitudinally-spaced locations.

Abstract: An apparatus is provided for a powerplant. The apparatus includes a heat pipe extending axially along an axis from a first end of the heat pipe to a second end of the heat pipe. The heat pipe extends circumferentially around the axis. The heat pipe includes an evaporator region, a condenser region and a plurality of fluid passages. The evaporator region is disposed at the second end of the heat pipe. The condenser region is disposed at the first end of the heat pipe. The condenser region is disposed radially inboard of the evaporator region. The fluid passages are axially between and fluidly couple the evaporator region and the condenser region.

Abstract: A fuel cooled aft bearing system including a main shaft supporting a compressor proximate a forward portion and a turbine proximate an aft portion; the main shaft comprising a shaft flow passage fluidly coupled with a fuel manifold proximate the aft portion and the shaft flow passage fluidly coupled with a combustor supply tube fluidly coupled with a combustor, the combustor in operative communication with the compressor and the turbine; an aft bearing supporting the main shaft proximate the aft portion; the aft bearing fluidly coupled with the fuel manifold of the main shaft; a strut in operative communication with the aft bearing, the strut comprising a strut flow passage fluidly coupled with the aft bearing; a vane in operative communication with the strut, the vane comprising a vane flow passage fluidly coupled with the strut flow passage; and a fuel supply fluidly coupled with the vane flow passage.

Abstract: An assembly is provided for a powerplant. This powerplant assembly includes an electric machine, a stationary structure and a fuel source. The electric machine includes an electric machine rotor. The electric machine rotor is configured to rotate about an axis. The stationary structure supports the electric machine and includes a heat exchange passage. The heat exchange passage spirals around the electric machine as the heat exchange passage extends within the stationary structure and axially along the electric machine. The fuel source is fluidly coupled to the heat exchange passage.

Abstract: An apparatus is provided for a powerplant. The apparatus includes a heat pipe extending axially along an axis from a first end of the heat pipe to a second end of the heat pipe. The heat pipe extends circumferentially around the axis. The heat pipe includes an evaporator region, a condenser region and a plurality of fluid passages. The evaporator region is disposed at the second end of the heat pipe. The condenser region is disposed at the first end of the heat pipe. The condenser region is disposed radially inboard of the evaporator region. The fluid passages are axially between and fluidly couple the evaporator region and the condenser region.

Abstract: A centralized multi engine startup system including a pallet structure; an energized gas source supported by the pallet structure; an umbilical gas line fluidly coupled to the energized gas source; and a vehicle in operative communication with the umbilical gas line, wherein each of the energized gas source and umbilical gas line are coupled to the pallet structure and remain with the pallet structure responsive to a vehicle launch from the pallet structure.

Abstract: A centralized multi engine startup system including a pallet structure; an energized gas source supported by the pallet structure; an umbilical gas line fluidly coupled to the energized gas source; and a vehicle in operative communication with the umbilical gas line, wherein each of the energized gas source and umbilical gas line are coupled to the pallet structure and remain with the pallet structure responsive to a vehicle launch from the pallet structure.

Abstract: A turbine vane for use in a gas turbine engine includes an airfoil section having a concave sidewall and a convex sidewall. Both the concave sidewall and convex sidewall extend spanwise between a platform and a radially outward airfoil tip and chordwise between a leading edge and a trailing edge. The concave sidewall includes a convex ablative region.

Abstract: A turbine vane for use in a gas turbine engine includes an airfoil section having a concave sidewall and a convex sidewall. Both the concave sidewall and convex sidewall extend spanwise between a platform and a radially outward airfoil tip and chordwise between a leading edge and a trailing edge. The concave sidewall includes a convex ablative region.