| CPC F02C 7/18 (2013.01) [F02C 7/22 (2013.01); F23R 3/40 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2240/36 (2013.01); F05D 2260/232 (2013.01); F05D 2300/11 (2013.01); F05D 2300/1432 (2013.01)] | 19 Claims |
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1. An assembly for a turbine engine with a flowpath, comprising:
a fuel source;
a turbine rotor comprising a plurality of turbine blades; and
a blade outer air seal forming a radial outer peripheral boundary of the flowpath, the blade outer air seal comprising a seal internal passage disposed radially outboard of the flowpath, the blade outer air seal configured to receive fuel from the fuel source, the blade outer air seal radially outboard of and extending axially along tips of the plurality of turbine blades, and the blade outer air seal configured to crack at least some of the fuel within the seal internal passage thereby cooling the blade outer air seal and providing at least partially cracked fuel;
wherein the assembly is configured to direct the at least partially cracked fuel into a stator vane internal passage of a stator vane upstream of the plurality of turbine blades and into the flowpath for combustion, and
wherein the stator vane internal passage includes a zigzag internal passage along a radial length of the stator vane.
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