Patent ID: 11959397
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 10:
11. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor,
the turbine section having a turbine airfoil that includes
an airfoil section having an airfoil wall defining an arced leading end, a trailing end, and first and second sides joining the arced leading end and the trailing end, the first and second sides spanning in a longitudinal direction between first and second ends, the airfoil wall circumscribing an internal core cavity,
an arced rib in the internal core cavity, and
a cooling passage network embedded in the airfoil wall between inner and outer portions of the airfoil wall, the cooling passage network having a trailing edge and an arced leading edge, the arched leading end, the arced rib, and the arced leading edge of the cooling passage network being arced such that profiles of the arched leading end, the arced rib, and the arced leading edge when taken in a radial cross-section are arced, the cooling passage network including longitudinally-elongated passages, at least one of the longitudinally-elongated passages is a diverging-converging passage, the diverging-converging passage including a divergent section that spans from the first end of the airfoil wall to an intermediate span location of the airfoil section, and a convergent section that spans from the intermediate span location to the second end of the airfoil wall.