TURBULATING COOLING STRUCTURES

摘要

In a first embodiment, a hollow gas turbine engine workpiece comprises first and second walls formed via additive manufacturing, and a cooling passage defined between the first and second walls by a surface of the first and second walls having arithmetic average surface roughness of at least 100 μin (0.0025 mm). In a second embodiment, a method of manufacture of a gas turbine engine component comprises depositing successive layers of pulverant material via additive manufacturing to form first and second walls defining a cooling passage therebetween, and loading a grain size of the pulverant material to produce lattice convective cooling design networks of various size and proportions with each having a range of relative roughness values, 0.10<ε/Dh<0.50 to achieve optimal thermal cooling performance along the cooling passage.

主权项

1. A hollow gas turbine engine workpiece comprising:
a first wall; a second wall; and a cooling passage defined between the first wall and the second wall by surfaces of the first and second walls having a relative roughness ε/Dh between 0.10 and 0.50.