Turbine blade having offset turbulators

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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416 96A, 415115, F01D 518

Patent

active

056811446

ABSTRACT:
A gas turbine engine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. Respective pluralities of first and second turbulator ribs extend inwardly from at least one of the first and second airfoil sides. Adjacent ones of second ends of the first and second ribs are staggered apart longitudinally and overlap chordally for defining a gap therebetween facing transversely for turning cooling air upon flow through the gap. The gap increases convective heat transfer enhancement for reducing cooling air requirements and improving blade creep life.

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J.C. Han et al, "Augmented Heat Transfer in Square Channels With Parallel, Crossed, and V-Shaped Angled Ribs," submitted to ASME Journal of Heat Transfer, Jun. 1990, pp. 1-23 and FIGS. 1-13.
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