Turbine blade having auxiliary 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

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active

056953208

ABSTRACT:
A gas turbine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A plurality of longitudinally spaced apart primary turbulator ribs extend into the internal passage from at least one of the first and second sides. An auxiliary turbulator rib is spaced between adjacent ones of the primary ribs. The auxiliary rib has a height which is less than the height of the primary ribs for augmenting convective heat transfer enhancement with reduced pressure loss, and, therefore, reduced cooling air requirements.

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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.
S.D. Spring, "Improved Methods For Determining Heat Transfer," The Leading Edge, Winter 1987/1988, Contents page and pp. 4-9.
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Metzger-Fan-Yu, "Effects of Rib Angle and Orientation on Local Heat Transfer in Square Channels with Angled Roughness Ribs," Compact Heat Exchangers, copyright 1989, pp: Title and 151-167.

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