Blade cooling

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

Reexamination Certificate

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Details

C416S191000, C416S192000

Reexamination Certificate

active

07037075

ABSTRACT:
Turbine blades used in jet engines generally require cooling in order to achieve desired engine performance. Cooling of blade tip areas is difficult due to the limited space available such that thickening tip areas in order to allow passages and holes to be incorporated adds to weight and therefore stressing along with causing additional manufacturing costs. The present cooling arrangement includes coolant release passages5which present coolant flow to coolant entrainment elements or fins2such that the coolant flow is entrained close to the blade tip surface12. Thus, turbulent air flow caused by adjacent shrouds and edges are inhibited from diluting the coolant flow and therefore reducing thermal efficiency.

REFERENCES:
patent: 4390320 (1983-06-01), Eiswerth
patent: 5503529 (1996-04-01), Anselmi et al.
patent: 5531568 (1996-07-01), Broadhead
patent: 5695321 (1997-12-01), Kercher
patent: 5733102 (1998-03-01), Lee et al.
patent: 6672829 (2004-01-01), Cherry et al.
patent: 6790005 (2004-09-01), Lee et al.
patent: 58-47104 (1983-03-01), None

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