Flow sleeve for a low NOx combustor

Power plants – Combustion products used as motive fluid – Having mounting or supporting structure

Reexamination Certificate

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Details

C060S752000

Reexamination Certificate

active

07082770

ABSTRACT:
A gas turbine combustor structure having improved cooling effectiveness and increased life as well as a method for improving the cooling effectiveness is disclosed. The gas turbine combustor incorporates a unique flow sleeve configuration for directing air to more effectively cool a combustion liner. The flow sleeve geometry is configured to incorporate a conical aft portion having a plurality of air feed holes that reduce pressure loss to the incoming air and flow separation effects from the surrounding combustor hardware, thereby resulting in improved combustor performance.

REFERENCES:
patent: 4872312 (1989-10-01), Iizuka et al.
patent: 5291732 (1994-03-01), Halila
patent: 5802854 (1998-09-01), Maeda et al.
patent: 6334310 (2002-01-01), Sutcu et al.
patent: 2004/0261419 (2004-12-01), McCaffrey et al.

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