Bolting configuration for joining ceramic combustor liner to...

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

Reexamination Certificate

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C060S753000

Reexamination Certificate

active

07546743

ABSTRACT:
A gas turbine combustor includes a substantially cylindrical combustor liner located substantially concentrically within a flow sleeve, the combustor liner composed through a ceramic matrix composite material, a forward end of the combustor liner provided with a plurality of circumferentially arranged bolt holes. An inner metal ring is located about an outside surface of the forward end of the combustor liner, the inner metal ring provided with a second plurality of circumferentially spaced bolt holes, with a plurality of bolts extending through the first and second pluralities of bolt holes and secured by self-locking nuts. An outer metal ring is spaced radially outwardly of the inner metal ring, with a plurality of circumferentially spaced struts extending between the inner and outer rings.

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European Search Report for Application No. EP 06 25 4132 on Mar. 15, 2007, in Munich.
Partial European Search Report No. EP 06 25 4132 on Jan. 9, 2007, in Munich.

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