Methods and system for cooling integral turbine nozzle and...

Details Methods and system for cooling integral turbine nozzle and... Methods and system for cooling integral turbine nozzle and...

2006-11-30

2010-06-22

Nguyen, Ninh H (Department: 3745)

Rotary kinetic fluid motors or pumps

With diversely oriented inlet or additional inlet for...

C415S173100, C415S001000

Reexamination Certificate

active

07740442

ABSTRACT:
A method for cooling a shroud segment of a gas turbine engine includes providing a turbine shroud assembly including a shroud segment having a leading edge defining a forward face. A turbine nozzle is coupled to the turbine shroud assembly such that a gap is defined between an aft face of an outer band of the turbine nozzle and the forward face, wherein a lip formed on the aft face is positioned radially inwardly with respect to the gap and extends substantially axially downstream from the gap. Cooling air is directed into the gap. Cooling air exiting the gap impinges against the lip to facilitate film cooling the shroud segment.

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European search report, dated Feb. 10, 2010, from the European Patent Office for co-pending EP application No. 07117106 (6 pages).

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