Turbine nozzle interface seal and methods
Number of patents in Portfolio can not be more than 2000
United States of America Patent
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-
Dec 26, 2000
Grant Date -
N/A
app pub date -
Jan 29, 1999
filing date -
Jan 29, 1999
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
An interface seal for a turbine engine including a rotor shroud hanger including at least one opening, an outer band including an aft rail, and a seal spring mounted in the opening and extending over an interface between the outer band and the shroud hanger, is described. The seal provides a barrier that prevents the leakage of high pressure cooling air through the interface into the combustion gas flowpath bypassing turbine engine components, and thus forces the high pressure cooling air through the necessary turbine engine components.
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