Counterbalanced flow turbine nozzle

Rotary kinetic fluid motors or pumps – With passage in blade – vane – shaft or rotary distributor...

Reexamination Certificate

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Details

C415S191000

Reexamination Certificate

active

06929446

ABSTRACT:
A turbine nozzle includes hollow vanes extending between outer and inner bands. The vanes include a pattern of outlet holes distributed over the pressure and suction sides thereof for discharging cooling air collectively at a reference flowrate. The pattern of holes includes multiple rows of showerhead holes bridging the leading edge, and two rows of gill holes spaced aft therefrom along the suction side. A row of auxiliary holes is spaced aft from the showerhead holes through the pressure side, and the gill holes are sized to counterbalance the added discharge air through the auxiliary holes for maintaining the reference flowrate.

REFERENCES:
patent: 4616976 (1986-10-01), Lings et al.
patent: 4684323 (1987-08-01), Field
patent: 5356265 (1994-10-01), Kercher
patent: 5383766 (1995-01-01), Przirembel et al.
patent: 5538394 (1996-07-01), Inomata et al.
patent: 6168381 (2001-01-01), Reddy
patent: 6183198 (2001-02-01), Manning et al.
patent: 6270317 (2001-08-01), Manning et al.
patent: 6354797 (2002-03-01), Heyward
patent: 6428273 (2002-08-01), Keith et al.
patent: 6554563 (2003-04-01), Noe et al.
GE Aircraft Engines, CF6-50 Turbine Nozzle, five photos, on sale more than 1 year before Sep. 2003.
GE Aircraft Engines, CF6-80E Turbine Nozzle, two photos, on sale more than 1 year before Sep. 2003.

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