Complementary cooled turbine nozzle

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

Reexamination Certificate

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C415S115000

Reexamination Certificate

active

06884036

ABSTRACT:
A turbine nozzle includes outer and inner bands integrally joined to a vane having a three-pass serpentine flow circuit between opposite pressure and suction sidewalls. The outer band includes an inlet for channeling cooling air into a first channel of the circuit located behind a leading edge of the vane. A first outlet is disposed in the inner band at the bottom of the first channel where it joins the second channel of the circuit. A second outlet is also disposed in the inner band at the bottom of a third channel of the circuit which is disposed in flow communication with the second channel. The first channel behind the leading edge is smooth except for corresponding rows of first and second turbulators spaced laterally apart. The first turbulators bridge the pressure and suction sidewalls directly behind the leading edge, and the second turbulators are disposed behind the suction sidewall.

REFERENCES:
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patent: 4416585 (1983-11-01), Abdel-Messeh
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patent: 6089826 (2000-07-01), Tomita et al.
patent: 6132169 (2000-10-01), Manning et al.
patent: 2112467 (1983-07-01), None
GE Aircraft Engines, “CF34-3B Stage 2 Nozzle,” in commercial use in U.S.A. before Mar. 2002.

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