Cooled turbine nozzle assembly and a method of calculating the d

Details Cooled turbine nozzle assembly and a method of calculating the d Cooled turbine nozzle assembly and a method of calculating the d

1994-03-03

1995-05-23

Look, Edward K.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

415116, 60 3932, 60757, F01D 904, F01D 906

Patent

active

054175453

ABSTRACT:
A turbine nozzle assembly includes an annular array of nozzle guide vanes located downstream of a combustor discharge casing. Each nozzle guide vane includes an aerofoil portion which is cast integrally with a radially inner platform and a radially outer platform. The radially outer platform of each nozzle guide vane has an extension to provide a smooth transition of the gases from the combustor discharge casing to the nozzle guide vanes. Two rows of cooling holes are provided in the extension to film cool the inner surface of the platform. A method is described to calculate the diameter of each of the cooling holes so that a uniform flow of cooling air passes over the inner surface of the each platform.

REFERENCES:
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patent: 4946346 (1990-08-01), Ito
2301 N.T.I.S. Tech Notes (Engineering) (1985) Jan., No. 1D, Springfield, Va., USA.
Walter Traupel, Thermische Turbomaschinen, Springer-Verlag Berlin Heidelberg New York 1977 and Tralslation No. G 3645--Walter Traupel.
Search Report Dated Jun. 16, 1994.

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