Cooled shroud of gas turbine stationary blade

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

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Details

415116, 416 96A, 416 96R, 416 97R, 416 97A, 416 90R, F01D 518

Patent

active

059972459

ABSTRACT:
The invention relates to a cooled shroud in a gas turbine stationary blade which is able to flow a cooling air in the entire area of an inner shroud for cooling thereof. Three stationary blades are fixed to the inner shroud 2, a cover 13, 14 is provided to form a space 21 and space 22a, 22b and 22c, respectively. The cooling air is introduced through an independent air passage 3A of a leading edge of each stationary blade into the spaces 22a, 22b and 22c and is flown therefrom through a tunnel 18 and air reservoirs 19-2, 19-3 and 19-4 to be blown out of a trailing edge while cooling surfaces of the shrouds and the trailing edges. Also, a portion of the cooling air from the space 22b is flown into the space 21 through a tunnel 11, a leading edge side passage 12 and an endmost tunnel 11 and is then blown out of the trailing edge through a tunnel 18 and an air reservoir 19-1, so that the leading edge portion, the endmost portion and the endmost trailing edge portion are cooled. By use of the independent air passage, the cooling air is introduced to cool the entire area of the shroud.

REFERENCES:
patent: 5344283 (1994-09-01), Magowan et al.
patent: 5413458 (1995-05-01), Calderbank
patent: 5848876 (1998-12-01), Tomita

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