Impingement cooling for the shroud of a gas turbine

Details Impingement cooling for the shroud of a gas turbine Impingement cooling for the shroud of a gas turbine

1998-09-02

2000-10-03

Look, Edward K.

Rotary kinetic fluid motors or pumps

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

415117, 4151731, F01D 514

Patent

active

061263893

ABSTRACT:
An inner shroud 22 is coupled to an outer shroud 20 which receives cooling air through an inlet 54 for flow to the inner shroud. The inner shroud includes a wall 42 which defines in part the hot gas path 16 and a plurality of cavities 44 on an opposite side of the wall. The inner shroud includes a cover 40 having depending compartments 52 with apertures 56 through the floor of the compartments. When the cover overlies the inner shroud body, the compartments are received in the cavities and cooling air from the inlet flows into the compartments and through the apertures for impingement cooling of the inner shroud wall. Spent cooling air exits the inner shroud through passages 45 through circumferential and/or axial facing side walls of the inner shroud and/or the wall of the inner shroud defining the hot gas path.

REFERENCES:
patent: 4317646 (1982-03-01), Steel et al.
patent: 5350277 (1994-09-01), Jacala et al.
patent: 5391052 (1995-02-01), Correia et al.
patent: 5480281 (1996-01-01), Correia

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