| 摘要 |
This invention relates to a method and an apparatus for the cooling of t he casing (1) of the turbines (2, 3) of jet engines, in which cooling air is diverted from a bypass flow and supplied to the outer side of the casing via an inlet duct (8) provided with a shut-off element (5). According to the present invention , the cooling air is supplied to a first chamber (6) in which it is divided by volume. One portion of the cooling air is issued to the casing (1) via orifice holes (10), while another portion is ducted via several tubes (9) to a second chamber (7 ) which annularly encloses the casing {1) in the area of a low-pressure turbin e (3).
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