Method and apparatus for the cooling of jet-engine turbine...

Details Method and apparatus for the cooling of jet-engine turbine... Method and apparatus for the cooling of jet-engine turbine...

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/12 (2006.01) B64D 33/08 (2006.01) F01D 11/24 (2006.01) F01D 25/14 (2006.01) F02C 7/18 (2006.01)

Patent

CA 2344128

This invention relates to a method and an apparatus for the cooling of the 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 turbine (3).

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