CPC F01D 25/12 (2013.01) [F01D 5/18 (2013.01); F01D 5/181 (2013.01); F01D 5/185 (2013.01); F01D 9/041 (2013.01); F01D 25/08 (2013.01); F01D 25/10 (2013.01); F01D 25/14 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2260/205 (2013.01); F05D 2260/207 (2013.01); F05D 2260/213 (2013.01)] | 10 Claims |
1. An integral cooling system for a turbine casing and guide vanes in an aeroengine, wherein an inner guide ring (2) and a plurality of guide vanes (3) are mounted on the turbine casing (1);
the cooling system comprises a heat exchanger (5), an electromagnetic pump (51), an expansion joint (52) and a cooling pipeline (6);
an annular cavity (13) is provided in the turbine casing (1), the cooling pipeline (6) is mounted on an inner wall of the annular cavity (13) and periodically and uniformly distributed along a circumferential direction of the turbine casing (1), and the cooling pipeline (6) is filled with cooling liquid;
a mounting cavity (14) is further provided in the turbine casing (1), and the mounting cavity (14) communicates with the annular cavity (13); the heat exchanger (5), the electromagnetic pump (51) and the expansion joint (52) are all mounted in the mounting cavity (14), and one of connecting ports of the electromagnetic pump (51) communicates with the cooling pipeline (6); and
one end of the expansion joint (52) communicates with another of the connecting ports of the electromagnetic pump (51), another end of the expansion joint (52) communicates with one of connecting ports of the heat exchanger (5), and another of the connecting ports of the heat exchanger (5) communicates with the cooling pipeline (6).
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