Gas-turbine engine for use as airplane engine, has cooling fins attached as series intermediate cooler on outer casing of high pressure compressor for cooling main air stream without removing main air stream from flow path

摘要

The engine (10) has a high pressure compressor (30), where cooling fins (33) are attached as a series intermediate cooler on an outer casing (34) of the high pressure compressor. The cooling fins cool main air stream (12) without removing the air stream from flow path. The cooling fins protrude into bypass air stream (11). The cooling fins exhibit flow resistance and heat transfer to guide vanes of a blade ring (31) of the high pressure compressor. A branched part of the bypass air stream is guided along the outer casing of the high pressure compressor.