| 摘要 |
PROBLEM TO BE SOLVED: To solve problems of a gas turbine helicopter engine in which a thickness of coating forming an acoustic attenuator occupies a significant volume to negatively affect a size of the engine, and a design change such that the engine, in particular, a metal casing thereof accommodates the acoustic attenuator is required. SOLUTION: In the gas turbine helicopter engine, lips 30, 32 defining a radial air intake 34 are connected along an opening 12a of an engine compressor air supply passage 12. The air intake lips are at least partially formed by sound attenuators 40, 42 calculated to attenuate sound frequencies produced by a compressor rotation. COPYRIGHT: (C)2008,JPO&INPIT
|
