| 摘要 |
PURPOSE: To avoid deficiency or local reductions in clearance between static shrouds and the ends of rotor blades caused by the bleeding of working fluid in an axial flow compressor having bleed apertures by improving its static structure including the inner and outer casings thereof. CONSTITUTION: The compressor part of a turbofan/gas turbine engine includes a rotor 38 to which rotor blades 40 are attached in stages, and a static structure constituted of an inner casing 42 and an outer casing 70. The inner casing 42 is made up of a plurality of mutually coupled annular casing parts 44, 46, 48 and 50, which carry annular channel members 51, 52, 54 and 56 having respective shroud structures 58, 60, 62 and 64. Between both those casings 42 and 70, an annular chamber 80 is defined into which the working fluid of a first predetermined pressure is supplied. The working fluid of a second predetermined pressure within the inner casing 42 is extracted out through a bleed duct 88. |
