Aspirated High Pressure Compressor
Final technical rept. 1 May 2003-31 Aug 2005
MASSACHUSETTS INST OF TECH CAMBRIDGE DEPT OF AERONAUTICS AND ASTRONAUTICS
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The design and test of a two-stage, vaneless, aspirated counter-rotating fan is presented in this paper. The fan nominal design objectives were a pressure ratio of 31 and adiabatic efficiency of 87. A pressure ratio of 2.9 at 89 efficiency was measured in the tests. The configuration consists of a counter-swirl-producing inlet guide vane, followed by a high tip speed 1450 feetsec non-aspirated rotor, and a counter-rotating low speed 1150 feetsec aspirated rotor. The lower tip speed and lower solidity of the second rotor results in a blade loading above conventional limits, but enables a balance between the shock loss and viscous boundary layer loss, the latter of which can be controlled by aspiration. The aspiration slot on the second rotor suction surface extends from the hub up to 80 span, with a conventional tip clearance, and the bleed flow is discharged at the hub. The fan was tested in a short duration blow down facility. Particular attention was given to the design of the instrumentation to obtain efficiency measurements.
- Hydraulic and Pneumatic Equipment