| Budget Amount *help |
¥4,550,000 (Direct Cost: ¥3,500,000、Indirect Cost: ¥1,050,000)
Fiscal Year 2010: ¥780,000 (Direct Cost: ¥600,000、Indirect Cost: ¥180,000)
Fiscal Year 2009: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
Fiscal Year 2008: ¥2,340,000 (Direct Cost: ¥1,800,000、Indirect Cost: ¥540,000)
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| Research Abstract |
Experimental investigation on the unsteady cascade flow characteristics as well as global behavior of the compressor system under the compression plane wave injection from the compressor downstream were carried out by using an axial flow compressor test rig which connected the shock tube directly in series to its outlet. Rotor blades rushes into stall transitionally with the injection of a compression wave, and shows a complicated unsteady recovery process by the difference in an operating point. Even when the compression wave is injected at the time of compressor stable operation in which the gradient of the characteristic curve is negative, the compressor system may rush into unsteady phenomena such as rotating stall and surge. Moreover, some of the stall cells rotate within the rotor cascade according to a large-scale surge cycle, the rotating stall and surge are found to be related closely each other.
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