| Citation: | TANG Fang-ming, YU Jia, LI Wei-wei, JI Lu-cheng. Blade shape optimization of multistage compressor using adjoint method with static pressure constraint at interfaces between rows[J]. Journal of Aerospace Power, 2015, 30(8): 1869-1874. doi: 10.13224/j.cnki.jasp.2015.08.010
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To solve the problem with the drift of operation condition during the optimization procedure when adjoint method applied in multistage compressor, based on the previous development work of multistage compressor blades optimization design using adjoint method and thin shear-layer N-S equations, the entropy production was selected as the objective function with given mass flow rate and total pressure ratio as imposed constraints, a new constraint was introduced, namely, the spanwise static pressure distribution at the interfaces between rows was imposed. Taking one 5 stage compressor as a test case, the new method was applied at inter-row interfaces behind the rotor and the stator of the first stage in environment of the first 1.5 stage and the whole 5 stage compressor. The results show that the drift problem of the operation condition during optimization procedure is resolved successfully by applying the constraint on spanwise static pressure distribution at the interfaces between rows and the efficiency of 5 stage compressor is got 0.4% improving.
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