Design Optimization of Shielding Effect for Aircraft Engine Noise

Kazuhisa CHIBA; Taro IMAMURA; Kazuhisa AMEMIYA; Kazuomi YAMAMOTO

doi:10.1299/jee.2.567

Design Optimization of Shielding Effect for Aircraft Engine Noise

Journal of Environment and Engineering ◽

10.1299/jee.2.567 ◽

2007 ◽

Vol 2 (3) ◽

pp. 567-577 ◽

Cited By ~ 3

Author(s):

Kazuhisa CHIBA ◽

Taro IMAMURA ◽

Kazuhisa AMEMIYA ◽

Kazuomi YAMAMOTO

Keyword(s):

Design Optimization ◽

Aircraft Engine ◽

Shielding Effect ◽

Engine Noise

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5314 Design Exploration of Shielding Effect for Aircraft-Engine Noise

The proceedings of the JSME annual meeting ◽

10.1299/jsmemecjo.2006.7.0_281 ◽

2006 ◽

Vol 2006.7 (0) ◽

pp. 281-282

Author(s):

Kazuhisa CHIBA ◽

Taro IMAMURA ◽

Kazuomi YAMAMOTO

Keyword(s):

Aircraft Engine ◽

Shielding Effect ◽

Engine Noise ◽

Design Exploration

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Design Optimization of Aircraft Engine-Mount Systems

14th Biennial Conference on Mechanical Vibration and Noise: Vibration and Control of Mechanical Systems ◽

10.1115/detc1993-0227 ◽

1993 ◽

Author(s):

Hashem Ashrafiuon

Keyword(s):

Design Optimization ◽

Vibration Isolation ◽

Optimization Problems ◽

Three Dimensional ◽

Low Frequency ◽

Aircraft Engine ◽

Variable Metric ◽

Design Variables ◽

Engine Mount ◽

Optimization Search

Abstract Design optimization of aircraft engine-mount systems for vibration isolation is presented. The engine is modeled as a rigid body connected to a flexible base representing the nacelle. The base is modeled with mass and stiffness matrices and structural damping using finite element modeling. The mounts are modeled as three-dimensional springs with hysteresis damping. The objective is to select the stiffness coefficients and orientation angles of the individual mounts to minimize the transmitted forces from the engine to the base. Meanwhile, the mounts have to be stiff enough not allowing engine deflection to exceed its limits under static and low frequency loadings. It is shown that with an optimal system the transmitted forces may be reduced significantly particularly when mount orientation angles are also treated as design variables. The optimization problems are solved using a Constraint Variable Metric approach. The closed form derivatives of the engine vibrational amplitudes with respect to design variables are derived in order to achieve a more effective optimization search technique.

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