Reliability Based Design Optimization of a Composite Airframe Component

Patnaik, Surya N.; Pai, Shantaram S.; Coroneos, Rula M.

doi:10.2514/6.2008-5879

Cited by 4 publications

(5 citation statements)

References 6 publications

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“…A sandwich construction for the blade is proposed for this fan blade with composite face sheets and a weak core made of honeycomb material, which is qualified to Boeing BMS 8-124 material specification [7]. The density of the honeycomb hexagonal cell is small, has weak in plane stiffness properties and acts as empty space to separate the face sheet and hence increase the bending stiffness without increasing weight.…”

Section: Formulation Of the Composite Blade Designmentioning

confidence: 99%

Structural Analysis and Optimization of a Composite Fan Blade for Future Aircraft Engine

Coroneos

2012

Int. J. Turbo Jet-Engines

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This paper addresses the structural analysis and optimization of a composite sandwich ply lay-up of a NASA baseline solid metallic fan blade comparable to a future Boeing 737 MAX aircraft engine. Sandwich construction with a polymer matrix composite face sheet and honeycomb aluminum core replaces the original baseline solid metallic fan model made of Titanium. The focus of this work is to design the sandwich composite blade with the optimum number of plies for the face sheet that will withstand the combined pressure and centrifugal loads while the constraints are satisfied and the baseline aerodynamic and geometric parameters are maintained. To satisfy the requirements a sandwich construction for the blade is proposed with composite face sheets and a weak core made of honeycomb aluminum material. For aerodynamic considerations, the thickness of the core is optimized where as the overall blade thickness is held fixed in order not to alter the original airfoil geometry. Weight reduction is taken as the objective function by varying the core thickness of the blade within specified upper and lower bounds. Constraints are imposed on radial displacement limitations and ply failure strength. From the optimum design, the minimum number of plies, which will not fail, is back-calculated. The ply lay-up of the blade is adjusted from the calculated number of plies and final structural analysis is performed. Analyses were carried out by utilizing the OpenMDAO Framework, developed at NASA Glenn Research Center combining optimization with structural assessment.

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Section: Formulation Of the Composite Blade Designmentioning

confidence: 99%

Structural Analysis and Optimization of a Composite Fan Blade for Future Aircraft Engine

Coroneos

2012

Int. J. Turbo Jet-Engines

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“…Many RSMs have been advanced such as Kriging surrogate model, 17 neural network model, 18,19 support vector machine model, [20][21][22][23] rough set model, 24 and stochastic RSM. 25 These RSMs have been studied continuously for structural reliability optimization design and perfectly employed in engineering, [26][27][28] which provides an enlightening insight for the MDAR design with MOMD.…”

Section: Mdar Optimization Featuresmentioning

confidence: 99%

“…Firstly, according to the computing method in Patnaik et al, 27 Andrea, 28 Fei and Bai, 29 Hu et al, 30 Fitzpatrick et al, 31 and Pugh et al, 32 the sensitivities and the probabilities of the original variables of the kth subject in the lth object impacting the SOSD output response Y (kl) should be calculated as shown in the following equation…”

Section: Mdar Probabilistic Analysis Based On Dcrsmmentioning

confidence: 99%

Study on the theory, method and model for mechanical dynamic assembly reliability optimization

Fei

Bai

2014

Proceedings of the Institution of Mechanical Engineers, Part C:

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To improve the performance and reliability of gas turbine like an aeroengine, the multi-object multi-discipline (MOMD) reliability optimization design of high press turbine (HPT) blade-tip radial running clearance (BTRRC) was first accomplished based on the mechanical dynamic assembly reliability (MDAR) theory and distributed collaborative response surface method (DCRSM). Four optimization models of MDAR were developed based on the features of assembly machinery and the thought of DCRSM, which are, respectively, called as the direct reliability optimization model (denoted by M1), the multilayer reliability optimization models (denoted by M2), the direct reliability optimization model-based probabilistic analysis (denoted by M3), and the multilayer reliability optimization model-based probabilistic analysis (denoted by M4). Through the MDAR optimization design of BTRRC by the four standard optimization models, some conclusions are drawn as follows: (1) the DCRSM is proved to be effective and feasible for MOMD MDAR optimization design with high computational efficiency and precision; (2) all the reliability optimization results of BTRRC and assembly objects satisfy the requirements of optimization design, and the optimized BTTRC variations are reduced by about 10% and obey the normal distribution, which are quite promising in improving the design and control of HPT BTRRC; (3) in computational efficiency, the computing time of M1 and M3 is far less than those of M2 and M4, meanwhile M3 and M4 are superior to M1 and M2; (4) in computational accuracy, M1 and M2 are better than M3 and M4, as well as M2 and M4 are higher than M1 and M3 theoretically. The presented study does not only fulfill the HPT BTRRC dynamic assembly design from a probabilistic optimization perspective and improve the performance and reliability of gas turbine engine, but also provides a promising approach and four valuable optimization models for MDAR optimization design. Besides, the present efforts are of great significance in enriching the theory and method of mechanical reliability design.

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“…Especially for aerospace equipment, the safety and reliability of mechanical system has become the weakest link in the whole product system. 10,11 Therefore, the reliability analysis of large and complex mechanical system has become the most important task in recent years. However, the reliability analysis of mechanical system is much more complex than that of the electronic system, which is mainly due to the multi-state failure of components in mechanical system.…”

Section: Introductionmentioning

confidence: 99%

An improved dynamic load-strength interference model for the reliability analysis of aero-engine rotor blade system

Zhao

Ren

Bai

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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As the power source of an aircraft, aero-engine tends to meet many rigorous requirements for high thrust-weight ratio and reliability with the continuous improvement of aero-engine performance. In this paper, based on the order statistics and stochastic process theory, an improved dynamic load-strength interference (LSI) model was proposed for the reliability analysis of aero-engine rotor blade system, with strength degradation and catastrophic failure involved. In presented model, the “unconventional active” characteristic of rotor blade system, changeable functioning relationships and system-component configurations, was fully considered, which is necessary for both theoretical analysis and engineering application. In addition, to reduce the computation cost, a simplified form of the improved LSI model was also built for convenience of engineering application. To verify the effectiveness of the improved model, reliability of turbojet 7 engine rotor blade system was calculated by the improved LSI model based on the results of static finite element analysis. Compared with the traditional LSI model, the result showed that there were significant differences between the calculation results of the two models, in which the improved model was more appropriate to the practical condition.

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Reliability Based Design Optimization of a Composite Airframe Component

Cited by 4 publications

References 6 publications

Structural Analysis and Optimization of a Composite Fan Blade for Future Aircraft Engine

Structural Analysis and Optimization of a Composite Fan Blade for Future Aircraft Engine

Study on the theory, method and model for mechanical dynamic assembly reliability optimization

An improved dynamic load-strength interference model for the reliability analysis of aero-engine rotor blade system

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