Optimization, Design and Structural Testing of a High Deformable Adaptive Wing Leading Edge

2016 ◽  
Author(s):  
Anton Rudenko ◽  
Martin Radestock ◽  
Hans P. Monner
Keyword(s):  
Optimization Design ◽  
Leading Edge ◽  
Structural Testing ◽  
Adaptive Wing

Extremely deformable morphing leading edge: Optimization, design and structural testing

2017 ◽  
Vol 29 (5) ◽  
pp. 764-773 ◽  
Author(s):  
Anton Rudenko ◽  
André Hannig ◽  
Hans Peter Monner ◽  
Peter Horst
Keyword(s):  
Hybrid Composite ◽  
Optimization Design ◽  
Leading Edge ◽  
Future Generation ◽  
Structural Testing ◽  
High Lift ◽  
Optimization Framework ◽  
Element Simulation ◽  
Structural Tests ◽  
Kinematic Optimization

The future generation of high-lift devices needs to be improved to reduce the noise footprint and increase the performance for takeoff and landing of transport aircraft. To contribute to these goals, an active blown Coandă flap-based high-lift system is being investigated within the German national Collaborative Research Center 880 as an alternative to the state-of-the-art flaps. A key part of this system is an adaptive gapless droop nose with extremely large morphing deformation. The design and construction of this component are based on a structural optimization framework. The framework consists of two hierarchical design steps: an optimization of the hybrid composite skin layout with integral T-stringers, acting as joints to the inner actuation mechanism, and the kinematic optimization of the latter. A hybrid skin structure allows a large curvature to rupture in the morphing direction, while providing high stiffness in the transverse direction. This article describes a full-scale hybrid composite morphing droop nose and its structural tests. The results of these tests are finally compared to the finite element simulation and applied for validation of the optimization framework. A sensitivity analysis is provided to evaluate the influence of modelling and manufacturing uncertainties to the shape quality.

scholarly journals Effect of Tip Clearance on Helico-Axial Flow Pump Performance at Off-Design Case

Processes ◽  
2021 ◽  
Vol 9 (9) ◽  
pp. 1653
Author(s):  
Nengqi Kan ◽  
Zongku Liu ◽  
Guangtai Shi ◽  
Xiaobing Liu
Keyword(s):  
Optimization Design ◽  
Flow Characteristics ◽  
Axial Flow ◽  
Leading Edge ◽  
Tip Clearance ◽  
Hydraulic Loss ◽  
Tip Leakage Flow ◽  
Tip Leakage ◽  
Axial Flow Pump ◽  
Flow Pump

To reveal the effect of tip clearance on the flow behaviors and pressurization performance of a helico-axial flow pump, the standard k-ε turbulence model is employed to simulate the flow characteristics in the self-developed helico-axial flow pump. The pressure, streamlines and turbulent kinetic energy in a helico-axial flow pump are analyzed. Results show that the tip leakage flow (TLF) forms a tip-separation vortex (TSV) when it enters the tip clearance and forms a tip-leakage vortex (TLV) when it leaves the tip clearance. As the blade tip clearance increases, the TLV moves along the blade from the leading edge (LE) to trailing edge (TE). At the same time, the entrainment between the TLV and the main flow deteriorates the flow pattern in the pump and causes great hydraulic loss. In addition, the existence of tip clearance also increases the possibility of TLV cavitation and has a great effect on the pressurization performance of the helico-axial flow pump. The research results provide the theoretical basis for the structural optimization design of the helico-axial flow pump.

STRUCTURAL DESIGN AND NUMERICAL SIMULATION OF THE DIFFUSER FOR MAGLEV AXIAL BLOOD PUMP

2014 ◽  
Vol 14 (03) ◽  
pp. 1450045
Author(s):  
HUACHUN WU ◽  
GAO GONG ◽  
ZHIQIANG WANG ◽  
YEFA HU ◽  
CHUNSHENG SONG
Keyword(s):  
Optimization Design ◽  
Design Method ◽  
Leading Edge ◽  
Pressure Head ◽  
Hydraulic Performance ◽  
Blood Pump ◽  
Blade Angle ◽  
Blade Number ◽  
Blade Thickness ◽  
Blood Pumps

Hydraulic performance is an especially important factor for maglev axial blood pumps that have been used in patients with heart disease. Most maglev axial blood pumps basically consist of a straightener, an impeller and a diffuser. The diffuser plays a key role in the performance of the maglev axial blood pump to provide an adequate pressure head and increase the hydraulic efficiency. Maglev axial blood pumps with various structural diffusers exhibit different hydraulic performance. In this study, computational fluid dynamics (CFD) analysis was performed to quantify hydrodynamic in a maglev axial blood pump with a flow rate of 6 L/min against a pressure head of 100 mmHg to optimize the diffuser structure. First, we design the prototype of diffuser structure based on traditional design method, establish blood flow channel models using commercial software ANSYS FLUENT. Specifically, compare the performance of pump with the diffusers of different parameters, such as the leading edge blade angle, blade-thickness and blade-number. The results show that the diffuser structures with the thickening blade by arc airfoil law, blade-number of 6, leading edge blade angle of 24°, and trailing edge blade angle of 90° exhibited the best hydraulic performance which could be utilized in the optimization design of maglev axial blood pumps.

Multidisciplinary design optimization of adaptive wing leading edge

2013 ◽  
Vol 56 (7) ◽  
pp. 1790-1797 ◽  
Author(s):  
RuJie Sun ◽  
GuoPing Chen ◽  
Chen Zhou ◽  
LanWei Zhou ◽  
JinHui Jiang
Keyword(s):  
Design Optimization ◽  
Multidisciplinary Design Optimization ◽  
Leading Edge ◽  
Multidisciplinary Design ◽  
Adaptive Wing

scholarly journals Topology optimization of compliant adaptive wing leading edge with composite materials

2014 ◽  
Vol 27 (6) ◽  
pp. 1488-1494 ◽  
Author(s):  
Xinxing Tong ◽  
Wenjie Ge ◽  
Chao Sun ◽  
Xiaoyong Liu
Keyword(s):  
Topology Optimization ◽  
Composite Materials ◽  
Leading Edge ◽  
Adaptive Wing

Experimental and Numerical Study of Blade Profiles for Axial Flow Fans

1998 ◽  
Author(s):  
Veronique Henry
Keyword(s):  
Optimization Design ◽  
Numerical Study ◽  
Axial Flow ◽  
Leading Edge ◽  
Design Parameters ◽  
Blade Design ◽  
Aerodynamic Design ◽  
Design And Optimization ◽  
Expected Performance ◽  
Ventilation Fan

Abstract An experimental and numerical investigation is presented for blade profiles in axial flow fans. In order to improve the aerodynamic design of the blades, first numerical simulations with a two dimensional cascade oriented code have been performed in the rotor passage of a single-stage axial flow ventilation fan. The optimization design has been performed involving statistics. The influence of four design parameters have been investigated: rate of curvature, leading edge shape, chordwise location of the maximum camber and chordwise location of the maximum thickness. The new profile produced has been tested in wind-tunnel with a well-known C4 profile to validate the expected performance level. Next step has consisted in performing Navier-Stockes computations. Results demonstrate that the use of a coupled viscous-inviscid approach is appropriate for blade design and optimization. The Navier-Stockes code can be seen as a complementary tool as it leads to a complete description of the flow.

Optimization, design and testing for morphing leading edge

2020 ◽  
pp. 095440622094188
Author(s):  
Yu Yang ◽  
Zhigang Wang ◽  
Binwen Wang ◽  
Shuaishuai Lyu
Keyword(s):  
Optimization Design ◽  
Design Method ◽  
Leading Edge ◽  
Optimization Method ◽  
Collaborative Optimization ◽  
Noise Abatement ◽  
Deformation Control ◽  
Design Variables ◽  
Weight Penalty

Wing's morphing leading edge, drooping in a seamless way, has significant potential for noise abatement and drag reduction. Innovative design methods for compliant skin and internal actuating mechanism, respectively, are proposed and validated through a mockup in this paper. For the skin, a collaborative optimization method is presented, which takes all design variables, continuous and discrete, into account simultaneously. Moreover, to overcome the drawback of conventional algorithm, which is insufficient for deformation control in critical regime, weight penalty is imposed on present objective function. On the other hand, an internal kinematic actuating mechanism is designed from an improved concept, of which positions of level-rod hinges are optimized in a larger zone to fit the deflection requirement. The test of mockup validates the above methods, and excellent morphing quality of the compliant skin proves the advancement of the collaborative optimization method. However, the design method of internal actuating mechanism needs further improvement, and the error induced deteriorates the final morphing quality of the mockup.

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