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Generalized Aerodynamic Modeling of Dynamic Wake Curvature for Open Rotors With Slender Blades

机译：细长叶片开放转子动态尾气曲率的广义空气动力学建模

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摘要

This paper elaborates on the theoretical development of an analytical approach, capable of modeling the effect of dynamic wake curvature on the aeroelastic response of open rotors with slender blades. The classical solution of incompressible, potential flow derived for a curved vortex tube of uniform vorticity strength is employed. The previously developed curved vortex tube analysis is mathematically generalized to account for arbitrary radial and circumferential variations of circulatory disk loading. An orthogonality analysis is carried out to obtain a finite set of inflow perturbation coefficients that describe the aerodynamic effect of wake curvature in a generalized manner. The end result is a set of integral expressions that provide the interharmonic coupling between the inflow perturbations on the rotor disk due to a curved trailing wake and the corresponding variations of disk loading. The obtained perturbation coefficients are subsequently superimposed upon an existing finite-state induced flow model that assumes a skewed, noncurved cylindrical wake. The developed mathematical approach for fluid mechanics is coupled with an unsteady blade element aerodynamics model, a rotor blade structural mechanics model, and a nonlinear rotor dynamics model. The combined formulation is implemented in an existing helicopter flight mechanics code. The overall method is initially employed to assess the effect of wake curvature on the dynamic response of a small-scale articulated rotor with a flap frequency ratio equal to unity. Subsequently, the integrated model is deployed to investigate the influence of wake curvature and inflow modeling fidelity on the predicted oscillatory blade loads and transient control response of a full-scale helicopter rotor. Comparisons are carried out with flight test measurements as well as with complex free-wake analysis methods. It is shown that including the effect of wake curvature is essential for predicting the transient control response of the investigated rotor. Good agreement is demonstrated between the proposed analytical model and nonlinear predictions carried out by resolving the complex wake geometry. The developed fluid mechanics formulation is a time-accurate method derived from first-principles and is applicable to both axial and nonaxial flow conditions.
机译：本文详细介绍了一种分析方法的理论发展，该方法能够模拟动态尾流曲率对带有细长叶片的开放式转子的气动弹性响应的影响。采用了具有均匀涡度强度的弯曲涡流管的不可压缩势流的经典解。先前开发的弯曲涡流管分析在数学上得到了概括，以解决循环盘载荷的任意径向和周向变化。进行正交性分析以获得有限的流入扰动系数集，这些流入扰动系数集以广义方式描述了尾流曲率的空气动力学效应。最终结果是一组整数表达式，这些表达式提供了由于弯曲尾随尾流而引起的转子盘上的流入扰动与盘负载的相应变化之间的谐波间耦合。随后，将获得的摄动系数叠加到现有的有限状态诱导流模型上，该模型假定了偏斜的，非弯曲的圆柱状尾流。为流体力学开发的数学方法与非定常叶片要素空气动力学模型，转子叶片结构力学模型和非线性转子动力学模型相结合。合并的公式在现有的直升机飞行力学规范中实现。最初采用整体方法来评估尾流曲率对襟翼频率比等于1的小规模铰接式转子的动态响应的影响。随后，使用集成模型来研究尾流曲率和入流建模保真度对全尺寸直升机旋翼的预期振荡叶片载荷和瞬态控制响应的影响。通过飞行测试测量以及复杂的自由苏醒分析方法进行比较。结果表明，包括尾流曲率的影响对于预测所研究转子的瞬态控制响应至关重要。通过解析复杂的尾流几何形状，所提出的分析模型与进行的非线性预测之间显示出良好的一致性。所开发的流体力学公式是一种基于第一原理的时间精确方法，适用于轴向和非轴向流动条件。

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  • 来源
    《Journal of turbomachinery》 |2016年第6期|061001.1-061001.16|共16页
  • 作者

    Ioannis Goulos;

  • 作者单位

    Propulsion Engineering Centre, School of Aerospace, Transport and Manufacturing, Cranfield University, Bedfordshire MK430AL, UK;

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