An Investigation of the Aerodynamic and Vibration Behavior of a Helicopter Rotor Blade

Volume 4: Advances in Aerospace Technology ◽

10.1115/imece2020-23668 ◽

2020 ◽

Author(s):

Mohammad Khairul Habib Pulok ◽

Uttam K. Chakravarty

Keyword(s):

Rotor Blade ◽

Fluid Structure Interaction ◽

Interaction Model ◽

Scale Model ◽

Helicopter Rotor ◽

Small Scale ◽

Fluid Structure ◽

Structure Interaction ◽

Aerodynamic Analysis ◽

Helicopter Rotor Blade

Abstract Rotary-wing aircrafts are the best-suited option in many cases for its vertical take-off and landing capacity, especially in any congested area, where a fixed-wing aircraft cannot perform. Rotor aerodynamic loading is the major reason behind helicopter vibration, therefore, determining the aerodynamic loadings are important. Coupling among aerodynamics and structural dynamics is involved in rotor blade design where the unsteady aerodynamic analysis is also imperative. In this study, a Bo 105 helicopter rotor blade is considered for computational aerodynamic analysis. A fluid-structure interaction model of the rotor blade with surrounding air is considered where the finite element model of the blade is coupled with the computational fluid dynamics model of the surrounding air. Aerodynamic coefficients, velocity profiles, and pressure profiles are analyzed from the fluid-structure interaction model. The resonance frequencies and mode shapes are also obtained by the computational method. A small-scale model of the rotor blade is manufactured, and experimental analysis of similar contemplation is conducted for the validation of the numerical results. Wind tunnel and vibration testing arrangements are used for the experimental validation of the aerodynamic and vibration characteristics by the small-scale rotor blade. The computational results show that the aerodynamic properties of the rotor blade vary with the change of angle of attack and natural frequency changes with mode number.

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Structural Response Analysis of LNG CCS Experiencing the Sloshing Impact Determined by Both Convolution and Fluid Structure Interaction Method

Volume 2B: Structures, Safety and Reliability ◽

10.1115/omae2013-11336 ◽

2013 ◽

Cited By ~ 2

Author(s):

Se Yun Hwang ◽

Jang Hyun Lee ◽

Sung Chan Kim ◽

In Sik Nho ◽

Beom Seon Jang ◽

...

Keyword(s):

Structural Strength ◽

Fluid Structure Interaction ◽

Structural Response ◽

Computation Time ◽

Scale Model ◽

Small Scale ◽

Response Analysis ◽

Fluid Structure ◽

Structure Interaction ◽

History Of

Sloshing assessment of LNG cargo tanks is expected to satisfy the required structural strength of insulation components. It is difficult to estimate the sloshing pressure and structural response of cargo containment in real size because of the uncertainty of intensive computation time as well as the complexity of sloshing motion. In this study, several procedural components are suggested to meet the endurable strength of LNG CCS during the design of LNG cargo containment. The measured sloshing impacts from small scale model test are treated by individual impacts. Thereafter, static and transient structural response of LNG CCS is sequentially performed in order to evaluate the structural strength. The structural response is also calculated in time series through convolution method considering the history of pressure. It is used to investigate the structural response induced by the history of impacts. Finally, an idealized fluid structure interaction on the localized insulation panel is investigated in order to evaluate the structural strength in actual scale.

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Numerical Investigations of the Long Blade Performance Using RANS Solution and FEA Method Coupled With One-Way and Two-Way Fluid-Structure Interaction Models

Volume 2: I&C, Digital Controls, and Influence of Human Factors; Plant Construction Issues and Supply Chain Management; Plant Operations, Maintenance, Aging Management, Reliability and Performance; Renewable Energy Systems: Solar, Wind, Hydro and Geothermal; Risk Management, Safety and Cyber Security; Steam Turbine-Generators, Electric Generators, Transformers, Switchgear, and Electric BOP and Auxiliaries; Student Competition; Thermal Hydraulics and Computational Fluid Dynamics ◽

10.1115/power-icope2017-3100 ◽

2017 ◽

Cited By ~ 1

Author(s):

Minyan Yin ◽

Jun Li ◽

Liming Song ◽

Zhenping Feng

Keyword(s):

Rotor Blade ◽

Mechanical Performance ◽

Fluid Structure Interaction ◽

Interaction Model ◽

Leading Edge ◽

Von Mises Stress ◽

Maximum Displacement ◽

Fluid Structure ◽

Structure Interaction ◽

Von Mises

The aerodynamic and mechanical performance of the last stage was numerically investigated using three-dimensional Reynolds-Averaged Navier-Stokes (RANS) solution and Finite Element Analysis (FEA) coupled with the one-way and two-way fluid-structure interaction models in this work. The part-span damping snubber and tip damping shroud of the rotor blade and aerodynamic pressure on rotor blade mechanical performance was considered in the one-way model. The two-way fluid-structure interaction model coupled with the mesh deformation technology was conducted to analyze the aerodynamic and mechanical performance of the last stage rotor blade. One-way fluid-structure interaction model numerical results show that the location of nodal maximum displacement moves from leading edge of 85% blade span to the trailing edge of 85% blade span. The position of nodal maximum Von Mises stress is still located at the first tooth upper surface near the leading edge at the blade root of pressure side. The two-way fluid-structure interaction model results show that the variation of static pressure distribution on long blade surface is mostly concentrated at upper region, absolute outflow angle of long blade between the 40% span and 95% span reduces, the location of nodal maximum displacement appears at the trailing edge of 85% blade span. Furthermore, the position of nodal maximum Von Mises stress remains the same and the value decreases compared to the oneway fluid-structure model results.

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