Numerical Simulation of Helicopter Blade Ice Shedding using a Bilinear Cohesive Zone Model

Chen, Yong; Fu, Liang

doi:10.4271/2015-01-2121

Cited by 3 publications

(2 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Ice may re-impinge on the tail rotor, fly into the engine, or strike the body of the rotorcraft. The shedding from helicopter blades has much in common with the shedding of ice in turbine engines [87][88][89] and on windmills [90][91][92]. As ice mass grows on blades, ice will typically shed in a rotating environment when the centrifugal force, which is proportional to ice mass, exceeds the adhesion forces which are proportional to contact area.…”

Section: Ice Shedding In a Rotating Environmentmentioning

confidence: 99%

The measurement of the adhesion of glaze ice.

Hardesty¹

View full text Add to dashboard Cite

Icing is a lethal and costly aviation hazard affecting aircraft of all sizes ranging from small UAVs to large commercial craft such as the Boeing 787, resulting in hundreds of deaths over the last century and resulting in billions of dollars of economic impact. Three predominant types of icing, namely, airframe icing, engine icing, and rotorcraft icing, dominate aircraft icing research. Each type poses unique challenges. In the case of rotor icing, attention needs to give to the rotating environment with large oscillatory loads and icing conditions. In the case of airframe icing, special attention needs to be paid to a variety of loading cases from the available options for de-icing and anti-icing equipment. In the case of engine icing, the formation mechanism is poorly understood and the structure of the ice needs to be studied in greater detail. Airframe icing requires However, all three share the same fundamental problem that ice sticks to surfaces. How strongly ice adheres to a surface dictates how hard it is to remove. The adhesion strength then regulates the primary threat from icing-the maximum aerodynamic penalty that accretion will have. It also dictates the threat of impingement from shed ice elsewhere on the aircraft, such that a piece of ice from the main rotor could strike the tail rotor on a helicopter, destroying it.

show abstract

Section: Ice Shedding In a Rotating Environmentmentioning

confidence: 99%

The measurement of the adhesion of glaze ice.

Hardesty¹

View full text Add to dashboard Cite

show abstract

“…Chen and Fu [4] developed an ice shedding model by taking into account the coupling of the failure of the interface between ice and rotor blade surface and the failure of ice itself. A bilinear cohesive zone model (CZM) was introduced to simulate the initiation and propagation of ice/blade interface crack and a maximum stress criterion was used to describe the failure occurred in the ice.…”

Section: Introductionmentioning

confidence: 99%

A novel method for robust and efficient prediction of ice shedding from rotorcraft blades

Rausa¹,

Morelli²,

Guardone³

2021

Journal of Computational and Applied Mathematics

View full text Add to dashboard Cite

The safety of rotorcraft operating in cold environments is jeopardised by the possibility of ice accretion on the rotor blades. Eventually, ice can shed from the blade due to the high centrifugal forces and impact other parts of the rotorcraft or unbalance the rotor. To establish the shedding time and location for rotorcraft, a robust and efficent numerical multi-step icing simulations tool is presented here for predicting the shedding phenomenon. A volume-mesh based approach is used to allow for representing the ice shape. In order to increase the robustness of the method, an interpolation procedure is implemented which establishes the possible occurrence of the shedding event and restricts the search domain. Ice shapes along the blades are computed by means of two-dimensional ice accretion simulations: ice shapes are then interpolated over the blade span. Numerical results compares fairly well, in terms of shedding time and location, to the experimental ones obtained in the AERTS test facility, thus demonstrating the soundness of the present approach.

show abstract