Challenges in Predicting Rotor Blade Ice Protection Coverage Extent using Alternate Flow Solver and Lewice3D Bell Helicopter Textron

Format:

Conference/Event

Author/Creator:

Aubert, Aubert, author.

Contributor:

Wright, Jason

Conference Name:

SAE 2011 International Conference on Aircraft and Engine Icing and Ground Deicing (2011-06-13 : Chicago, Illinois, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 2011

Summary:

As the technology in rotor deicing matures, more programs arewilling to engage in the certification of their helicopters forflight into icing conditions. The S-92A helicopter, AW139, V-22,and EC225 aircraft have been certified/qualified recently and areillustrative examples of such engagement. The state-of-the-artconfiguration definition of rotor ice protection systems that havebeen introduced into the western rotorcraft manufacturer'sproduction line has been limited to electro-thermal deicingsystems. System configurations may use either chordwise or spanwiseshedding schemes and could differ in design and operation.Regardless of the selected design configuration, an analysis of therequired extent of protection coverage must be performed unless onehas access to data offering sufficient similitude in terms ofairfoil geometry and flight conditions. The analytical path may berequired to account for blade oscillation with continuouslychanging angles of attack through the entire azimuth, andcontinuously changing local velocities along the span of theblades, with local variation in the associated heat transfer andwater drop collection efficiency.While Lewice2D has been the code of choice for fixed-wingaircraft, its potential flow solver is quite limited when it comesto analyzing small-chord airfoils at high angles of attack and atlocal velocities approaching the speed of sound. Therefore, amethod has been explored which utilizes a more applicable flowsolver combined with the drop trajectory solver from the Lewice3Dcode. This combination has been selected as the best option interms of accuracy and run time. Because of its availability andlevel of familiarization within Bell Helicopter, the FENSAP flowsolver by Newmerical Technologies Incorporated (NTI) was selected.This paper presents the findings from the process used inestablishing the coverage extent on a representative and readilyavailable 206 helicopter tail rotor blade model. The model is to betested in the NASA Glenn Research Center Icing Research Tunnel insupport of the "High Fidelity Icing Analysis and Validationfor Rotors" project which is funded by Vertical LiftConsortium (VLC) members Bell Helicopter, The Boeing Company, andSikorsky Aircraft Corporation. Georgia Institute of Technology andNASA are active participants in the collaborative research effort,which is partially funded by the National Rotorcraft TechnologyCenter (NRTC)

Notes:

Vendor supplied data

Publisher Number:

2011-38-0097

Access Restriction:

Restricted for use by site license