Heat Transfer in the Core Compressor Under Ice Crystal Icing Conditions

[+] Author and Article Information
Alexander Bucknell

University of Oxford, Oxford, UK

Matthew McGilvray

University of Oxford, Oxford, UK

David R.H. Gillespie

University of Oxford, Oxford, UK

Geoffrey B Jones

Rolls-Royce Plc, Derby, UK

Alasdair Reed

Rolls-Royce Plc, Derby, UK

Dr. David R Buttsworth

University of Southern Queensland, Toowoomba, AU

1Corresponding author.

ASME doi:10.1115/1.4038460 History: Received July 22, 2017; Revised September 13, 2017


It has been recognised in recent years that high altitude atmospheric ice crystals pose a threat to aircraft engines. It is believed that solid ice particles can accrete inside the core compressor, although the exact mechanism by which this occurs remains poorly understood. Development of analytical and empirical models of the ice crystal icing phenomenon is necessary for both future engine design and this-generation engine certification. A comprehensive model will require the integration of a number of aerodynamic, thermodynamic and mechanical components. This paper studies one such component, specifically the thermodynamic and mechanical processes experienced by ice particles impinging on a warm surface. Results are presented from an experimental campaign using a heated and instrumented flat plate. The plate was installed in the Altitude Icing Wind Tunnel (AIWT) at the National Research Council of Canada (NRC). The heated plate is designed to measure the heat flux from a surface at temperatures representative of the early core compressor, under varying convective and icing heat loads. Heat transfer enhancement was observed to rise approximately linearly with both total water content and particle diameter over the ranges tested. A Stokes number greater than unity proved to be a useful parameter in determining whether heat transfer enhancement would occur. A particle energy parameter was used to estimate the likelihood of fragmentation. Results showed that when particles were both ballistic and likely to fragment, heat transfer enhancement was independent of both Mach and Reynolds numbers over the ranges tested.

Rolls-Royce plc
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In