Optimisation of an air film cooled CFRP panel with an embedded vascular network

Research output: Contribution to journalArticle (Academic Journal)peer-review

8 Citations (Scopus)
352 Downloads (Pure)


The increasing use in the aerospace industry of strong, lightweight composite materials in primary structural components promises to substantially reduce aircraft non-pay-load weight, improving fuel consumption and operating profitability. This study explores the extension of composite material to regions of gas turbine engines previously considered too hot for composites with moderate melting points. Throughout the majority of a gas turbine cycle, gas stream temperatures exceed the polymer composite glass transition by a considerable margin. Boundary layer cooling strategies, however, may be adopted in the compression stages to extend the downstream distance that can be constructed using lightweight composites. This paper presents formulation and validation of a numerical model and its use in an optimisation study to develop a systematic process for thermal design of polymer composite structures in ‘warm’ gas streams. Internal vascular and external boundary layer film cooling strategies are considered.
Original languageEnglish
Pages (from-to)284-296
Number of pages13
JournalInternational Journal of Heat and Mass Transfer
Early online date14 May 2015
Publication statusPublished - Sep 2015

Bibliographical note

Date of Acceptance: 23/04/2015


  • Carbon fibre reinforced polymer
  • Film cooling
  • Microvascular
  • Thermal analysis


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