An investigation on an anti-ice static vane of a gas turbine engine

Tatar V., ARAS H.

APPLIED THERMAL ENGINEERING, vol.110, pp.1039-1050, 2017 (SCI-Expanded) identifier identifier

  • Publication Type: Article / Article
  • Volume: 110
  • Publication Date: 2017
  • Doi Number: 10.1016/j.applthermaleng.2016.09.022
  • Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus
  • Page Numbers: pp.1039-1050
  • Keywords: Anti-ice system of gas turbine engine, Icing, Heat transfer analysis, Flow visualization, HEAT-TRANSFER, AIRCRAFT, MODEL
  • Eskisehir Osmangazi University Affiliated: Yes


An anti-ice system is designed for front bearing structure to prevent ice accretion. This paper aims to evaluate effect of exit angle of discharge hole and break edge operation applied to the hole in terms of icing. Two discharge hole exit angle configurations were investigated throughout icing rig tests. The effects of sharp edge breaking over anti-ice jet flow were investigated via flow visualization tests in wind tunnel with Re of 45.000, 90.000, and 180.000. Four break edge configurations were studied; without break edge, 0.35 x D, 0.74 x D, 0.87 x D where D is diameter of the hole. Film effect on vane surface was monitored for each testing condition. As flow exit angle increases, ice accretes near trailing edge on pressure side because of that heat transfer from the jet flow to the surface decreases and air film cannot be maintained on the surface at the downstream of the hole. The results show noticeable effects of the break edge operation. As the break edge value increases, affected area by the air film decreases. The configuration without break edge provides more efficient air film compared to the others; thus it provides enhancement on the heat transfer between hot air flow and the cold surface. (C) 2016 Elsevier Ltd. All rights reserved.