Experiments were run to investigate the feasibility of a flash vaporization system for aircraft gas turbine engines. The experiments consisted of a determination of boiling points, dew points, critical temperature, critical pressure, heat transfer coefficients, deposit formation rates, and deposit removal in a flowing system. Three fuels were included in the experiments including Jet-A, ERBS, and a premium No. 2 diesel fuel. Engine conditions representing the E3 at SLTO, cruise and idle were simulated in the vaporization system and it was found that single phase flow was maintained in the heat exchanger and downstream of the throttle. Deposits encountered in the heat exchanger represented a thermal resistance as high as 1.3 × 103 M2 K/watt and a deposit formation rate over 1000 gC/cm2 hr. It was found that the deposit can be removed by cleaning with air at a temperature of 720 K for 10 minutes.

This content is only available via PDF.