Abstract
A dimensional analysis, of both the equations governing boundary-layer flow with heat transfer and of the steady and unsteady boundary conditions, demonstrates that twelve non-geometric, dimensionless parameters are required for the complete similarity of a three-dimensional, compressible, viscous flow with a freestream pressure gradient. A comparison of the principle operating parameters for a number of existing gas turbine test facilities, designed to model the aerodynamic and heat transfer conditions in real engines, suggests that full modeling of engine boundary-layer phenomena has not been achieved. A semi-empirical, boundary-layer analysis suggests that measured velocity boundary-layer profiles from adiabatic test facilities differ significantly with those from a gas turbine operating at engine gas to wall temperature ratios. Similarly, the analysis established the shape of the velocity boundary-layer to be dependent upon the specific-heat ratio.
Original language | English |
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Pages (from-to) | 8 |
Number of pages | 8 |
Journal | American Society of Mechanical Engineers (Paper) |
Publication status | Published - 1995 |
Event | Proceedings of the International Gas Turbine and Aeroengine Congress and Exposition - Houston, TX, USA Duration: 5 Jun 1995 → 8 Jun 1995 |