Aerodynamics and Heat Transfer for
Modern Gas-Turbine Engines Workshop (AHTGTEW)
13 - 31 August 2012
Aerodynamics and Heat Transfer for modern gas-turbine engines consists of two parts: Internal Aerodynamics and Heat Transfer, offered concurrently in a 3-week period (42 hours lecture per part).
Part 1 provides a unified approach to internal aerodynamics that deals with fluid flow and thermodynamics of gas-turbine engine sub-systems – fans, propellers, compressors, turbines, inlets, and nozzles. Compressibility, rotational, viscous, turbulence, and other complicated effects will be dealt with where appropriate. The cycle analysis and performance of common modern aircraft engines – ramjet, turbo-jet, turbo-fan, turboprop, and turbo-shaft engines will be examined, including discussions on cycle innovation and new types of engines based on the lecturer’s research.
Part 2 deals with the important aspect that high-performance gas engines require high inlet temperature in excess of 1700oK, and more closely approaching 2000 oK, and progressively higher in the future, for high-performance engines. Not only new materials of construction are required on rotating blades that can withstand the thermal stress under the high temperature, they have to withstand also stresses induced from rotation/centrifugal and aerodynamic loading, therefore advanced cooling technologies are badly needed for the rotating turbine blades and the stationary vanes. After a review of the fundamentals on heat transfer (i.e. conduction, convection and radiation), the curriculum focuses on the physics and technologies of enhancing heat transfer in turbine blades and vanes. The advanced cooling technologies include, but not limited to,
convection, jet impingement, film cooling, and transpiration. Rotational, viscous, freestream turbulence, buoyancy, blade curvature effects will also be handled. Finally, experimental methods and numerical modeling will be discussed.