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RISElevated Mainstream Mach Number Effects on Shaped Gas Turbine Film Cooling Holes
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Abstract. Compressible flow fields associated with engine realistic high-speed conditions can have a significant impact on the performance of shaped film cooling holes in gas turbines. Such flow fields are dependent upon ...
Considerations for Compressible Film Cooling: A Computational Study of the Effects of Transonic Flows and Varying Mainstream Mach Number
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Recent evidence suggests that film cooling flows with engine-realistic mainstream Mach number have declined performance in comparison to those with conventional low-speed laboratory conditions. Consideration and understanding ...
Evaluation of Adjoint-Optimized Holes—Part I Baseline Performance
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: With the advent of the use of additive manufacturing to build gas turbine components, the design space for new hole geometries is essentially unlimited. Recently, a computational adjoint-based optimization method was used ...
Printability and Overall Cooling Performance of Additively Manufactured Holes With Inlet and Exit Rounding
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: To improve cooling effectiveness of gas turbine hardware, various film cooling hole shapes have previously been researched. Unique design modifications have recently been made possible through the design freedom allotted ...
Experimental and Computational Investigation of Integrated Internal and Film Cooling Designs Incorporating a Thermal Barrier Coating
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Few studies in the open literature have studied the effect of thermal barrier coatings (TBC) when used in combination with shaped hole film cooling and enhanced internal cooling techniques. The current study presents ...