... permanently changes consistent with the maximum temperature of exposure during the test. A laser-based instrumentation technique is then used to obtain temperatures. The maximum temperature profile of the surface can be determined through a customized calibration. Given the complex cooling system...

... turbine roughness additive manufacturing cooling heat transfer correlation computational fluid dynamics (CFD) heat transfer and film cooling In recent years, the interest in the application of additive manufacturing (AM) has increased exponentially. This technology allows significant...

... located in the test section of a low-speed wind tunnel. The vanes have the profile of high-pressure nozzle guide vanes, and the central vane is equipped with the internal cooling and the trailing-edge coolant ejection. The coolant is ejected through trailing-edge slots that are inclined in the span-wise...

...Weiguo Ai; Thomas H. Fletcher Numerical computations were conducted to simulate flash deposition experiments on gas turbine disk samples with internal impingement and film cooling using a computational fluid dynamics (CFD) code ( FLUENT ). The standard k- ω turbulence model and Reynolds-averaged...

...Weiguo Ai; Nathan Murray; Thomas H. Fletcher; Spencer Harding; Jeffrey P. Bons Particulate deposition experiments were performed in a turbine accelerated deposition facility to examine the nature of flyash deposits near film cooling holes. Deposition on both bare metal and thermal barrier coating...

...Weiguo Ai; Nathan Murray; Thomas H. Fletcher; Spencer Harding; Scott Lewis; Jeffrey P. Bons Deposition on film-cooled turbine components was studied in an accelerated test facility. The accelerated deposition facility seeds a natural-gas burning combustor with finely ground coal ash particulate...

... a little coolant reaches the pressure side in the aft part of the passage. However, at a blowing ratio of 1.5, there is a dramatic change in the flow structure. Both the oil-dot visualization and the cooling effectiveness maps indicate that at this blowing ratio, the coolant exiting the slot has sufficient...

...Filippo Coletti; Manfredi Scialanga; Tony Arts The present contribution is devoted to the experimental study of the conjugate heat transfer in a turbine blade cooling cavity located near the trailing edge. The cooling scheme is characterized by a trapezoidal cross-section, one rib-roughened wall...

...Christian Heneka; Achmed Schulz; Hans-Jörg Bauer; Andreas Heselhaus; Michael E. Crawford An experimental study on film cooling performance of laterally inclined diffuser shaped cooling holes is presented. The measurements have been conducted on a flat plate with coolant ejected from a plenum...

...Giovanna Barigozzi; Giuseppe Franchini; Antonio Perdichizzi; Silvia Ravelli The present paper investigates the effects of the application of trenched holes in the front part of a contoured film cooled endwall. Two trench configurations were tested, changing the trench depth. Tests have been carried...

...Valerio Lallini; Jan Janikovic; Pericles Pilidis; Riti Singh; Panagiotis Laskaridis A tool to evaluate the turbine cooling air schedule during the flight path is presented. The method is suitable for complex gas turbine engine models where accurate calculation of thermodynamic parameters...

...S. Naik; C. Georgakis; T. Hofer; D. Lengani This paper investigates the flow, heat transfer, and film cooling effectiveness of advanced high pressure turbine blade tips and endwalls. Two blade tip configurations have been studied, including a full rim squealer and a partial squealer with leading...

... over the pulsing duration is very small, suggesting a large thermal inertia that keeps the wall surface largely unaffected by the time scale of the pulsations; this holds true for both blowing ratios tested. 02 08 2010 10 08 2010 19 07 2011 19 07 2011 cooling film flow...

...R. M. Mathison; C. W. Haldeman; M. G. Dunn Heat-flux measurements are presented for a one-and-one-half stage high-pressure turbine operating at design-corrected conditions with modulated cooling flows in the presence of different inlet temperature profiles. Coolant is supplied from a heavily film...

...Florian Hoefler; Simon Schueren; Jens von Wolfersdorf; Shailendra Naik Heat transfer measurements of a confined impingement cooling configuration with ribs on the target surfaces are presented. The assembly consists of four nonperpendicular walls of which one holds two rows of staggered inclined...

...C. W. Haldeman; M. G. Dunn; R. M. Mathison A fully cooled transonic high-pressure turbine stage is utilized to investigate the combined effects of turbine stage cooling variation and vane inlet temperature profile on heat transfer to the blades with the stage operating at the proper design...

...C. W. Haldeman; M. G. Dunn; R. M. Mathison A fully cooled turbine stage is utilized to investigate the combined effects of turbine stage cooling variation and high-pressure turbine (HPT) vane inlet temperature profile on the aerodynamics and heat transfer of the turbine stage operating...

...Martin Elfert; Michael Schroll; Wolfgang Förster The flow field characteristics of a two-pass cooling system with an engine-similar layout have been investigated experimentally using the nonintrusive particle image velocimetry (PIV). It consists of a trapezoidal inlet duct, a nearly rectangular...

...Toshihiko Takahashi; Ken-ichi Funazaki; Hamidon Bin Salleh; Eiji Sakai; Kazunori Watanabe This paper describes the assessment of CFD simulations for the film cooling on the blade leading edge with circular cooling holes in order to contribute durability assessment of the turbine blades. Unsteady...

...Diganta P. Narzary; Kuo-Chun Liu; Akhilesh P. Rallabandi; Je-Chin Han Adiabatic film-cooling effectiveness is examined on a high-pressure turbine blade by varying three critical engine parameters, viz., coolant blowing ratio, coolant-to-mainstream density ratio, and freestream turbulence intensity...