... are assembled with various weave patterns, but this uneven surface could introduce aerodynamic losses, and it will be necessary to determine the best film cooling hole arrangement for minimal thermal engine efficiency loss. As part of an effort to assess the impact of geometric constraints of CMC implementation...

... significantly improved composite cooling performance, especially the effusion hole. However, it should be noted that the incorporation of effusion hole also resulted in serious pressure loss of coolant. Keywords: Film Cooling; Impingement Cooling, Shaped Hole, Leading Edge, Conjugate Heat Transfer NOMENCLATURE...

... lift-off from component surfaces and are subsequently diluted due to mixing with the main flow. Recent advances in additive manufacturing (AM) technologies have enabled the fabrication of porous materials with precisely engineered lattice structures, significantly enhancing the film cooling...

... Abstract Adiabatic cooling effectiveness, as a primary indicator of film cooling performance, still suffers from the disputable measurement principle in transonic flow. The two measuring techniques in the state of the art, linear regression method and dual linear regression technique, produce...

.... However, the cooling effectiveness is greatly reduced when considering the swirling flow from the combustor. In the current work, against strong swirling inflow, a new solution to improve endwall film cooling performance through applying the slashface leakage with the double surface angle is carried out...

... Abstract Additive Manufacturing has been proving a very interesting potential to produce objects having both tiny dimensions and complex and twisted shapes. For this reason, in the last years, many efforts have been done to employ AM techniques to film cooling technique in the turbine blade...

... Abstract Based on the turbine blade model, the film cooling effectiveness data of single rows of holes at different positions were obtained through numerical simulation, and the superposition characteristics of multiple rows of holes under different average blowing ratios were studied...

... Abstract Film cooling effectiveness (FCE) is strongly influenced by film cooling hole geometry, mainstream boundary condition (boundary layer thickness and turbulence intensity), and coolant injection conditions (density ratio and blowing ratio). It is also shown that the flow structure...

... Abstract Prediction of film cooling performance on turbine airfoils with multiple rows of film cooling holes based on the measured performance of a single row of holes relies on use of superposition analysis. There have been many past studies of superposition predictions of film cooling...

... Abstract In recent studies, a turbine film cooling shaped hole designed by adjoint optimization techniques (X-AOpt) was found to substantially increase film cooling performance with 90% greater adiabatic effectiveness than a reference 7-7-7 shaped hole. Two aspects of the geometry contribute...

... Abstract Film cooling effectiveness and leakage flow play crucial roles in turbine blade heat transfer. In contrast to the conventional trailing edge cutback squealer blade tip (CB-tip), this study aims to compare the film cooling effectiveness of a suction side squealer tip (SS-tip) under...

... Abstract The instantaneous effect of unsteady wakes on film cooling effectiveness using a fast response pressure sensitive paint (PSP) was studied. Testing was performed in a five passage, low speed wind tunnel using five times scaled versions of typical high pressure blades (axial chord of 17...

... Abstract High fidelity and resolution of film cooling data on turbine blades can provide accurate and visually informative insights into physical phenomena, serving as valuable references for designers. However, due to the complexity of heat transfer problems and the limitations of data...

... Abstract Film cooling is an important cooling technique used in modern gas turbines and air engines. It is a typical jet-in-cross-flow problem, where the jet interacts with the mainstream, leading to complex vortex structures and turbulence properties. In this paper, the deviation between RANS...

... Abstract The numerical studies for film cooling performance have gained considerable interest for the development of advanced gas turbines and aero-engines. However, the accuracy of Reynolds-Averaged Navier-Stokes simulations is significantly influenced by the uncertainties associated...

... Abstract The present study numerically investigated the effect of typical leading edge structural parameters on the film cooling characteristics under rotating conditions. The studied parameters included the blade rotating speed (400rpm, 600rpm and 800rpm), the number of each row of film holes...

... Abstract Film cooling is essential for the proper functioning and desired operation of modern gas turbine engines. In this study, numerical investigations were performed to study the effects of forward and reversed hole configurations on the performance of sweeping jet film cooling...

... was used to model the film cooling flow injection at the vane surface without having to resolve each hole patch by the surface mesh itself. The paper presents a validation of the injection region model, and it compares the results of the different modelling approaches, including the hybrid 1D-3D model...

... Abstract Effectiveness of film cooling (η) has been characterized by the density (DR h ) and blowing (BR h ) ratios. In this study, a dimensional analysis and a computational study, based on steady RANS with and without conjugate heat transfer, were performed to identify and examine parameters...

... Abstract A recently proposed baseline shaped film cooling hole is numerically investigated on a flat plate at four blowing ratios (M), 0.5, 1.0, 2.0 and 3.0 and two density ratios (DR), 1.2 and 1.5. Results show that there exists an optimal blowing ratio and a best coolant operating condition...