... Abstract The film cooling performance on the pressure side of turbine blades with single-row film holes is experimentally investigated. Three blades with single-row film holes at three locations (x/S = 10%, 29%, and 48%) of the pressure-side are studied at three rotating Reynolds numbers of 3.6...

... term in the equation are compared quantitatively. Turbulent enthalpy transport is found to be in the same order of magnitude as the advection term associated with mean motion and thus is not negligible when considering the convective heat transfer problem of film cooling, which differs from...

... Abstract This study measures the film cooling effectiveness along the trailing edge of a turbine blade in a linear cascade. The film cooling effectiveness is measured and analyzed using the pressure sensitive paint (PSP) technique. Two different trailing edge designs are investigated including...

... Abstract Previous studies showed that the Reynolds-averaged Navier Stokes simulation (RANS) which used gradient diffusion hypothesis (GDH) severely under-predicts the scalar diffusion downstream the film cooling jet flow. Scalar flux models of different types have been developed throughout...

... Abstract Film cooling, as a key technology to ensure turbine survival in new generation gas turbines, has been studied profusely in subsonic flows. But in transonic flow, the determination of adiabatic cooling effectiveness faces a dilemma in the state of the art. Specifically, derivation...

... Abstract In a previous study from our laboratory, a computational adjoint based optimization method was used to design shaped film cooling holes fed by internal co-flow and cross-flow channels. The associated RANS computations predicted that the holes optimized for use with cross-flow (X-AOpt...

... Abstract Conjugate heat transfer (CHT) analyses were conducted to validate the accuracy of numerical method in the prediction of aerodynamic and thermal performance of the film cooled C3X vane. The effect of inlet preswirl on the film cooling performance of the vane surface was investigated...

... Abstract In this study, a shaped hole optimization approach based on Large Eddy Simulations and Efficient Global Optimization (EGO) is presented. The shape of a fan-shaped hole used for turbine film cooling is then optimized to maximize the film cooling performance and the numerical problem...

... Abstract Film cooling remains a critical technology for cooling gas turbine components. In recent years, additive manufacturing (AM) has been used to develop novel film cooling hole designs which significantly increase the film cooling effectiveness. However, engine scale AM builds have...

... Abstract Effusion film cooling is effective for cooling high temperature turbine blades because it requires less coolant and produces a more uniform temperature distribution than conventional film cooling. Effusion cooling for a cylindrical model representing the leading edge of a gas turbine...

... surface. In the early blade design phases, the designers must accurately determine the location, the pattern, the distribution density, the shape, and the size of cooling holes to maximize the blade film cooling whilst maintaining the external aerodynamics. Hundreds of simulation cycles may be needed...

... Abstract With increasing aerodynamic and thermal loads, film cooling has been a popular technology integrated into the design of the modern gas turbine vane endwall, especially for the first-stage vane endwall. A staggering amount of research has been completed to quantify the effect...

... Abstract The sweeping jet can be a promising candidate in film cooling applications since it has a large lateral jet spreading which can be considered an advantage when compared to the regular steady jet film cooling. Fluidic oscillators can generate a sweeping jet without the need for any...

... jets. Will they move synchronously with the fluid or asynchronously with a phase lag? How would the interaction between the droplets and the sweeping jets affect the film cooling effectiveness? To answer these questions, Part II of this paper specifically focuses on investigating the droplet dynamics...

... between the internal and film cooling flow of the turbine blade. magnetic resonance velocimetry gas turbine heat transfer internal cooling film cooling flow measurement Proceedings of ASME Turbo Expo 2022 Turbomachinery Technical Conference and Exposition GT2022 June 13-17, 2022, Rotterdam...

.... In other words, the first stage NGV’s lifespan is determined by the vane material’s durability. Therefore, effective cooling systems and thermal barrier coating (TBC) are provided. This paper presents a numerical prediction of the thermomechanical sensitivity of the first stage NGV with film cooling under...

.... As for the external cooling, film cooling technology has been widely used in the modern advanced design of gas turbines in order to enhance the cooling performance and reducing the cooling air usage. According to the public literature, conventional cylindrical film cooling hole has been studied by many researchers...

... 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 to design shaped film cooling holes fed by internal co-flow...

... Abstract The present study employed computational fluid dynamics (CFD) to explore the effect of the shape parameters of fan-shaped holes on film cooling effectiveness, and the optimum values and variation laws of each shape parameter to maximize the averaged film cooling effectiveness were...

... also indicated that there was generally a very good match in the Mach numbers and metal temperatures for all the turbine blades and vanes. gas turbine aerodynamics cooling heat transfer testing validation film cooling operation Proceedings of ASME Turbo Expo 2021 Turbomachinery...