...%. A detailed study about the effects of the close-coupled interface geometry on film cooling performance of the endwall and vane surfaces was conducted in parallel with this study and is presented in a separate two-part paper [ 27 , 28 ]. Current literature suggests that a minimum combustor coolant...

... of cooling channel, W ch 1 t Impingement distance, I 0.63 t Height of cooling channel, H ch 1 t Table 6 Heat transfer parameters with different film-hole diameters Parameters Film cooling hole diameter D f / t 0.1 0.2 0.3 0.4 0.5 Nu tar 71.57...

... the test section downstream of a combustor that generates burnt gases or by simply heating the incoming air [ 13 – 15 ]. Investigations of direct flame-film cooling interactions are of great importance with the advent of new concepts (downsizing, giratory combustor) but are scarce due to the improved level...

... and external cooling structures is very challenging and calls for non-intrusive, three-dimensional measuring techniques. As a response, this work utilizes magnetic resonance velocimetry (MRV) to measure the velocity field in a scaled turbine blade with engine-representative internal and film cooling structures...

...Mingyang Hao; Bo Bai; Yuanyuan Li; Zhigang Li; Jun Li 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...

...Haiteng Ma; Wei Zeng; Siming Dai; Hongmei Jiang 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...

...Chen Li; Baitao An; Jianjun Liu The coolant flow condition at the film hole entrance has a notable effect on film cooling effectiveness. The previous studies about internal ribbed crossflow effects are the hole with a circular inlet cross section. In this study, a diffusion slot hole with a race...

...Matthew J. Horner; Christopher Yoon; Michael Furgeson; Todd A. Oliver; David G. Bogard 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...

... for publication in the J ournal of T urbomachinery . 25 08 2021 01 02 2022 01 02 2022 04 03 2022 computational fluid dynamics (CFD) fluid dynamics and heat transfer phenomena in gas turbine combustors heat transfer film cooling effusion modeling reduced-order model As far...

... 2021 heat transfer film cooling turbine blade tip measurement advancements In high-pressure turbines (HPT), complex over-tip-leakage (OTL) flow occurs within the clearance gap between the rotor blade and the casing. Previous studies indicate that there are significant changes...

...Haifeng Xing; Lei Luo; Wei Du; Songtao Wang The direct prediction model for adiabatic film cooling effectiveness distribution and inverse prediction model for design parameters are studied in this article. Convolutional neural networks (CNNs) are trained on a set of simulated adiabatic film cooling...

... be increased by decreasing the lens aperture, this approach is impractical as a large aperture is essential to maintain an acceptable signal-to-noise ratio (SNR). To solve these problems in the optical aerothermal measurements of film-cooled gas turbine blades, an approach combining the focal-sweep method...

... t = total References [1] Bogard , D. G. , and Thole , K. A. , 2006 , “ Gas Turbine Film Cooling ,” J. Propul. Power , 22 ( 2 ), pp. 249 – 270 . 10.2514/1.18034 [2] Denton , J. D. , 1993 , “ Loss Mechanisms in Turbomachines ,” ASME J. Turbomach. , 115 ( 4...

... involves an engine-representative combustor–turbine interface geometry, combustor coolant flow, and endwall film cooling flow injected upstream of a linear cascade. The approach flow conditions represent flow exiting a cooled, low-NOx combustor. This first part of this two-part study aims to understand...

...Mahmood H. Alqefl; Kedar P. Nawathe; Pingting Chen; Rui Zhu; Yong W. Kim; Terrence W. Simon Flow over gas turbine endwalls is complex and highly three-dimensional. As boundaries for modern engine designs are pushed, this already-complex flow is affected by aggressive application of film cooling...

.... , and Metzger , D. E. , 1995 , “ Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models ,” ASME J. Turbomach. , 117 ( 1 ), pp. 12 – 21 . 10.1115/1.2835630 [4] Bunker , R. S. , 2001 , “ A Review of Turbine Blade Tip Heat Transfer ,” Ann. N. Y. Acad. Sci. , 934 ( 1 ), pp...

...Zhen Zhang; Hui Li; Xinrong Su; Xin Yuan The performance of film cooling is influenced by many parameters, and the nonuniform flow caused by the internal cooling system is found to largely affect the film cooling, which further complicates the in-hole flow and draws new difficulties in predicting...

... down facility consisting of five vanes was used. The film cooling effectiveness was measured using binary pressure-sensitive paint (BPSP). The mainstream flow was set using isentropic exit Mach numbers of 0.7 and 0.9. The coolant-to-mainstream density ratio varied from 1.0 to 2.0. The coolant...

...Zhiqiang Yu; Jianjun Liu; Chen Li; Baitao An; Guangyao Xu This paper focuses on the influences of the discrete-hole shape and layout on the blade endwall film cooling effectiveness. The effect of upstream purge slot injection on the film cooling performance of the discrete hole was also...

...Ziyu Chen; Yifei Li; Xinrong Su; Xin Yuan One-dimensional laterally averaged adiabatic film cooling effectiveness η ¯ l a t -based correlations have been widely employed in the cooling design of the modern gas turbine and aero-engine; however, the flow field of the discrete film cooling is fully...