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Measurements Of Adiabatic Effectiveness From Full Coverage Film Cooling On A Scaled Turbine Vane With Laidback Fanshaped Holes
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Book Synopsis Measurements of Adiabatic Effectiveness from Full Coverage Film Cooling on a Scaled Turbine Vane with Laidback Fanshaped Holes by : Owen Michael O'Neal
Download or read book Measurements of Adiabatic Effectiveness from Full Coverage Film Cooling on a Scaled Turbine Vane with Laidback Fanshaped Holes written by Owen Michael O'Neal and published by . This book was released on 2017 with total page 206 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study was focused on measurements of adiabatic effectiveness on a scaled turbine vane which made use of a contoured endwall to match engine conditions. The vane model featured a full coverage film-cooling configuration with five rows of cylindrical holes in the showerhead and ten rows of laidback fanshaped holes distributed on the pressure and suction sides. The vane model was tested across a wide range of blowing ratios in several different coolant configurations including: individual rows on the pressure and suction side, full coverage tests with and without showerhead cooling, and full coverage tests at low and high mainstream turbulence levels. Comparisons between these configurations were made in order to assess the effects of local curvature, showerhead cooling, and mainstream turbulence levels. Single row tests measured in areas of high convex curvature tended to have an improved performance relative to flat plate predictions, while the opposite was true for rows in areas of concave curvature. Overall, showerhead cooling did not provide any significant improvements in effectiveness far downstream on both the pressure and suction side. Increasing mainstream turbulence levels tended to diminish the film cooling effectiveness. The negative effect of higher mainstream turbulence was most significant at low blowing ratios, but became negligible at higher flow rates.
Book Synopsis Adiabatic Wall Effectiveness Measurements of Film-cooling Holes with Expanded Exits by : M. Gritsch
Download or read book Adiabatic Wall Effectiveness Measurements of Film-cooling Holes with Expanded Exits written by M. Gritsch and published by . This book was released on 1997 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Orlando, FL, Jun 2-Jun 5, 1997.
Book Synopsis Adiabatic effectiveness for full coverage film cooling with normal holes on a flat plate by : Mark Kenneth Harrington
Download or read book Adiabatic effectiveness for full coverage film cooling with normal holes on a flat plate written by Mark Kenneth Harrington and published by . This book was released on 2000 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Convex Curvature on Adiabatic Effectiveness for a Film Cooled Turbine Vane by : James R. Winka
Download or read book Effects of Convex Curvature on Adiabatic Effectiveness for a Film Cooled Turbine Vane written by James R. Winka and published by . This book was released on 2013 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of experiments were carried out to measure the effects of convex surface curvature on film cooling. In the first series of experiments cooling holes were positioned along the vane such that their non-dimensional curvature parameter, 2r/d, was matched. Single row of holes with the same diameter were placed at high and moderate curvature position along a turbine vane resulting in 2r/d = 28 and 40, accordingly. A third row of holes was installed on the vane at the same location as the moderate curvature row with a larger hole diameter, resulting in 2r/d = 28, matching the high curvature row. Adiabatic temperature measurements were then carried out for blowing ratios of M = 0.30 to 1.60 tested at a density ratio of DR = 1.20. The results indicated that there was some scaling of performance present with matching 2r/d, but there was not an exact matching of performance. The second series of experiments focused on the effects of a changing surface curvature downstream of injection. Two row of holes were positioned along the vane surface such that the local radius of curvature and hole diameters were equivalent, with one row positioned upstream of the maximum curvature point and the other downstream of the maximum curvature point. Adiabatic temperature measurements were carried out for blowing ratios of M = 0.30 to 1.60 and tested at a density ratio of DR = 1.20. The results show that the change in curvature downstream plays a significant role in the performance of film cooling and that the local surface curvature is insufficient in capturing its effects. Additional experiments were carried out to measure the effects of the approaching boundary layer influence on film cooling as well as the effect of injection angle at a weakly convex surface.
Book Synopsis Gas Turbine Heat Transfer and Cooling Technology, Second Edition by : Je-Chin Han
Download or read book Gas Turbine Heat Transfer and Cooling Technology, Second Edition written by Je-Chin Han and published by CRC Press. This book was released on 2012-11-27 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive reference for engineers and researchers, Gas Turbine Heat Transfer and Cooling Technology, Second Edition has been completely revised and updated to reflect advances in the field made during the past ten years. The second edition retains the format that made the first edition so popular and adds new information mainly based on selected published papers in the open literature. See What’s New in the Second Edition: State-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling Modern experimental methods for gas turbine heat transfer and cooling research Advanced computational models for gas turbine heat transfer and cooling performance predictions Suggestions for future research in this critical technology The book discusses the need for turbine cooling, gas turbine heat-transfer problems, and cooling methodology and covers turbine rotor and stator heat-transfer issues, including endwall and blade tip regions under engine conditions, as well as under simulated engine conditions. It then examines turbine rotor and stator blade film cooling and discusses the unsteady high free-stream turbulence effect on simulated cascade airfoils. From here, the book explores impingement cooling, rib-turbulent cooling, pin-fin cooling, and compound and new cooling techniques. It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques, as well as flow and thermal measurement techniques. The book concludes with discussions of governing equations and turbulence models and their applications for predicting turbine blade heat transfer and film cooling, and turbine blade internal cooling.
Book Synopsis Experimental Investigation of Overall Effectiveness and Coolant Jet Interactions on a Fully Cooled C3X Turbine Vane by : John W. McClintic
Download or read book Experimental Investigation of Overall Effectiveness and Coolant Jet Interactions on a Fully Cooled C3X Turbine Vane written by John W. McClintic and published by . This book was released on 2013 with total page 300 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study focused on experimentally measuring the performance of a fully cooled, scaled up C3X turbine vane. Experimental measurements focused on investigating row-to-row interactions of coolant jets and the contributions of external film cooling and internal impingement cooling to overall cooling effectiveness. Overall effectiveness was experimentally measured using a thermally scaled, matched Biot number vane model featuring a realistic internal impingement scheme and had normalized surface temperatures that were representative of those found on engine components. A geometrically identical vane was also constructed out of low conductivity polystyrene foam to measure the normalized adiabatic wall temperature, or adiabatic effectiveness of the film cooling configuration. The vanes featured a full coverage film-cooling scheme with a five-row showerhead and 13 total rows of holes containing 149 total coolant holes. This study was the first study to make highly detailed measurements of overall effectiveness on a fully-cooled vane model and expands on previous studies of adiabatic and overall effectiveness on the showerhead and single rows of holes on a matched Biot vane by considering a fully cooled configuration to determine if the results from these previous studies also hold for a fully cooled configuration. Additionally, velocity and thermal fields were measured just upstream of two different suction side rows of holes in order to study the effect of introducing upstream coolant injection. The effects of mainstream turbulence and span-wise location were examined and at the downstream row of holes, the contributions of different rows of holes to the approach flow were compared. This study was the first to measure mean and fluctuating velocity data on the suction side of a turbine vane with upstream coolant injection. Understanding the effects of how upstream injection affects the performance of downstream rows of holes is critical to understanding the film cooling performance on a fully cooled turbine airfoil.
Book Synopsis Experimental Measurement of Overall Effectiveness and Internal Coolant Temperatures for a Film Cooled Gas Turbine Airfoil with Internal Impingement Cooling by : Randall Paul Williams
Download or read book Experimental Measurement of Overall Effectiveness and Internal Coolant Temperatures for a Film Cooled Gas Turbine Airfoil with Internal Impingement Cooling written by Randall Paul Williams and published by . This book was released on 2012 with total page 258 pages. Available in PDF, EPUB and Kindle. Book excerpt: A scaled-up gas turbine vane model was constructed in such a way to achieve a Biot number (Bi) representative of an actual engine component, and experiments were performed to collect temperature data which may be used to validate computational fluid dynamics (CFD) codes used in the design of gas turbine cooling schemes. The physical model incorporated an internal impingement plate to provide cooling on the inner wall surface, and film cooling over the external surface was provided by a single row of holes located on the suction side of the vane. A single row of holes was chosen to simplify the operating condition and test geometry for the purpose of evaluating CFD predictions. Thermocouples were used to measure internal gas temperatures and internal surface temperatures over a range of coolant flow rates, while infra-red thermography was used to measure external surface temperatures. When Bi is matched to an actual engine component, these measured temperatures may be normalized relative to the coolant temperature and mainstream gas temperature to determine the overall cooling effectiveness, which will be representative of the real engine component. Measurements were made to evaluate the overall effectiveness resulting from internal impingement cooling alone, and then with both internal impingement cooling and external film cooling as the coolant flow rate was increased. As expected, with internal impingement cooling alone, both internal and external wall surfaces became colder as the coolant flow rate was increased. The addition of film cooling further increased the overall effectiveness, particularly at the lower and intermediate flow rates tested, but provided little benefit at the highest flow rates. An optimal jet momentum flux ratio of I=1.69 resulted in a peak overall effectiveness, although the film effectiveness was shown to be low under these conditions. The effect of increasing the coolant-to-mainstream density ratio was evaluated at one coolant flow rate and resulted in higher values of overall cooling effectiveness and normalized internal temperatures, throughout the model. Finally, a 1-dimensional heat transfer analysis was performed (using a resistance analogy) in which overall effectiveness with film cooling was predicted from measurements of film effectiveness and overall effectiveness without film cooling. This analysis tended to over-predict overall effectiveness, at the lowest values of the jet momentum flux ratio, while under-predicting it at the highest values.
Book Synopsis Investigation of Approach Flow Parameters, Scaling Factors, and Measurement Accuracy for Film Cooling Effectiveness and Heat Transfer Coefficient Measurements by : Joshua Brian Anderson
Download or read book Investigation of Approach Flow Parameters, Scaling Factors, and Measurement Accuracy for Film Cooling Effectiveness and Heat Transfer Coefficient Measurements written by Joshua Brian Anderson and published by . This book was released on 2017 with total page 572 pages. Available in PDF, EPUB and Kindle. Book excerpt: Film cooling is widely used in gas turbine engines to manage temperatures within the hot section of the engine. In this work, several investigations are described, all of which studied how fundamental hydrodynamic and thermal parameters influence the performance of film cooling. The first investigation studied the impact of freestream turbulence, boundary layer thickness, Reynolds number, and Mach number on film cooling performance, using axial shaped film cooling holes. The second study considered a similar set of parameters, and investigated their impact on compound-angle oriented film cooling holes. Both of these studies utilized measurements of adiabatic effectiveness and heat transfer coefficient augmentation. In general, the parameters had effects which were dependent on the coolant flow rate and density ratio. The final study considered methods to reduce the experimental uncertainty which arises from conduction and radiation errors in thermal measurements. A careful evaluation of the thermal boundary layer was used to validate these corrections
Book Synopsis Surface Measurements and Predictions of Full-coverage Film Cooling by : Greg Natsui
Download or read book Surface Measurements and Predictions of Full-coverage Film Cooling written by Greg Natsui and published by . This book was released on 2012 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: Full-coverage film cooling is investigated both experimentally and numerically. First, surface measurements local of adiabatic film cooling eeffectiveness and heat transfer augmentation for four different arrays are described. Reported next is a comparison between two very common turbulence models, Realizable k-[epsilon] and SST k-[omega], and their ability to predict local film cooling effectiveness throughout a full-coverage array. The objective of the experimental study is the quantification of local heat transfer augmentation and adiabatic film cooling effectiveness for four surfaces cooled by large, both in hole count and in non-dimensional spacing, arrays of film cooling holes. The four arrays are of two different hole-to-hole spacings (P/D = X/D = 14.5; 19.8) and two different hole inclination angles ([alpha] = 30°; 45°), with cylindrical holes compounded relative to the flow ([beta] = 45°) and arranged in a staggered configuration. Arrays of up to 30 rows are tested so that the superposition effect of the coolant film can be studied. In addition, shortened arrays of up to 20 rows of coolant holes are also tested so that the decay of the coolant film following injection can be studied. Levels of laterally averaged effectiveness reach values as high as [eta with line above]= 0.5, and are not yet at the asymptotic limit even after 20-30 rows of injection for all cases studied. Levels of heat transfer augmentation asymptotically approach values of h=h0 [almost equal to] 1.35 rather quickly, only after 10 rows. It is conjectured that the heat transfer augmentation levels off very quickly due to the boundary layer reaching an equilibrium in which the perturbation from additional film rows has reached a balance with the damping effect resulting from viscosity. The levels of laterally averaged adiabatic film cooling effectiveness far exceeding [eta with line above]= 0.5 are much higher than expected. The heat transfer augmentation levels off quickly as opposed to the film effectiveness which continues to rise (although asymptotically) at large row numbers. This ensures that an increased row count represents coolant well spent. The numerical predictions are carried out in order to test the ability of the two most common turbulence models to properly predict full-coverage film cooling. The two models chosen, Realizable k-[epsilon] (RKE) and Shear Stress Transport k-[omega] (SSTKW), are both two-equation models coupled with Reynolds Averaged governing equations which make several gross physical assumptions and require several empirical values. Hence, the models are not expected to provide perfect results. However, very good average values are seen tobe obtained through these simple models. Using RKE in order to model full-coverage filmcooling will yield results with 30% less error than selecting SSTKW.
Book Synopsis Film cooling on the pressure surface of a turbine vane by : James W. Gauntner
Download or read book Film cooling on the pressure surface of a turbine vane written by James W. Gauntner and published by . This book was released on 1977 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Computational Investigation of Film Cooling on a Large Scale C3X Turbine Vane Including Conjugate Effects by : Thomas Earl Dyson
Download or read book Experimental and Computational Investigation of Film Cooling on a Large Scale C3X Turbine Vane Including Conjugate Effects written by Thomas Earl Dyson and published by . This book was released on 2012 with total page 576 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study focused on the improvement of film cooling for gas turbine vanes using both computational and experimental techniques. The experimental component used a matched Biot number model to measure scaled surface temperature (overall effectiveness) distributions representative of engine conditions for two new configurations. One configuration consisted of a single row of holes on the pressure surface while the other used numerous film cooling holes over the entire vane including a showerhead. Both configurations used internal impingement cooling representative of a 1st vane. Adiabatic effectiveness was also measured. No previous studies had shown the effect of injection on the mean and fluctuating velocity profiles for the suction surface, so measurements were made at two locations immediately upstream of film cooling holes from the fully cooled cooling configuration. Different blowing conditions were evaluated. Computational tools are increasingly important in the design of advanced gas turbine engines and validation of these tools is required prior to integration into the design process. Two film cooling configurations were simulated and compared to past experimental work. Data from matched Biot number experiments was used to validate the overall effectiveness from conjugate simulations in addition to adiabatic effectiveness. A simulation of a single row of cooling holes on the suction side also gave additional insight into the interaction of film cooling jets with the thermal boundary layer. A showerhead configuration was also simulated. The final portion of this study sought to evaluate the performance of six RANS models (standard, realizable, and renormalization group k-[epsilon]; standard k-[omega]; k-[omega] SST; and Transition SST) with respect to the prediction of thermal boundary layers. The turbulent Prandtl number was varied to test a simple method for improvement of the thermal boundary layer predictions.
Book Synopsis A Comparison of Film Cooling Techniques in a High Speed, True Scale, Fully Cooled Turbine Vane Ring by : Michael J. Umholtz
Download or read book A Comparison of Film Cooling Techniques in a High Speed, True Scale, Fully Cooled Turbine Vane Ring written by Michael J. Umholtz and published by . This book was released on 2007 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Rough Wall and Near-hole Obstruction Effects on Film Cooling with and Without a Transverse Trench by : Ruwan Prasanna Somawardhana
Download or read book Rough Wall and Near-hole Obstruction Effects on Film Cooling with and Without a Transverse Trench written by Ruwan Prasanna Somawardhana and published by . This book was released on 2006 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt: Significant degradation of adiabatic effectiveness can be caused by surface roughness and near-hole obstructions formed from deposition of contaminants. Since obstructions are a randomly occurring event, there are many variables to consider, namely shape, width, length, height, and position in relation to a film cooling hole. In addition to this, the level of overall surface roughness must also be considered. This study investigated these different variables on the suction side of a scaled-up turbine vane using cylindrical holes to determine what is important when considering surface roughness and obstructions. In addition, the use of a transverse trench was tested with a rough wall and near-hole obstructions and was found to be a method to mitigate a large part of the degrading effects caused by a rough surface and near-hole obstructions.
Book Synopsis Detailed film cooling effectiveness and three component velocity field measurements on a first stage turbine vane subject to high freestream turbulence by : Marcus Damian Polanka
Download or read book Detailed film cooling effectiveness and three component velocity field measurements on a first stage turbine vane subject to high freestream turbulence written by Marcus Damian Polanka and published by . This book was released on 1999 with total page 718 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Film Cooling Effectiveness on a Turbine Vane in Transonic Conditions by : Isabella Gayoso
Download or read book Film Cooling Effectiveness on a Turbine Vane in Transonic Conditions written by Isabella Gayoso and published by . This book was released on 2023 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this experiment, measurements of the overall cooling effectiveness for a film cooled turbine vane airfoil in a high-speed cascade were obtained using infrared thermography. The vane used was the NASA C3X with impingement holes (showerhead cooling) and convective cooling holes on both the suction and pressure side. This work was done in the Mechanical Engineering Department's Experimental and Computational Convection Lab and used the high-speed cascade capability of the lab. The rationale for conducting this work was to obtain experimental data on film cooling effectiveness in a turbine vane in engine-like conditions at transonic speeds. Previous work has been done at subsonic speeds, but few pieces of literature examine this parameter at transonic speeds. The data can then be used to validate or compare to CFD models and to better understand what happens to the vane temperature distribution during engine operation. This understanding could inform the design of film cooling holes to reduce thermal strain "hot spots" which lead to failure of the vane. The results showed that trends for values of overall film effectiveness were as expected in this experiment, such as increases in blowing ratio correlating to increases in overall film effectiveness. However, the blowing ratios used in this study were not as high as values studied previously, indicating a need for more data on overall film effectiveness at transonic speeds.
Book Synopsis Comparison of Cooling Effectiveness of Turbine Vanes with and Without Film Cooling by :
Download or read book Comparison of Cooling Effectiveness of Turbine Vanes with and Without Film Cooling written by and published by . This book was released on 1974 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Three-Dimensional Coupled Internal/External Simulation of a Film-Cooled Turbine Vane by : James D. Heidmann
Download or read book A Three-Dimensional Coupled Internal/External Simulation of a Film-Cooled Turbine Vane written by James D. Heidmann and published by . This book was released on 1999 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
