Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Effects Of Upstream Synfuel Deposition On Film Cooling Effectiveness And Convective Heat Transfer Coefficient Near Industrial Gas Turbine Film Cooling Holes
Download Effects Of Upstream Synfuel Deposition On Film Cooling Effectiveness And Convective Heat Transfer Coefficient Near Industrial Gas Turbine Film Cooling Holes full books in PDF, epub, and Kindle. Read online Effects Of Upstream Synfuel Deposition On Film Cooling Effectiveness And Convective Heat Transfer Coefficient Near Industrial Gas Turbine Film Cooling Holes ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Effects of Upstream Synfuel Deposition on Film Cooling Effectiveness and Convective Heat Transfer Coefficient Near Industrial Gas Turbine Film Cooling Holes by : Scott Dudley Lewis
Download or read book Effects of Upstream Synfuel Deposition on Film Cooling Effectiveness and Convective Heat Transfer Coefficient Near Industrial Gas Turbine Film Cooling Holes written by Scott Dudley Lewis and published by . This book was released on 2008 with total page 202 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: An experimental film cooling study was performed to understand heat transfer effects due to upstream synfuel deposition. A scaled up model incorporating actual synfuel deposition topography was used. The model contained six cylindrical holes inclined at 300. A flat model with the same film cooling hole geometry was used for comparison. An infrared camera was used to obtain both the film cooling effectiveness from a steady state test and heat transfer coefficient from a transient test. The roughness model had deposition valleys along the centerline of the holes, which caused the flow to accelerate around the peaks and helped to keep the coolant jet down on the surface. This flow acceleration caused large film cooling effectiveness improvements for the 1 and 1.5 blowing ratio cases. The heat transfer coefficient showed both cooling benefits as well as cooling losses due to deposit roughness. The roughness model showed no kidney vortices as opposed to the flat model, which produced a beneficial localized reduction in heat transfer coefficient around the film cooling holes. Although a sharp detrimental rise in heat transfer coefficient occurred on the rough model for the 1.5 blowing ratio case. The heat flux ratio shows the overall cooling effect and a substantial cooling benefit compared to the flat model occurred at blowing ratios of 1 and 1.5. It is concluded that the film cooling effects of upstream deposition on actual turbine blades can be highly beneficial.
Book Synopsis Conjugate Heat Transfer Effects on Gas Turbine Film Cooling by : William Robb Stewart
Download or read book Conjugate Heat Transfer Effects on Gas Turbine Film Cooling written by William Robb Stewart and published by . This book was released on 2014 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt: The efficiency of natural gas turbines is directly linked to the turbine inlet temperature, or the combustor exit temperature. Further increasing the turbine inlet temperature damages the turbine components and limits their durability. Advances in turbine vane cooling schemes protect the turbine components. This thesis studies the conjugate effects of internal cooling, film cooling and thermal barrier coatings (TBC) on turbine vane metal temperatures. Two-dimensional thermal profiles were experimentally measured downstream of a single row of film cooling holes on both an adiabatic and a matched Biot number model turbine vane. The measurements were taken as a comparison to computational simulations of the same model and flow conditions. To improve computational models of the evolution of a film cooling jet as it propagates downstream, the thermal field above the vane, not just the footprint on the vane surface must be analyzed. This study expands these data to include 2-D thermal fields above the vane at 0, 5 and 10 hole diameters downstream of the film cooling holes. In each case the computational jets remained colder than the experimental jets because they did not disperse into the mainstream as quickly. Finally, in comparing results above adiabatic and matched Biot number models, these thermal field measurements allow for an accurate analysis of whether or not the adiabatic wall temperature was a reasonable estimate of the driving temperature for heat transfer. In some cases the adiabatic wall temperature did give a good indication of the driving temperature for heat transfer while in other cases it did not. Previous tests simulating the effects of TBC on an internally and film cooled model turbine vane showed that the insulating effects of TBC dominate over variations in film cooling geometry and blowing ratio. In this study overall and external effectiveness were measured using a matched Biot number model vane simulating a TBC of thickness 0.6d, where d is the film cooing hole diameter. This new model was a 35% reduction in thermal resistance from previous tests. Overall effectiveness measurements were taken for an internal cooling only configuration, as well as for three rows of showerhead holes with a single row of holes on the pressure side of the vane. This pressure side row of holes was tested both as round holes and as round holes embedded in a realistic trench with a depth of 0.6 hole diameters. Even in the case of this thinner TBC, the insulating effects dominate over film cooling. In addition, using measurements of the convective heat transfer coefficient above the vane surface, and the thermal conductivities of the vane wall and simulated TBC material, a prediction technique of the overall effectiveness with TBC was evaluated.
Book Synopsis Film cooling effectiveness and heat transfer coefficient distributions around diffusion shaped holes, ASME 99-GT-34 by : Y. Yu
Download or read book Film cooling effectiveness and heat transfer coefficient distributions around diffusion shaped holes, ASME 99-GT-34 written by Y. Yu and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.
Book Synopsis Effect of Surface Roughness on Local Film Cooling Effectiveness and Heat Transfer Coefficients by : Douglas Neal Barlow
Download or read book Effect of Surface Roughness on Local Film Cooling Effectiveness and Heat Transfer Coefficients written by Douglas Neal Barlow and published by . This book was released on 1994 with total page 588 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Detailed Investigation of the Fluid Dynamics and Heat Transfer Related to Injection from a Compound Angled Shaped Film Cooling Hole by : Shane Haydt
Download or read book A Detailed Investigation of the Fluid Dynamics and Heat Transfer Related to Injection from a Compound Angled Shaped Film Cooling Hole written by Shane Haydt and published by . This book was released on 2018 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbines are used around the world to provide thrust for airplanes and to generate electricity. Designers and operators are constantly chasing higher thermal efficiency, and even an incremental increase is considered an achievement. Higher thermal efficiency begets higher turbine inlet temperatures, and the parts that are exposed to these temperatures require sophisticated cooling technologies. One such cooling method is shaped film cooling, which ejects low momentum coolant with the goal of it staying attached to the wall, spreading laterally, and providing a lower driving temperature for convection.In some film cooling manufacturing processes, the meter and diffuser are created in separate steps with separate machines, and an offset can occur in that process. A study was designed to quantify the change in adiabatic effectiveness for five offset directions: fore, fore-left, left, aft-left, and aft. All offset directions caused a detriment to film cooling performance, except for the fore offset, which improved adiabatic effectiveness relative to a no offset case. CFD helped show that the fore offset created a separation in the region of the film cooling metering section where jetting occurs, which decreased the high momentum and made the cooling jet more likely to remain attached to the surface. This study resulted in a patent.A large range of area ratios and blowing ratios were examined in a study designed to isolate the effect of area ratio by lengthening the diffuser of a shaped hole. Very high area ratios were generated that resulted in significant cooling potential. It was shown that at each area ratio there is an optimal blowing ratio beyond which the effectiveness will decrease or plateau. This was reduced to an optimal effective blowing ratio, M/AR, which was shown through CFD to be the condition when the coolant jet core has similar velocity magnitude to the mainstream flow. This results in a weak shear layer and a weak counter-rotating vortex pair.In an axially oriented hole, the mainstream flows over the top of a cooling jet and around the sides, in equal measure, creating a symmetric flowfield. In a compound angled shaped hole, the mainstream flows primarily around the leeward side, creating a strong shear layer and an asymmetric streamwise vortex. Compound angled shaped holes are used commonly in gas turbines, but there has been no work examining the adiabatic effectiveness and heat transfer coefficient augmentation at a range of compound angles, and there are no flowfield measurements. A comprehensive study of the flowfield, cooling effectiveness, and heat transfer coefficient were obtained for compound angled shaped holes for compound angles ranging from 0-60 in 15 increments. It is shown that asymmetry and vorticity magnitude increase with increasing compound angle and increasing blowing ratio. Holes with high compound angles can maintain jet attachment at high blowing ratios because the streamwise component of blowing ratio is reduced, which leads to high effectiveness. The most important contribution of this work was showing that the streamwise vortex increases heat transfer coefficient in a region adjacent to the jet, where very little coolant coverage exists. For this reason, compound angled shaped holes can cause local regions of increased heat flux relative to an uncooled surface, which may be an issue for some designs if not properly accounted for. Heat transfer coefficient augmentation increases as compound angle and blowing ratio increase. Designs that promote jet interaction, such as holes with a smaller pitchwise spacing or holes with significant lateral motion, cover the entire endwall in coolant and lessen the negative effects of high heat transfer coefficient augmentation.
Book Synopsis Film Cooling Effectiveness and Mass/heat Transfer Coefficient Downstream of One Row of Discrete Holes by : R. J. Goldstein
Download or read book Film Cooling Effectiveness and Mass/heat Transfer Coefficient Downstream of One Row of Discrete Holes written by R. J. Goldstein and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, June 2 - June 5, 1998.
Book Synopsis The Effect of Film Cooling on the Heat Transfer Between a Shrouded Rotating Disk and a Radially Inward Flow by : Darryl E. Metzger
Download or read book The Effect of Film Cooling on the Heat Transfer Between a Shrouded Rotating Disk and a Radially Inward Flow written by Darryl E. Metzger and published by . This book was released on 1963 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Film Cooling with Ejection from a Row of Inclined Circular Holes by : Christian Liess
Download or read book Film Cooling with Ejection from a Row of Inclined Circular Holes written by Christian Liess and published by . This book was released on 1973 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Influence of Gap Leakage on the Film Effectiveness and Heat Transfer Around Discrete Injection Holes by : Yue Cheng Hsing
Download or read book Influence of Gap Leakage on the Film Effectiveness and Heat Transfer Around Discrete Injection Holes written by Yue Cheng Hsing and published by . This book was released on 1997 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: Research has been performed to investigate the heat transfer characteristics of cooling film over a misaligned leaking gap, using a thermographic phosphor fluorescence imaging technique. Such a flow pattern is usually seen on the component-to-component interface of inlet guide vanes in a gas turbine system. This problem can be classified as a four-temperature problem. The present study defines a true driving potential of the convective heat transfer of a four-temperature system. Experiments are performed systematically to investigate problems of traditional film cooling, the gap leakage together with a misaligned interface effect, and finally, a combined four-temperature system. The result of current film cooling studies reveals a comparable agreement with that found in open literature using conventional measurement techniques. The same conclusion is obtained for a gap leakage study at an aligned interface circumstance. Another finding of the gap leakage study is that the cooling performance in a backward-facing step is the best among all misaligned interface situations. For a four-temperature situation, the flowfield changes significantly in the presence of a leaking gap downstream of film-cooling jets or vise versa. The cooling performance of each coolant injection is either enhanced or degraded, depending on the ratio of the blow strength the first coolant film to that of the second. The misaligned interface effect lessens when the ratio is smaller than one. In contrast to the gap leakage results, the forward-facing step situation presents the best film effectiveness distribution. Generally, the cooling performance is decreased when film-cooling jets re revealed upstream of a gap leakage. The effect is opposite when a leaking gap is located upstream.
Book Synopsis Fundamental Heat Transfer Research for Gas Turbine Engines by :
Download or read book Fundamental Heat Transfer Research for Gas Turbine Engines written by and published by . This book was released on 1980 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of Shaping Inclined Slots on Film Cooling Effectiveness and Heat Transfer Coefficient by : J. P. Farmer
Download or read book The Effect of Shaping Inclined Slots on Film Cooling Effectiveness and Heat Transfer Coefficient written by J. P. Farmer 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 Effects of Hole Length, Supply Plenum Geometry, and Freestream Turbulence on Film Cooling Performance by :
Download or read book Effects of Hole Length, Supply Plenum Geometry, and Freestream Turbulence on Film Cooling Performance written by and published by . This book was released on 2000 with total page 324 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Film Cooling Effectiveness and Mass/heat Transfer Coefficient Downstream of One Row of Discrete Holes with 45 Degree Compound Angles by : Peitong Jin
Download or read book Film Cooling Effectiveness and Mass/heat Transfer Coefficient Downstream of One Row of Discrete Holes with 45 Degree Compound Angles written by Peitong Jin and published by . This book was released on 1998 with total page 312 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Suction Side Roughness Effects on Film Cooling Heat Transfer on a Turbine Vane by :
Download or read book Suction Side Roughness Effects on Film Cooling Heat Transfer on a Turbine Vane written by and published by . This book was released on 2004 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study was conducted in a simulated three vane linear cascade to determine the effects of surface roughness and film cooling on the heat transfer coefficient distribution in the region downstream of the first row of suction side coolant holes. Suction side film cooling was operated in the range 0 less than M less than 1.4. The showerhead was tested at M(sub sh) = 1.6. In addition to the completely smooth condition, simulated airfoil roughness was used upstream of the coolant holes, downstream of the coolant holes, and both upstream and downstream of the coolant holes. Two levels of mainstream turbulence intensity were tested. The heat transfer measurements were conducted by application of a uniform heat flux in the region downstream of the coolant holes. The resulting surface temperature distributions were measured with infrared thermography. Because the upstream region was unheated, the influence of film cooling on the heat transfer coefficient was due to only to hydrodynamic effects and not thermal effects. The coolant to mainstream density ratio of the majority of the experiments was unity; however, a single experiment was conducted at a density ratio of DR = 1.6 to determine how the coolant to mainstream density ratio affects heat transfer. Net heat flux reduction calculations were performed by combining the heat transfer coefficient measurements of the present study with adiabatic effectiveness measurements of a separate study. In order to gain insight into the hydrodynamics that affect the heat transfer, boundary layer measurements were conducted using hot-wire anemometry.
Book Synopsis Film Cooling Effectiveness from Tows of Holes Under Simulated Gas Turbine Conditions by : M. R. Smith
Download or read book Film Cooling Effectiveness from Tows of Holes Under Simulated Gas Turbine Conditions written by M. R. Smith and published by . This book was released on 1974 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Overall Correlation of Film Cooling Effectiveness from One Row of Holes by : S. Baldauf
Download or read book An Overall Correlation of Film Cooling Effectiveness from One Row of Holes written by S. Baldauf 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 Effect on Gaseous Film Cooling of Coolant Injection Through Angled Slots and Normal Holes by : S. Stephen Papell
Download or read book Effect on Gaseous Film Cooling of Coolant Injection Through Angled Slots and Normal Holes written by S. Stephen Papell and published by . This book was released on 1960 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
