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Author : Issac Roland
Publisher :
ISBN 13 :
Total Pages : 164 pages
Book Rating : 4.:/5 (244 download)
Download or read book An Experimental Investigation of the Effect of Dimples on Turbine Adiabatic Film Cooling written by Issac Roland and published by . This book was released on 2008 with total page 164 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : S. Stephen Papell
Publisher :
ISBN 13 :
Total Pages : 68 pages
Book Rating : 4.:/5 (31 download)
Download or read book Experimental Investigation of Air Film Cooling Applied to an Adiabatic Wall by Means of an Axially Discharging Slot written by S. Stephen Papell and published by . This book was released on 1959 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James Edward Mayhew
Publisher :
ISBN 13 :
Total Pages : 482 pages
Book Rating : 4.:/5 (62 download)
Download or read book An Experimental Investigation of the Effect of Freestream Turbulence on Film Cooling Using Thermochromic Liquid Crystal Thermography written by James Edward Mayhew and published by . This book was released on 1999 with total page 482 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : David Seager
Publisher :
ISBN 13 :
Total Pages : 228 pages
Book Rating : 4.:/5 (397 download)
Download or read book An Experimental Investigation on the Effects of Film Cooling Hole Geometry written by David Seager and published by . This book was released on 1998 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Christian Liess
Publisher :
ISBN 13 :
Total Pages : 116 pages
Book Rating : 4.F/5 ( download)
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:
Author : Darryl E. Metzger
Publisher :
ISBN 13 :
Total Pages : 152 pages
Book Rating : 4.F/5 ( download)
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:
Author : John W. McClintic
Publisher :
ISBN 13 :
Total Pages : 300 pages
Book Rating : 4.:/5 (863 download)
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.
Author : Thomas Earl Dyson
Publisher :
ISBN 13 :
Total Pages : 576 pages
Book Rating : 4.:/5 (826 download)
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.
Author : S. Stephen Papell
Publisher :
ISBN 13 :
Total Pages : 64 pages
Book Rating : 4.:/5 (249 download)
Download or read book Experimental Investigation of Air Film Cooling Applied to an Adiabatic Wall by Means of an Axially Discharching Slot written by S. Stephen Papell and published by . This book was released on 1959 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Mohammad Arif Hossain
Publisher :
ISBN 13 :
Total Pages : 242 pages
Book Rating : 4.:/5 (122 download)
Download or read book Sweeping Jet Film Cooling written by Mohammad Arif Hossain and published by . This book was released on 2020 with total page 242 pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbine is an integrated part of modern aviation and power generation industry. The thermal efficiency of a gas turbine strongly depends on the turbine inlet temperature (TIT), and the turbine designers are continuously pushing the TIT to a higher value. Due to the increased freedom in additive manufacturing, the complex internal and external geometries of the turbine blade can be leveraged to utilize innovative cooling designs to address some of the shortcomings of current cooling technologies. The sweeping jet film cooling has shown some promise to be an effective method of cooling where the coolant can be brought very close to the blade surface due to its sweeping nature. A series of experiments were performed using a row of fluidic oscillators on a flat plate. Adiabatic cooling effectiveness, convective heat transfer coefficient, thermal field, and discharge coefficient were measured over a range of blowing ratios and freestream turbulence. Results were compared with a conventional shaped hole (777-hole), and the sweeping jet hole shows improved cooling performance in the lateral direction. Numerical simulation also confirmed that the sweeping jet creates two alternating vortices that do not have mutual interaction in time. When the jet sweeps to one side of the hole exit, it acts as a vortex generator as it interacts with the mainstream ow. This prevents the formation of the counter-rotating vortex pair (CRVP) and allows the coolant to spread in the lateral direction. The results obtained from the low speed at plate tests were utilized to design the sweeping jet film cooling hole for more representative turbine vane geometry. Experiments were performed in a low-speed linear cascade facility. Results showed that the sweeping jet hole has higher cooling effectiveness in the near hole region compared to the shaped hole at high blowing ratios. Next, a detailed experimental investigation of sweeping jet film cooling on the suction surface of a near engine scale transonic nozzle guide vane at an engine relevant Mach number (Ma = 0.8) and Reynolds number (Re = 1x10e6) to determine the effect of compressibility. The heat transfer measurements were conducted with a transient IR method, and the convective heat transfer coefficient (HTC) and adiabatic film cooling effectiveness were estimated using a dual linear regression technique (DLRT). Aerodynamic loss measurements were also performed at an exit plane downstream of the vane cascade. Finally, a comprehensive design integration of sweeping jet film hole was carried out in a Direct Metal Laser Sintering (DMLS) enabled engine scale nozzle guide vane and experimental investigation of overall cooling effectiveness at engine relevant temperature conditions were assessed. The systematic evolution of a sweeping jet film cooling hole design from a large scale flat plate to an engine scale nozzle guide vane has been presented.
Author : Jason I. Shapiro
Publisher :
ISBN 13 :
Total Pages : 186 pages
Book Rating : 4.:/5 (259 download)
Download or read book An Experimental Investigation of the Effects of Induced High Turbulence in Film Cooling Flows written by Jason I. Shapiro and published by . This book was released on 2008 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt: A survey into the effects of turbulence intensity induced in film cooling flows was performed using thermal anemometry and thermocouple temperature measurements.
Author : Bengt Sundén
Publisher : Witpress
ISBN 13 :
Total Pages : 544 pages
Book Rating : 4.3/5 (91 download)
Download or read book Heat Transfer in Gas Turbines written by Bengt Sundén and published by Witpress. This book was released on 2001 with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt: This title presents and reflects current active research on various heat transfer topics and related phenomena in gas turbine systems. It begins with a general introduction to gas turbine heat transfer, before moving on to specific areas.
Author : Stephen J. Kline
Publisher :
ISBN 13 :
Total Pages : 65 pages
Book Rating : 4.:/5 (67 download)
Download or read book Experimental Investigation of the Effects of Cooling on Friction and on Boundary-layer Transistion for Low-speed Gas Flow at the Entry of a Tube written by Stephen J. Kline and published by . This book was released on 1953 with total page 65 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of cooling on boundary-layer transition in the steady flow of air in the entrance of a smooth round tube has been investigated experimentally. Runs were made at diameter Reynolds numbers varying from 50,000 to 106,000. The levels of disturbance were such as to yield adiabatic length Reynolds numbers (based on the length to the start of transition) ranging from 500,000 to 1,800,000. Transition was determined from logarithmic plots of local apparent friction factor against length Reynolds number. Temperature differences between the wall and the free stream up to 270 degrees F were applied, but no significant effect of cooling on the point of transition was found.
Author : Richard R. Cullom
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Experimental Investigation of the Effectiveness of an Ablation-produced Film in Cooling a Rocket Nozzle written by Richard R. Cullom and published by . This book was released on 1961 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 56 pages
Book Rating : 4.:/5 (949 download)
Download or read book An Experimental Investigation of an Anti-vortex of Film Cooling on Flat Plate Surface written by and published by . This book was released on 2014 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James R. Winka
Publisher :
ISBN 13 :
Total Pages : 246 pages
Book Rating : 4.:/5 (863 download)
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.
Author :
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (946 download)
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.
