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Two Dimensional Cold Air Cascade Study Of A Film Cooled Turbine Stator Blade 5 Comparison Of Experimental And Analytical Aerodynamic Results For Blade With 12 Rows Of 0038 Centimeter 0015 Inch Diameter Coolant Holes Having Streamwise Ejection Angl
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Book Synopsis Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade. 5: Comparison of Experimental and Analytical Aerodynamic Results for Blade with 12 Rows of 0.038-centimeter-(0.015 Inch) Diameter Coolant Holes Having Streamwise Ejection Angl by :
Download or read book Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade. 5: Comparison of Experimental and Analytical Aerodynamic Results for Blade with 12 Rows of 0.038-centimeter-(0.015 Inch) Diameter Coolant Holes Having Streamwise Ejection Angl written by and published by . This book was released on 1978 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade by : Herman W. Prust
Download or read book Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade written by Herman W. Prust and published by . This book was released on 1978 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723300318 Total Pages :24 pages Book Rating :4.3/5 (3 download)
Book Synopsis Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 5 by : National Aeronautics and Space Administration (NASA)
Download or read book Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 5 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-20 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Published experimental aerodynamic efficiency results were compared with results predicted from two published analytical methods. This is the second of two such comparisons. One of the analytical methods was used as published; the other was modified for certain cases of coolant discharge from the blade suction surface. The results show that for 23 cases of single row and multirow discharge covering coolant fractions from 0 to about 9 percent, the difference between the experimental and predicted results was no greater than about 1 percent in any case and less than 1/2 percent in most cases. Prust, H. W., Jr. Glenn Research Center NASA-TP-1204, E-9342 RTOP 505-04
Book Synopsis Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade. 5 by : H. W. Prust (Jr)
Download or read book Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade. 5 written by H. W. Prust (Jr) and published by . This book was released on 1978 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade. 4: Comparison of Experimental and Analytical Aerodynamic Results for Blade with 12 Rows of 0.076-centimeter-(0.030-inch-) Diameter Holes Having Streamwise Ejection Angles by :
Download or read book Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade. 4: Comparison of Experimental and Analytical Aerodynamic Results for Blade with 12 Rows of 0.076-centimeter-(0.030-inch-) Diameter Holes Having Streamwise Ejection Angles written by and published by . This book was released on 1978 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Previously published experimental aerodynamic efficiency results for a film cooled turbine stator blade are compared with analytical results computed from two published analytical methods. One method was used as published; the other was modified for certain cases of coolant discharge from the blade suction surface. For coolant ejection from blade surface regions where the surface static pressures are higher than the blade exit pressure, both methods predict the experimental results quite well. However, for ejection from regions with surface static pressures lower than the blade exit pressure, both methods predict too small a change in efficiency. The modified method gives the better prediction.
Book Synopsis Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade by : Herman W. Prust
Download or read book Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade written by Herman W. Prust and published by . This book was released on 1978 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781724754981 Total Pages :32 pages Book Rating :4.7/5 (549 download)
Book Synopsis Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 4 by : National Aeronautics and Space Administration (NASA)
Download or read book Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 4 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-06 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Previously published experimental aerodynamic efficiency results for a film cooled turbine stator blade are compared with analytical results computed from two published analytical methods. One method was used as published; the other was modified for certain cases of coolant discharge from the blade suction surface. For coolant ejection from blade surface regions where the surface static pressures are higher than the blade exit pressure, both methods predict the experimental results quite well. However, for ejection from regions with surface static pressures lower than the blade exit pressure, both methods predict too small a change in efficiency. The modified method gives the better prediction. Prust, H. W., Jr. Glenn Research Center NASA-TP-1151, E-9187 RTOP 505-04
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781720155133 Total Pages :26 pages Book Rating :4.1/5 (551 download)
Book Synopsis Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 5: Comparison of Experimental and Analytical Aerodynamic Results for Bla by : National Aeronautics and Space Adm Nasa
Download or read book Two-Dimensional Cold-Air Cascade Study of a Film-Cooled Turbine Stator Blade. 5: Comparison of Experimental and Analytical Aerodynamic Results for Bla written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-10 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Published experimental aerodynamic efficiency results were compared with results predicted from two published analytical methods. This is the second of two such comparisons. One of the analytical methods was used as published; the other was modified for certain cases of coolant discharge from the blade suction surface. The results show that for 23 cases of single row and multirow discharge covering coolant fractions from 0 to about 9 percent, the difference between the experimental and predicted results was no greater than about 1 percent in any case and less than 1/2 percent in most cases. Prust, H. W., Jr. Glenn Research Center NASA-TP-1204, E-9342 RTOP 505-04
Book Synopsis Two-dimensional Cold Air Cascade Study of a Film Cooled Turbine Stator Blade by : Herman W. Purst
Download or read book Two-dimensional Cold Air Cascade Study of a Film Cooled Turbine Stator Blade written by Herman W. Purst and published by . This book was released on 1975 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade by : Herman W. Prust
Download or read book Two-dimensional Cold-air Cascade Study of a Film-cooled Turbine Stator Blade written by Herman W. Prust and published by . This book was released on 1976 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Two-dimensional Cold Air Cascade Study of a Film Cooled Turbine Stator Blade by : Herman W. Purst
Download or read book Two-dimensional Cold Air Cascade Study of a Film Cooled Turbine Stator Blade written by Herman W. Purst and published by . This book was released on 1975 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Study of the Effect of Wake Passing on Turbine Blade Film Cooling by : James D. Heidmann
Download or read book An Experimental Study of the Effect of Wake Passing on Turbine Blade Film Cooling written by James D. Heidmann and published by . This book was released on 1997 with total page 14 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 Cold-air Study of the Effect on Turbine Stator Blade Aerodynamic Performance of Coolant Ejection from Various Trailing-edge Slot Geometries. 1 by : H. W. Prust (Jr)
Download or read book Cold-air Study of the Effect on Turbine Stator Blade Aerodynamic Performance of Coolant Ejection from Various Trailing-edge Slot Geometries. 1 written by H. W. Prust (Jr) and published by . This book was released on 1974 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparison of Experimental and Analytical Aerodynamic Results for Blade with 12 Rows of 0.038-centimeter- (0.015-in.-) Diameter Coolant Holes Having Streamwise Ejection Angles by : Herman W. Prust
Download or read book Comparison of Experimental and Analytical Aerodynamic Results for Blade with 12 Rows of 0.038-centimeter- (0.015-in.-) Diameter Coolant Holes Having Streamwise Ejection Angles written by Herman W. Prust and published by . This book was released on 1978 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of Wake Passing on Turbine Blade Film Cooling by : James D. Heidmann
Download or read book The Effect of Wake Passing on Turbine Blade Film Cooling written by James D. Heidmann and published by . This book was released on 1996 with total page 272 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Film Cooling Effectiveness on Gas Turbine Blades by : Shiou-Jiuan Li
Download or read book Experimental Investigation of Film Cooling Effectiveness on Gas Turbine Blades written by Shiou-Jiuan Li and published by . This book was released on 2013 with total page 158 pages. Available in PDF, EPUB and Kindle. Book excerpt: High turbine inlet temperature becomes necessary for increasing thermal efficiency of modern gas turbines. To prevent failure of turbine components, advance cooling technologies have been applied to different portions of turbine blades. The detailed film cooling effectiveness distributions along a rotor blade has been studied under combined effects of upstream trailing edge unsteady wake with coolant ejection by the pressure sensitive paint (PSP). The experiment is conducted in a low speed wind tunnel with a five blade linear cascade and exit Reynolds number is 370,000. The density ratios for both blade and trailing edge coolant ejection range from 1.5 to 2.0. Blade blowing ratios are 0.5 and 1.0 on suction surface and 1.0 and 2.0 on pressure surface. Trailing edge jet blowing ratio and Strouhal number are 1.0 and 0.12, respectively. Results show the unsteady wake reduces overall effectiveness. However, the unsteady wake with trailing edge coolant ejection enhances overall effectiveness. Results also show that the overall effectiveness increases by using heavier coolant for ejection and blade film cooling. Leading edge film cooling has been investigated using PSP. There are two test models: seven and three-row of film holes for simulating vane and blade, respectively. Four film holes' configurations are used for both models: radial angle cylindrical holes, compound angle cylindrical holes, radial angle shaped holes, and compound angle shaped holes. Density ratios are 1.0 to 2.0 while blowing ratios are 0.5 to 1.5. Experiments were conducted in a low speed wind tunnel with Reynolds number 100,900. The turbulence intensity near test model is about 7%. The results show the shaped holes have overall higher effectiveness than cylindrical holes for both designs. As increasing density ratio, density effect on shaped holes becomes evident. Radial angle holes perform better than compound angle holes as increasing blowing and density ratios. Increasing density ratio generally increases overall effectiveness for all configurations and blowing ratios. One exception occurs for compound angle and radial angle shaped hole of three-row design at lower blowing ratio. Effectiveness along stagnation row reduces as increasing density ratio due to coolant jet with insufficient momentum caused by heavier density coolant, shaped hole, and stagnation row. The electronic version of this dissertation is accessible from http://hdl.handle.net/1969.1/148288
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720482284 Total Pages :64 pages Book Rating :4.4/5 (822 download)
Book Synopsis Effect of Film-Hole Shape on Turbine Blade Film Cooling Performance by : National Aeronautics and Space Administration (NASA)
Download or read book Effect of Film-Hole Shape on Turbine Blade Film Cooling Performance written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-30 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The detailed heat transfer coefficient and film cooling effectiveness distributions as well as tile detailed coolant jet temperature profiles on the suction side of a gas turbine blade A,ere measured using a transient liquid crystal image method and a traversing cold wire and a traversing thermocouple probe, respectively. The blade has only one row of film holes near the gill hole portion on the suction side of the blade. The hole geometries studied include standard cylindrical holes and holes with diffuser shaped exit portion (i.e. fanshaped holes and laidback fanshaped holes). Tests were performed on a five-blade linear cascade in a low-speed wind tunnel. The mainstream Reynolds number based on cascade exit velocity was 5.3 x 10(exp 5). Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. The wake Strouhal number was kept at 0 or 0.1. Coolant blowing ratio was varied from 0.4 to 1.2. Results show that both expanded holes have significantly improved thermal protection over the surface downstream of the ejection location, particularly at high blowing ratios. However, the expanded hole injections induce earlier boundary layer transition to turbulence and enhance heat transfer coefficients at the latter part of the blade suction surface. In general, the unsteady wake tends to reduce film cooling effectiveness.Han, J. C. and Teng, S.Glenn Research CenterHEAT TRANSFER COEFFICIENTS; COOLANTS; TEMPERATURE PROFILES; SUCTION; TURBINE BLADES; HEAT MEASUREMENT; FILM COOLING; BOUNDARY LAYER TRANSITION; CASCADE WIND TUNNELS; CYLINDRICAL BODIES; EJECTION; GAS TURBINES; HOLE DISTRIBUTION (MECHANICS); LIQUID CRYSTALS; LOW SPEED; THERMAL PROTECTION; THERMOCOUPLES; WIND TUNNELS
