Download or read book Secondary Flow Total Pressure Loss and the Effect of Circumferential Distortions in Axial Turbine Cascades written by Earl William Renaud and published by . This book was released on 1991 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Aerodynamic Unsteadiness in Axial Turbomachines written by R. Dénos and published by . This book was released on 2005 with total page 632 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1979 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Download or read book 30th AIAA ASME SAE ASEE Joint Propulsion Conference written by and published by . This book was released on 1994 with total page 728 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reduction of Secondary Flow Losses in a Turbine for Use in Man portable Power Generation written by Andrew J. Yatsko and published by . This book was released on 2014 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: As the world has moved into a more energy-demanding environment, there has been the push for higher energy density in a smaller package. One of the potential solutions is through the application of a gas turbine engine; yet the challenge is extracting the energy efficiently through the small components. The focus of the research is on the turbine components and how secondary flow losses from generated airfoil shapes can be reduced to improve component performance. One of the secondary flow loss items to be addressed is the generation of the Horseshoe Vortex. The Horseshoe Vortex is an aerodynamic phenomenon that occurs in axial turbine cascades that degrades the aerodynamic performance. This research will show that through airfoil design optimization, the Horseshoe Vortex on small turbine nozzles can be reduced. The initial turbine design was generated using simple imcompressible flow calculations and then run through a Navier-Strokes SST solver. This solver allows for the interaction of the boundary layer with the airfoil geometry, therefore generating a new set of inlet velocity triangles. The geometry was then optimized to match the new inlet velocity triangle. The new optimized airfoil was run through the same boundary layer build up, and the same boundary conditions as the original incompressible design. The presented results will show that the Horseshoe Vortex has been mitigated and that the total pressure distribution at the exit of the turbine inlet nozzle cascade has improved by 7.6%.
Download or read book Study of Secondary flow Patterns in an Annular Cascade of Turbine Nozzle Blades with Vortex Design written by Harold E. Rohlik and published by . This book was released on 1953 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: In order to increase understanding of the origin of losses in a turbine, the secondary-flow components in the boundary layers and the blade wakes of an annular cascade of turbine nozzle blades (vortex design) were investigated. A detailed study was made of the total-pressure contours and, particularly, of the inner-wall loss cores down-stream of the blades.
Download or read book Secondary Flows and Inlet Skew in Axial Flow Turbine Cascades written by J. A. Walsh and published by . This book was released on 1987 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Investigation of Loss in an Annular Cascade of Turbine nozzle Blades of Free Vortex Design written by Hubert W. Allen and published by . This book was released on 1953 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the flow pattern immediately downstream of an annular cascade of nozzle blades designed for vortex-type velocity distribution and hub discharge angle of approximately 65 degrees from axial was conducted in order to obtain a better understanding of the processes by which the distribution of losses and deviations from design turning angle occur. For the two Mach numbers investigated, the loass region at the outer shroud decreased while that at the inner shroud increased with increasing Mach number.
Download or read book Dissertation Abstracts International written by and published by . This book was released on 1992 with total page 830 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Invesitgation of Losses and Secondary Flow Turbine Cascades written by Wishaa Mohammed Hosny and published by . This book was released on 1971 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book On the Experimental Evaluation of Loss Production and Reduction in a Highly Loaded Low Pressure Turbine Cascade written by Philip Steven Bear and published by . This book was released on 2016 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: Improvements in turbine design methods have resulted in the development of blade profiles with both high lift and good Reynolds lapse characteristics. An increase in aerodynamic loading of blades in the low pressure turbine section of aircraft gas turbine engines has the potential to reduce engine weight or increase power extraction. Increased blade loading means larger pressure gradients and increased secondary losses near the endwall. Prior work has emphasized the importance of reducing these losses if highly loaded blades are to be utilized. The present study analyzes the secondary flow field of the front-loaded low-pressure turbine blade designated L2F with and without blade profile contouring at the junction of the blade and endwall. The current work explores the loss production mechanisms inside the low pressure turbine cascade. Stereoscopic particle image velocimetry data, total pressure loss data and oil flow visualization are used to describe the secondary flow field. The flow is analyzed in terms of total pressure loss, vorticity, Q-Criterion, Reynolds' stresses, turbulence intensity and turbulence production. The flow description is then expanded upon using an Implicit Large Eddy Simulation of the flow field. The RANS momentum equations contain terms with static pressure derivatives. With some manipulation these equations can be rearranged to form an equation for the change in total pressure along a streamline as a function of velocity only. After simplifying for the flow field in question the equation can be interpreted as the total pressure transport along a streamline. A comparison of the total pressure transport calculated from the velocity components and the total pressure loss is presented and discussed. Peak values of total pressure transport overlap peak values of total pressure loss through and downstream of the passage suggesting that total pressure transport is a useful tool for localizing and predicting loss origins and loss development using velocity data which can be obtained non-intrusively.
Download or read book ASME Technical Papers written by and published by . This book was released on 2000 with total page 574 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1976 with total page 990 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Secondary Flows and Losses in a Turbine Cascade written by D. G. Gregory-Smith and published by . This book was released on 1983 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: In designing axial flow turbines, one needs relatively simple prediction techniques for the angle variations and losses produced by secondary flows. To improve the physical basis of such techniques, an investigation was made of the flow in a cascade of large scale rotor blades of some 110 deg of turning. The aspect around 0.2 of the span. The flow was traversed in great detailed on ten planes using cobra-type probes with a computerised data recording and analysis system. Results are presented graphically using contour and vector plots on various planes through the flow field. The horse-show vortex and passage vortex development are clearly seen, with the upstream boundary layer being shed downstream as a loss core. Another region of high loss is related to a counter vortex in the corner between the sunction surface and the end wall. Results were also pitch averaged, and compared with predictions of angle and loss distribution. Some traversing was carried out using hot wire anemometry. Regions of high turbulence intensity and shear stress were identified, associated with the regions of high loss. Some indication is given of the mechanisms of loss production within the cascade.
Download or read book Paper written by and published by . This book was released on 2000 with total page 576 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Radial Flow Turbocompressors written by Michael Casey and published by Cambridge University Press. This book was released on 2021-06-10 with total page 789 pages. Available in PDF, EPUB and Kindle. Book excerpt: An introduction to the theory and engineering practice that underpins the component design and analysis of radial flow turbocompressors. Drawing upon an extensive theoretical background and years of practical experience, the authors provide descriptions of applications, concepts, component design, analysis tools, performance maps, flow stability, and structural integrity, with illustrative examples. Features wide coverage of all types of radial compressor over many applications unified by the consistent use of dimensional analysis. Discusses the methods needed to analyse the performance, flow, and mechanical integrity that underpin the design of efficient centrifugal compressors with good flow range and stability. Includes explanation of the design of all radial compressor components, including inlet guide vanes, impellers, diffusers, volutes, return channels, de-swirl vanes and side-streams. Suitable as a reference for advanced students of turbomachinery, and a perfect tool for practising mechanical and aerospace engineers already within the field and those just entering it.
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1999 with total page 1020 pages. Available in PDF, EPUB and Kindle. Book excerpt:
