Download or read book Three Dimensional Rotational Inviscid Flow Calculation in Axial Turbine Blade Rows written by Tony Arts and published by . This book was released on 1985 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Calculation of Three dimensional Inviscid Rotational Flow in Axial Turbine Blade Rows written by W. Van Hove and published by . This book was released on 1983 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Quasi three dimensional Method for Calculating Blade Surface Velocities for an Axial Flow Turbine Blade written by Theodore Katsanis and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A FORTRAN Program for Calculating Three dimensional Inviscid Rotational Flows with Shock Waves in Axial Compressor Blade Rows written by William T. Thompkins and published by . This book was released on 1981 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: A FORTRAN-IV computer program has been developed for the calculation of the inviscid transonic/supersonic flow field in a fully three-dimensional blade passage of an axial compressor rotor or stator. Rotors may have dampers (part-span shrouds). MacCormack's explicit time-marching method is used to solve the unsteady Euler equations on a finite difference mesh. This technique captures shocks and smears them over several grid points. Input quantities are blade row geometry, operating conditions and thermodynamic quantities. Output quantities are three velocity components, density and internal energy at each mesh point. Other flow quantities are calculated from these variables. A short graphics package is included with the code, and may be used to display the finite difference grid, blade geometry and static pressure contour plots on blade-to-blade calculation surfaces or blade suction and pressure surfaces. Flows in four transonic compressor rotors have been analyzed and compared with exit flow field measurements and intra-blade static density measurements obtained with a gas fluorescence technique. These comparisons have generally shown that the computed flow fields accurately model the experimentally determined passage shock positions and overall aerodynamic performance. The computer code was developed and generally run on a large minicomputer system, a Digital Equipment Corporation PDP-ll/70, with run times of two to three days. The code has also been run on several main-frame computers (IBM 3033, IBM 360/678, UNIVAC 1110, CDC 7600 and a CRAY-1). Typical run times on an IBM 3033 have been found to be 5-10 hours.
Download or read book Computational Fluid Dynamics Techniques written by Fathi Habashi and published by CRC Press. This book was released on 1995-11-22 with total page 930 pages. Available in PDF, EPUB and Kindle. Book excerpt: First published in 1995. Routledge is an imprint of Taylor & Francis, an informa company.
Download or read book Calculation of the Three dimensional Steady Inviscid Flow in a Transonic Axial Turbine Stage written by T. Arts and published by . This book was released on 1984 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Three Dimensional Inviscid Compressible Calculations Around Axial Flow Turbine Blades written by A. Fourmaux and published by . This book was released on 1991 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Boundary Elements VIII written by Masataka Tanaka and published by Springer Science & Business Media. This book was released on 2013-11-11 with total page 414 pages. Available in PDF, EPUB and Kindle. Book excerpt: The International Conference on Boundary Element Methods in Engineering was started in 1978 with the following objectives: i) To act as a focus for BE research at a time when the technique wasjust emerging as a powerful tool for engineering analysis. ii) To attract new as weIl as established researchers on Boundary Elements, in order to maintain its vitality and originality. iii) To try to relate the Boundary Element Method to other engineering techniques in an effort to help unify the field of engineering analysis, rather than to contribute to its fragmentation. These objectives were achieved during the last 7 conferences and this meeting - the eighth - has continued to be as innovative and dynamic as any ofthe previous conferences. Another important aim ofthe conference is to encourage the participation of researchers from as many different countries as possible and in this regard it is a policy of the organizers to hold the conference in different locations. It is easy to forget when working on scientific projects that in science as weIl as in other subjects, human relationships are as important as mathematical equations. Science progresses not only as a resuIt oflaboratory and computer experiments or abstract thinking but also by a process of personal interaction.
Download or read book A Comparison Study of Three dimensional Analysis Techniques and Loss Calculations for Axial Flow Turbines written by Richard James Timm and published by . This book was released on 1972 with total page 472 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 1968 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Three Dimensional Inviscid Effects and Limitations of Cascade Theory in Axial Flow Turbomachinery written by A. Tamura and published by . This book was released on 1974 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt: The general objective of the investigation reported in this thesis is to obtain a reliable understanding of the three dimensional potential flow through axial flow turbomachinery. The calculation of the three dimensional potential flow through an impeller is based on the method of distributed singularities. The blades are replaced by a series of line vortices and line sources which have their axes along the radial direction and are arranged along the blade camber surface. The basic perturbed velocity fields due to a single radial vortex line of constant strength and a single radial source line of variable strength along the radial direction are computed from a modified theory based on Tyson's and Rossow's formulation. Since the resultant perturbed flow fields are solutions of the linear Laplace equation and the boundary conditions are homogeneous, these solutions may be superimposed for a series of radial vortex lines and source lines located at arbitrary points. Eigen values and related functions are calculated for Bessel function of order m = 0 to 100, number of eigen values for each order of Bessel function n - 20, hub-to-tip ratio nu = 0.3, 0.6. A computer program to obtain the three dimensional flow field in a turbomachinery with arbitrary number of blades, number of singular points per blade, and singular points locations was developed. Examples illustrating the interference effects due to hub-to-tip ratio, stagger angle, numbers of the blades were carried out. The effects of the radial variation of the strength of the radial source line were examined. The three dimensional effects are found to be appreciable for low hub tip configuration with fewer number of blades. (Author).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 456 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 The Calculation of Three Dimensional Viscous Flow Through Multistage Turbomachines written by J. D. Denton and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The extension of a well-established three-dimensional flow calculation method to calculate the flow through multiple turbomachinery blade rows is described in this paper. To avoid calculating the unsteady flow, which is inherent in any machine containing both rotating and stationary blade rows, a mixing process is modeled at a calculating station between adjacent blade rows. The effects of this mixing on the flow within the blade rows may be minimized by using extrapolated boundary conditions at the mixing plane. Inviscid calculations are not realistic for multistage machines and so the method includes a range of options for the inclusion of viscous effects. At the simplest level such effects may be included by prescribing the spanwise variation of polytropic efficiency for each blade row. At the most sophisticated level viscous effects and machine performance can be predicted by using a thin shear layer approximation to the Navier-Stokes equations and an eddy viscosity turbulence model. For high-pressure-ratio compressors there is a strong tendency for the calculation to surge during the transient part of the flow. This is overcome by the use of a new technique, which enables the calculation to be run to a prescribed mass flow. Use of the method is illustrated by applying it to a multistage turbine of simple geometry, a two-stage low-speed experimental turbine, and two multistage axial compressors.
Download or read book Effects of a Skewed Inlet End Wall Boundary Layer on the 3 D Flow Field in an Annular Turbine Cascade written by E. Boletis and published by . This book was released on 1983 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents results of an experimental investigation on the effect of a skewed inlet boundary layer on the flow field in a low speed, low aspect ratio, high turning annular turbine nozzle guide vane. Three test series, differing by their degree of inlet skew, were performed. The flow was explored by means of double head four hole pressure probes in five axial planes from upstream to far downstream of the blade row. Results are presented in the form of contour plots and spanwise pitch-averaged distributions. The axial evolution of the measured pitch-averaged spanwise flow angle distribution is compared with a three dimensional, inviscid, rotational flow calculation.
Download or read book Secondary Flows and Endwall Boundary Layers in Axial Turbomachines written by and published by . This book was released on 1984 with total page 534 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ASME Technical Papers written by and published by . This book was released on 1985 with total page 940 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book COSMIC Software Catalog written by and published by . This book was released on 1987 with total page 444 pages. Available in PDF, EPUB and Kindle. Book excerpt:
