Investigation Of Advanced Counterrotation Blade Configuration Concepts For High Speed Turboprop Systems Task 4 Advanced Fan Section Aerodynamic Analysis

Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722604516
Total Pages : 78 pages
Book Rating : 4.6/5 (45 download)

DOWNLOAD NOW!

Download or read book Investigation of Advanced Counterrotation Blade Configuration Concepts for High Speed Turboprop Systems. Task 4 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The computer program user's manual for the ADPACAPES (Advanced Ducted Propfan Analysis Code-Average Passage Engine Simulation) program is included. The objective of the computer program is development of a three-dimensional Euler/Navier-Stokes flow analysis for fan section/engine geometries containing multiple blade rows and multiple spanwise flow splitters. An existing procedure developed by Dr. J. J. Adamczyk and associates at the NASA Lewis Research Center was modified to accept multiple spanwise splitter geometries and simulate engine core conditions. The numerical solution is based upon a finite volume technique with a four stage Runge-Kutta time marching procedure. Multiple blade row solutions are based upon the average-passage system of equations. The numerical solutions are performed on an H-type grid system, with meshes meeting the requirement of maintaining a common axisymmetric mesh for each blade row grid. The analysis was run on several geometry configurations ranging from one to five blade rows and from one to four radial flow splitters. The efficiency of the solution procedure was shown to be the same as the original analysis. Crook, Andrew J. and Delaney, Robert A. Unspecified Center...