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Axial-Flow Turbine Rotor Discharge-Flow Overexpansion and Limit-Loading Condition, Part I: Computational Fluid Dynamics (CFD) Investigation
NTRS Full-Text: Click to View  [PDF Size: 15.1 MB]
Author and Affiliation:
Chen, Shu-Cheng S.(NASA Glenn Research Center, Cleveland, OH United States)
Abstract: A Computational Fluid Dynamic (CFD) investigation is conducted over a two-dimensional axial-flow turbine rotor blade row to study the phenomena of turbine rotor discharge flow overexpansion at subcritical, critical, and supercritical conditions. Quantitative data of the mean-flow Mach numbers, mean-flow angles, the tangential blade pressure forces, the mean-flow mass flux, and the flow-path total pressure loss coefficients, averaged or integrated across the two-dimensional computational domain encompassing two blade-passages, are obtained over a series of 14 inlet-total to exit-static pressure ratios, from 1.5 (un-choked; subcritical condition) to 10.0 (supercritical with excessively high pressure ratio.) Detailed flow features over the full domain-of-computation, such as the streamline patterns, Mach contours, pressure contours, blade surface pressure distributions, etc. are collected and displayed in this paper. A formal, quantitative definition of the limit loading condition based on the channel flow theory is proposed and explained. Contrary to the comments made in the historical works performed on this subject, about the deficiency of the theoretical methods applied in analyzing this phenomena, using modern CFD method for the study of this subject appears to be quite adequate and successful. This paper describes the CFD work and its findings.
Publication Date: Jul 13, 2017
Document ID:
20170007293
(Acquired Aug 08, 2017)
Subject Category: FLUID MECHANICS AND THERMODYNAMICS; AIRCRAFT PROPULSION AND POWER; CYBERNETICS, ARTIFICIAL INTELLIGENCE AND ROBOTICS
Report/Patent Number: E-19365, GRC-E-DAA-TN36666, NASA/TM-2017-219506
Document Type: Technical Report
Contract/Grant/Task Num: WBS 081876.02.03.50.04.02
Financial Sponsor: NASA Glenn Research Center; Cleveland, OH United States
Description: 46p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright; Work of the U.S. Government - Public use permitted
NASA Terms: COMPUTATIONAL FLUID DYNAMICS; AXIAL FLOW TURBINES; TURBINE BLADES; SUPERCRITICAL FLOW; CRITICAL FLOW; SUBCRITICAL FLOW; STATIC PRESSURE; MACH NUMBER; FLOW COEFFICIENTS; MASS FLOW; PRESSURE DISTRIBUTION; PRESSURE RATIO; AIRCRAFT ENGINES; MEAN
Other Descriptors: COMPUTATIONAL FLUID DYNAMIC; TURBINE; AXIAL FLOW
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