Investigation of Flow Phenomena in a Transonic Fan Rotor Using Laser AnemometrySource: Journal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002::page 427Author:A. J. Strazisar
DOI: 10.1115/1.3239743Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Several flow phenomena, including flow field periodicity, rotor shock oscillation, and rotor shock system geometry have been investigated in a transonic low aspect ratio fan rotor using laser anemometry. Flow periodicity is found to increase with increasing rotor pressure rise and to correlate with blade geometry variations. Analysis of time-accurate laser anemometer data indicates that the rotor shock oscillates about its mean location with an amplitude of 3–4 percent of rotor chord. The shock surface is nearly two-dimensional for levels of rotor pressure rise at and above the peak efficiency level but becomes more complex for lower levels of pressure rise. Spanwise shock lean generates radial flows due to streamline deflection in the hub-to-shroud streamsurface.
keyword(s): Flow (Dynamics) , Lasers , Rotors , Shock (Mechanics) , Pressure , Geometry , Radial flow , Oscillations , Blades , Deflection AND Chords (Trusses) ,
|
Show full item record
contributor author | A. J. Strazisar | |
date accessioned | 2017-05-08T23:20:12Z | |
date available | 2017-05-08T23:20:12Z | |
date copyright | April, 1985 | |
date issued | 1985 | |
identifier issn | 1528-8919 | |
identifier other | JETPEZ-26618#427_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/99842 | |
description abstract | Several flow phenomena, including flow field periodicity, rotor shock oscillation, and rotor shock system geometry have been investigated in a transonic low aspect ratio fan rotor using laser anemometry. Flow periodicity is found to increase with increasing rotor pressure rise and to correlate with blade geometry variations. Analysis of time-accurate laser anemometer data indicates that the rotor shock oscillates about its mean location with an amplitude of 3–4 percent of rotor chord. The shock surface is nearly two-dimensional for levels of rotor pressure rise at and above the peak efficiency level but becomes more complex for lower levels of pressure rise. Spanwise shock lean generates radial flows due to streamline deflection in the hub-to-shroud streamsurface. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Investigation of Flow Phenomena in a Transonic Fan Rotor Using Laser Anemometry | |
type | Journal Paper | |
journal volume | 107 | |
journal issue | 2 | |
journal title | Journal of Engineering for Gas Turbines and Power | |
identifier doi | 10.1115/1.3239743 | |
journal fristpage | 427 | |
journal lastpage | 435 | |
identifier eissn | 0742-4795 | |
keywords | Flow (Dynamics) | |
keywords | Lasers | |
keywords | Rotors | |
keywords | Shock (Mechanics) | |
keywords | Pressure | |
keywords | Geometry | |
keywords | Radial flow | |
keywords | Oscillations | |
keywords | Blades | |
keywords | Deflection AND Chords (Trusses) | |
tree | Journal of Engineering for Gas Turbines and Power:;1985:;volume( 107 ):;issue: 002 | |
contenttype | Fulltext |