CaltechAUTHORS
  A Caltech Library Service

Performance of Axial Compressors with Asymmetric Inlet Flows

Katz, Robert (1958) Performance of Axial Compressors with Asymmetric Inlet Flows. California Institute of Technology , Pasadena, CA. (Unpublished) http://resolver.caltech.edu/CaltechAUTHORS:20151105-165306203

[img] PDF - Submitted Version
See Usage Policy.

16Mb

Use this Persistent URL to link to this item: http://resolver.caltech.edu/CaltechAUTHORS:20151105-165306203

Abstract

An experimental and analytical investigation was undertaken to determine the influence of asymmetric inlet flows on the performance of axial turbomachinery. Overall performance measurements and circumferential surveys of total pressures, velocities and flow angles were obtained in an axial compressor with inlet disturbances covering approximately 25% of the inlet annulus area. Three configurations were tested to find the principal effects in a single rotor, a complete stage and a multi-stage machine. A two-dimensional linearized theory was developed which includes the effect of losses and leaving angle deviations in the blade rows. The analysis may also be applied to propagating stall so that this theory allows a unified treatment of the two phenomena. Introducing the inlet disturbances did not alter the two-dimensional character of the flow in the compressor. Considerable attenuation of the disturbances occurred through a single rotor and the disturbances were almost completely attenuated downstream of a three stage configuration. The mutual interference of the blade rows with small axial spacing was responsible for significant stator losses. The overall performance deteriorated primarily due to losses occurring in the blade rows. In the three configurations tested the inception of propagating stall, as based on the mean flow rate, was essentially unchanged. The theory qualitatively described the flow behavior and a simple application of the theory would give an estimate of the blade forces.


Item Type:Report or Paper (Technical Report)
Additional Information:Final Report. Supported through Contract AF 18(600)-178 Office of Scientific Research Air Research and Development Command. AFOSR TR-58-89 AD 162 112.
Group:Guggenheim Jet Propulsion Center
Funders:
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)AF 18(600)-178
Record Number:CaltechAUTHORS:20151105-165306203
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:20151105-165306203
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:61921
Collection:CaltechAUTHORS
Deposited By: Kristin Buxton
Deposited On:06 Nov 2015 19:50
Last Modified:06 Nov 2015 19:50

Repository Staff Only: item control page