Accession Number : ADA232989


Title :   Unsteady Viscous Flow in a High Speed Core Compressor


Descriptive Note : Technical memo.


Corporate Author : ROYAL AEROSPACE ESTABLISHMENT FARNBOROUGH (UNITED KINGDOM)


Personal Author(s) : Cherrett, M A ; Bryce, J D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a232989.pdf


Report Date : Dec 1990


Pagination or Media Count : 13


Abstract : A probe incorporating a miniature high-frequency response pressure transducer has been traversed behind the first three stages of a high-speed multistage compressor operating at throttle settings corresponding to near choke, peak efficiency and near surge. A novel method of compensating for transducer temperature sensitivity was employed. Consequently, time-averaged pressures derived from the transducer were found to be in good agreement with pneumatic pressure measurements. Analysis of the unsteady pressure measurements revealed both the periodic and random fluctuations in the flowfield. This provided information on rotor-rotor interaction effects and the nature of viscous blade wake and secondary flows in each stage.


Descriptors :   *PERIODIC VARIATIONS , UNITED KINGDOM , HIGH RATE , CORES , RANDOM VARIABLES , EFFICIENCY , BLADES , SENSITIVITY , TIME , FLOW FIELDS , PRESSURE , WAKE , TRANSDUCERS , MEAN , UNSTEADY FLOW , COMPRESSORS , COMPENSATION , SURGES , VISCOUS FLOW , STAGING , PNEUMATIC EQUIPMENT , SECONDARY FLOW , PEAK VALUES , TEMPERATURE


Subject Categories : Fluid Mechanics
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE