Author: Kjell IsaksenPublisher:
ISBN:
Category :
Languages : en
Pages : 146
Book Description
An Investigation of Rotating Stall in a Single Stage Compressor
Author: Kjell IsaksenInvestigation of Rotating Stall in a Single-stage Axial Compressor
Author: S. R. MontgomeryPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 28
Book Description
The rotating-stall characteristics of a single-stage axial-flow compressor were investigated. The number of stall cells and their propagation velocities were found with and without stator blades. The measured velocities were compared with those predicted by Stenning's theory (see NACA TN 3580), assuming the dounstream pressure fluctuations to be negligible, and correlation within 10 percent was obtained at the onset of stall. It was found that the pressure fluctuations cauased by rotating stall were less downstream of the rotor than upstream; the minimum reduction across the rotor was 40 percent with stator blades and 75 percent without stator blades. It was also that, for the compressor tested, the stator blades decreased the number of stall cells and tended to induce rotating stall at larger mass flow rates.
Investigation of Rotating Stall in a Single Stage Axial Compressor
Author: Massachusetts Institute of Technology. Gas Turbine LaboratoryPublisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 31
Book Description
Rotating Stall Investigation of the 0.72 Hub-tip Ratio Single-stage Compressor
Author: Robert W. GrahamPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 30
Book Description
Experimental Investigation of the Rotating Stall in a Single Stage Axial Compressor
Author: Jacques ValensiExperimental and Theoretical Investigation of Rotating-stall Characteristics of Single-stage Axial-flow Compressor with Hub-tip Ratio of 0.76
Author: Robert W. GrahamStudies in the Control of Rotating Stall in a Single Stage Axial Compressor
Author: Huajun LiuAnalytical and Experimental Investigation of Rotating Stall Phenomena in Turbine Engine Compressors
Author: The Effect of Reynolds Number on Rotating Stall in a Single Stage Axial Compressor
Author: James Rosholt CoultDimension Determination of Precursive Stall Events in a Single Stage High Speed Compressor
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781725675087
Category :
Languages : en
Pages : 30
Book Description
This paper presents a study of the dynamics for a single-stage, axial-flow, high speed compressor core, specifically, the NASA Lewis rotor stage 37. Due to the overall blading design for this advanced core compressor, each stage has considerable tip loading and higher speed than most compressor designs, thus, the compressor operates closer to the stall margin. The onset of rotating stall is explained as bifurcations in the dynamics of axial compressors. Data taken from the compressor during a rotating stall event is analyzed. Through the use of a box-assisted correlation dimension methodology, the attractor dimension is determined during the bifurcations leading to rotating stall. The intent of this study is to examine the behavior of precursive stall events so as to predict the entrance into rotating stall. This information may provide a better means to identify, avoid or control the undesirable event of rotating stall formation in high speed compressor cores. Bright, Michelle M. and Qammar, Helen K. and Hartley, Tom T. Unspecified Center NASA-TM-107268, E-10335, NAS 1.15:107268 RTOP 505-62-50...