Investigation of Low-capacity High-pressure Stages of Centrifugal Compressors PDF Download
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Author: S. A. Anisimov Publisher: ISBN: Category : Languages : en Pages : 26
Book Description
In view of the importance to contemporary turbocompressor design of increasing the efficiency of low-capacity, high-pressure, centrifugal compressors, and the difficulties engendered by the small discharge volumes, the paper summarizes and evaluates the results obtained in tests of such compressor stages. Tests were carried out on 9 configurations of intermediate stages (impeller-diffuser-return bend and channel) and 3 configurations of terminal stages (impeller-diffuser). All the impellers had a relative width b2/D2 of approximately 0.02; the intermediate stage impellers had a diameter D2 of 352 mm and were tested at tip speeds of 300-315 m/sec., while the terminal stage impellers were 220-256 mm in diameter and were tested at 196-229 m/sec. Three types of diffusers (channeled, vaned and vaneless) were used for the intermediate stages, while the terminal stages were tested only with vaned diffusers. The effectiveness of a particular stage was evaluated on the basis of the stage efficiency, impeller efficiency, diffuser efficiency, stage pressure coefficient, stage pressure ratio, impeller pressure ratio, drag coefficient of the stationary parts, relative loss coefficient of the stagnation pressure, degree of reaction, Mach number, Reynolds number, flow coefficient, discharge rate and the angles of incidence of flow. (Author).
Author: S. A. Anisimov Publisher: ISBN: Category : Languages : en Pages : 26
Book Description
In view of the importance to contemporary turbocompressor design of increasing the efficiency of low-capacity, high-pressure, centrifugal compressors, and the difficulties engendered by the small discharge volumes, the paper summarizes and evaluates the results obtained in tests of such compressor stages. Tests were carried out on 9 configurations of intermediate stages (impeller-diffuser-return bend and channel) and 3 configurations of terminal stages (impeller-diffuser). All the impellers had a relative width b2/D2 of approximately 0.02; the intermediate stage impellers had a diameter D2 of 352 mm and were tested at tip speeds of 300-315 m/sec., while the terminal stage impellers were 220-256 mm in diameter and were tested at 196-229 m/sec. Three types of diffusers (channeled, vaned and vaneless) were used for the intermediate stages, while the terminal stages were tested only with vaned diffusers. The effectiveness of a particular stage was evaluated on the basis of the stage efficiency, impeller efficiency, diffuser efficiency, stage pressure coefficient, stage pressure ratio, impeller pressure ratio, drag coefficient of the stationary parts, relative loss coefficient of the stagnation pressure, degree of reaction, Mach number, Reynolds number, flow coefficient, discharge rate and the angles of incidence of flow. (Author).
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781726206143 Category : Languages : en Pages : 28
Book Description
Compressor stall is a catastrophic breakdown of the flow in a compressor, which can lead to a loss of engine power, large pressure transients in the inlet/nacelle and engine flameout. The implementation of active or passive strategies for controlling rotating stall and surge can significantly extend the stable operating range of a compressor without substantially sacrificing performance. It is crucial to identify the dynamic changes occurring in the flow field prior to rotating stall and surge in order to successfully control these events. Generally, pressure transducer measurements are made to capture the transient response of a compressor prior to rotating stall. In this investigation, Digital Particle Imaging Velocimetry (DPIV) is used in conjunction with dynamic pressure transducers to simultaneously capture transient velocity and pressure measurements in the non-stationary flow field during compressor surge. DPIV is an instantaneous, planar measurement technique which is ideally suited for studying transient flow phenomena in high speed turbomachinery and has been used previously to successfully map the stable operating point flow field in the diffuser of a high speed centrifugal compressor. Through the acquisition of both DPIV images and transient pressure data, the time evolution of the unsteady flow during surge is revealed.Wernet, Mark P. and Bright, Michelle M. and Skoch, Gary J.Glenn Research CenterCENTRIFUGAL COMPRESSORS; ROTATING STALLS; PARTICLE IMAGE VELOCIMETRY; PRESSURE MEASUREMENT; DYNAMIC PRESSURE; PRESSURE SENSORS; TRANSIENT PRESSURES; UNSTEADY FLOW...
Author: S. A. Anisimov
Author: S. A. Anisimov
Author: Gene Thomas Colwell
Author: Thomas Barker Ferguson
Author: National Aeronautics and Space Administration (NASA)
Author: Raymond M. Standahar
Author: Edward Thomas Faulkner
Author: Ted F. McKain
Author: John R. Erwin
Author: Edmund A. Memmott
Author: Rodrigo Rodriguez Erdmenger