Abstract
In order to investigate the stage performance of the multistage centrifugal compressor, the stage performance for each stage by using a two-stage test apparatus and the performance in combination of two stages were studied experimentally. The relevance between the flow distortion at the impeller inlet and the overall compressor performance were also studied. By the installation of the inlet casing the flow at the impeller inlet were considerably distorted, however, the differences of the performance in the axial inlet were scarecely indicated. The existence of the guid vane affected the overall compressor performance slightly. The joint shape from the nozzle to the inlet casing had effect on the losses. Total pressure loss coefficients of the inlet casing were almost constant to the inlet flow rate. In the intermediate stage the effect of the flow passage of the return channel was not noticed remarkably in the range of small flow rate. The flow at the return channel outlet was distorted compared to that of the axial inlet. However, the flow distortion index by the flow passage to the impellers was almost the same as that obtained from the axial inlet stage excluding the case of large flow rate, and the performance
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Citation Formats
Harada, Hideomi.
Experimental study on the stage performance of a multistage centrifugal compressor.
Japan: N. p.,
1988.
Web.
Harada, Hideomi.
Experimental study on the stage performance of a multistage centrifugal compressor.
Japan.
Harada, Hideomi.
1988.
"Experimental study on the stage performance of a multistage centrifugal compressor."
Japan.
@misc{etde_7030222,
title = {Experimental study on the stage performance of a multistage centrifugal compressor}
author = {Harada, Hideomi}
abstractNote = {In order to investigate the stage performance of the multistage centrifugal compressor, the stage performance for each stage by using a two-stage test apparatus and the performance in combination of two stages were studied experimentally. The relevance between the flow distortion at the impeller inlet and the overall compressor performance were also studied. By the installation of the inlet casing the flow at the impeller inlet were considerably distorted, however, the differences of the performance in the axial inlet were scarecely indicated. The existence of the guid vane affected the overall compressor performance slightly. The joint shape from the nozzle to the inlet casing had effect on the losses. Total pressure loss coefficients of the inlet casing were almost constant to the inlet flow rate. In the intermediate stage the effect of the flow passage of the return channel was not noticed remarkably in the range of small flow rate. The flow at the return channel outlet was distorted compared to that of the axial inlet. However, the flow distortion index by the flow passage to the impellers was almost the same as that obtained from the axial inlet stage excluding the case of large flow rate, and the performance of the following stage was not lowered. (16 figs, 2 refs)}
journal = []
volume = {54:498}
journal type = {AC}
place = {Japan}
year = {1988}
month = {Feb}
}
title = {Experimental study on the stage performance of a multistage centrifugal compressor}
author = {Harada, Hideomi}
abstractNote = {In order to investigate the stage performance of the multistage centrifugal compressor, the stage performance for each stage by using a two-stage test apparatus and the performance in combination of two stages were studied experimentally. The relevance between the flow distortion at the impeller inlet and the overall compressor performance were also studied. By the installation of the inlet casing the flow at the impeller inlet were considerably distorted, however, the differences of the performance in the axial inlet were scarecely indicated. The existence of the guid vane affected the overall compressor performance slightly. The joint shape from the nozzle to the inlet casing had effect on the losses. Total pressure loss coefficients of the inlet casing were almost constant to the inlet flow rate. In the intermediate stage the effect of the flow passage of the return channel was not noticed remarkably in the range of small flow rate. The flow at the return channel outlet was distorted compared to that of the axial inlet. However, the flow distortion index by the flow passage to the impellers was almost the same as that obtained from the axial inlet stage excluding the case of large flow rate, and the performance of the following stage was not lowered. (16 figs, 2 refs)}
journal = []
volume = {54:498}
journal type = {AC}
place = {Japan}
year = {1988}
month = {Feb}
}