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The blade angle distribution has been arranged in a manner that it merges with single value at impeller exit.
The static pressure and kinetic energy reaches a peak value at the impeller exit.
Slip factor generally explains the slip effect at the impeller exit and the factor is used to specify theoretical head developed by an impeller (Srinivasan 2008).
Shojaeefard et al. (2012) investigated both experimentally and numerically the effect of impeller exit angle for oil as working fluid and showed that increase of impeller outlet angle leads to improvement in the performance.
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Different from those of the traditional double-suction impeller, the hubs of the tested impellers extend to the impeller outlet.
The numerical simulation focused on the air flow from compressor impeller inlet to volute exit, and the overall performance level and range are predicted.
A limitation of the Euler Turbomachine Equation is that it is based on a finite control volume analysis which prescribes blade angles at the entrance and exit of the impeller, but provides no information on the number or geometry of the blades within the impeller.
According to the simulation results, some useful similarity laws related to the total pressure of the eccentric vortex center, the total pressure rise between the entrance and the exit, and the impeller rotational speed were summarized in this article.
Another limitation of the equation is that it assumes an infinite number of blades of zero thickness that results in uniform flow at the inlet and the exit, while a real impeller has a distinct velocity profile in between each blade that leads to losses not predicted by the equation.
Kamimoto and Matsuoka (1956) experimentally investigated the effect of exit blade angles and reported that the impeller with 30° exit angle has the best performance.
For such impeller configurations, looking from the pump outlet section toward the twin impellers, the blades of both impellers can be aligned along the exit width or staggered.
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Justyna Jupowicz-Kozak
CEO of Professional Science Editing for Scientists @ prosciediting.com