NDLI: Competing 3D Mechanisms in Compressor Flows

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	James, V. Taylor Robert, J. Miller
Copyright Year	2015
Abstract	Even though three-dimensional design is central to all modern compressor design systems, many of these methods still rely, at the their core on a two-dimensional, sectional, view of blade aerodynamics. This paper argues that this view fundamentally limits design by not correctly considering the way in which pressure gradient transverse to the flow direction affects both separation and loss. The first part of the paper details how 3D blade stacking and the transverse pressure gradient fundamentally alters the behaviour of the corner separations and trailing edge separations. By controlling this design parameter it is possible to switch between the two. The transverse pressure gradient is also shown to be responsible for a substantial increase in profile loss. In the second part this understanding is used to explore the uncertainty of the design space by simultaneously varying pitch-chord ratio and 3D stacking. It is shown that the design space is split in half by two different levels of risk.
Sponsorship	International Gas Turbine Institute
File Format	PDF
ISBN	9780791856635
DOI	10.1115/GT2015-43322
Volume Number	Volume 2A: Turbomachinery
Conference Proceedings	ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
Language	English
Publisher Date	2015-06-15
Publisher Place	Montreal, Quebec, Canada
Access Restriction	Subscribed
Subject Keyword	Design Uncertainty Blades Chords (trusses) Switches Aerodynamics Risk Compressors Pressure gradient Separation (technology) Flow (dynamics) Corners (structural elements)
Content Type	Text
Resource Type	Article

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