NDLI: Numerical Investigation of End Wall Boundary Layer Removal on Highly Loaded Axial Compressor Blade Rows

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Gümmer, V. Goller, M. Swoboda, M.
Copyright Year	2008
Abstract	This paper presents results of numerical investigations carried out to explore the benefit of end wall boundary layer removal from critical regions of highly loaded axial compressor blade rows. At the loading level of modern aero engine compressors, the performance is primarily determined by three-dimensional (3D) flow phenomena occurring in the end wall regions. Three-dimensional Navier–Stokes simulations were conducted on both a rotor and a stator test case in order to evaluate the basic effects and the practical value of bleeding air from specific locations at the casing end wall. The results of the numerical survey demonstrated substantial benefits of relatively small bleed rates to the local flow field and to the performance of the two blade rows. On the rotor, the boundary layer fluid was removed from the main flow path through an axisymmetric slot in the casing over the rotor tip. This proved to give some control over the tip leakage vortex flow and the associated loss generation. On the stator, the boundary layer fluid was taken from the flow path through a single bleed hole within the passage. Two alternative off-take configurations were evaluated, revealing a large impact of the bleed hole shape and the location on the cross-passage flow and the suction side corner separation. On both blade rows investigated, rotor and stator, the boundary layer removal resulted in a reduction of the local reverse flow, blockage, and losses in the respective near-casing region. This paper gives insight into changes occurring in the 3D passage flow field near the casing and summarizes the effects on the radial matching and pitchwise-averaged performance parameters, namely loss and deviation of the rotor and stator when suction is active. Primary focus is put on the aerodynamics in the blade rows in the main flow path; details of the internal flow structure within the bleed off-take cavities/ports are not discussed here.
Starting Page	011015
Ending Page	011019
Page Count	5
File Format	PDF
ISSN	0889504X
e-ISSN	15288900
Journal	Journal of Turbomachinery
Volume Number	130
Issue Number	1
DOI	10.1115/1.2749297
Language	English
Publisher	The American Society of Mechanical Engineers
Publisher Date	2008-01-25
Access Restriction	Subscribed
Subject Keyword	Airfoils Blades Boundary layers Clearances (Engineering) Compressors Corners (Structural elements) Design Engineering simulation Flow (Dynamics) Fluids Leakage Rotors Separation (Technology) Stators Suction
Content Type	Text
Resource Type	Article
Subject	Mechanical Engineering

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Numerical Investigation of Endwall Boundary Layer Removal on Highly-Loaded Axial Compressor Blade Rows

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