0
Research Papers

Comprehensive Application of a First Principles Based Methodology for Design of Axial Compressor Configurations

[+] Author and Article Information
Vishwas Iyengar1

 Southwest Research Institute® , 6220 Culebra Road, San Antonio, TX 78245vishwas.iyengar@swri.org

Lakshmi N. Sankar

 Georgia Institute of Technology, 270 Ferst Drive, Atlanta, GA 30332lsankar@ae.gatech.edu

1

Corresponding author.

J. Turbomach 134(6), 061035 (Sep 12, 2012) (9 pages) doi:10.1115/1.4006301 History: Received July 20, 2011; Revised July 21, 2011; Published September 12, 2012; Online September 12, 2012

Axial compressors are widely used in many aerodynamic applications. The design of an axial compressor configuration presents many challenges. It is necessary to retool the design methodologies to take advantage of the improved accuracy and physical fidelity of these advanced methods. Here, a first-principles based multiobjective technique for designing single stage compressors is described. The study accounts for stage aerodynamic characteristics and rotor-stator interactions. The proposed methodology provides a way to systematically screen through the plethora of design variables. This method has been applied to a rotor-stator stage similar to NASA Stage 35. By selecting the most influential design parameters and by optimizing the blade leading edge and trailing edge mean camber line angles, phenomena such as tip blockages, blade-to-blade shock structures and other loss mechanisms can be weakened or alleviated. It is found that these changes to the configuration can have a beneficial effect on total pressure ratio and stage adiabatic efficiency, thereby improving the performance of the axial compression system.

FIGURES IN THIS ARTICLE
<>
Copyright © 2012 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Flow chart showing the sequence of events in the proposed design methodology

Grahic Jump Location
Figure 2

Summary of parametric blade design based on design variables- aM,N , bM,N

Grahic Jump Location
Figure 3

Schematic diagram showing the interface location used for the aeroacoustic analysis

Grahic Jump Location
Figure 4

Performance map comparing the starting configuration to the optimized configuration

Grahic Jump Location
Figure 5

Adiabatic efficiency map comparing the starting configuration to the optimized configuration

Grahic Jump Location
Figure 6

Rotor blade loading curve comparison at (a) hub, (b) mid span and (c) tip between the starting configuration and optimized configuration

Grahic Jump Location
Figure 7

Stator blade loading curve comparison at (a) hub, (b) mid span and (c) tip between the starting configuration and optimized configuration

Grahic Jump Location
Figure 8

Comparisons of the blade-to-blade pressure fluctuation influencing the rotor-wake/stator interactions aft of the rotor blade at mid span

Grahic Jump Location
Figure 9

Comparisons of the hub-to-tip pressure fluctuations influencing the rotor-wake/stator interactions at rotor-stator interface

Grahic Jump Location
Figure 10

Direction and entropy strength of the rotor leading edge tip vortex

Grahic Jump Location
Figure 11

Entropy (nondimensional) contour comparison between the (a) starting and (b) optimized configurations, for mid passage location at off-design condition

Grahic Jump Location
Figure 12

Entropy (nondimensional) contour comparison between the (a) starting and (b) optimized configurations, for tip clearance section at off-design condition

Grahic Jump Location
Figure 13

Mach number contour comparison between the (a) starting and (b) optimized configurations at 90% span from hub at off-design condition

Grahic Jump Location
Figure 14

Mach number contour comparison between the (a) starting and (b) optimized configurations at tip off-design condition and two meridional planes above 70% span

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In