0
TECHNICAL PAPERS

An Approach to Integrated Multi-Disciplinary Turbomachinery Design

[+] Author and Article Information
Jerome P. Jarrett1

Department of Engineering, University of Cambridge, Trumpington Street, Cambridge CB2 1PZ, United Kingdomjpj1001@cam.ac.uk

William N. Dawes, P. John Clarkson

Department of Engineering, University of Cambridge, Trumpington Street, Cambridge CB2 1PZ, United Kingdom

1

Lead and Corresponding Author: Tel: +44-1223-332552

J. Turbomach. 129(3), 488-494 (Aug 18, 2006) (7 pages) doi:10.1115/1.2472416 History: Received February 10, 2006; Revised August 18, 2006

Aeroengines are designed using fractured processes. Complexity has driven the design of such machines to be subdivided by specialism, customer, and function. While this approach has worked well in the past, with component efficiencies, current material performance, and the possibilities presented by scaling existing designs for future needs becoming progressively exhausted, it is necessary to reverse this process of disintegration. Our research addresses this aim. The strategy we use has two symbiotic arms. The first is an open data architecture from which existing disparate design codes all derive their input and to which all send their output. The second is a dynamic design process management system known as “SignPosting.” Both the design codes and parameters are arranged into complementary multiple level hierarchies: fundamental to the successful implementation of our strategy is the robustness of the mechanisms we have developed to ensure consistency in this environment as the design develops over time. One of the key benefits of adopting a hierarchical structure is that it confers not only the ability to use mean-line, throughflow, and fully 3D computational fluid dynamics techniques in the same environment, but also to cross specialism boundaries and to insert mechanical, material, thermal, electrical, and structural codes, enabling exploration of the design space for multi-disciplinary nonlinear responses to design changes and their exploitation. We present results from trials of an early version of the system applied to the redesign of a generic civil aeroengine core compressor. SignPosting has allowed us to examine the hardness of design constraints across disciplines which has shown that it is far more profitable not to strive for even higher aerodynamic performance, but rather to improve the commercial performance by maintaining design and part-speed pressure ratio stability and efficiency while increasing rotor blade creep life by up to 70%.

FIGURES IN THIS ARTICLE
<>
Copyright © 2007 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

The development of non-compounded steam turbines, 1884–1930 (4)

Grahic Jump Location
Figure 2

The classic optimization problem

Grahic Jump Location
Figure 3

The jet engine detailed design problem

Grahic Jump Location
Figure 4

Plotting user variable vectors

Grahic Jump Location
Figure 5

Choosing the direction in which to move

Grahic Jump Location
Figure 6

The SignPosting system for turbomachinery

Grahic Jump Location
Figure 7

SignPosting redesign overlaid on the datum main gas path geometry

Grahic Jump Location
Figure 8

Mechanical redesign

Grahic Jump Location
Figure 9

Aerodynamic redesign

Grahic Jump Location
Figure 10

Illustrative Smith Chart

Grahic Jump Location
Figure 11

Effect on aerodynamic performance

Grahic Jump Location
Figure 12

Evidence of orthogonal design

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.

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