Fast optimisation of a three-dimensional bypass system using a new aerodynamic design method

F. Barbarossa, M. E. Rife, M. Carnevale, A. B. Parry, J. S. Green, L. Di Mare

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)

Abstract

The propulsive efficiency of civil aviation power plants can be effectively improved by increasing the bypass ratio. Higher bypass ratios, however, exacerbate issues of performance, stability and integrity due to the interaction between the engine pylon, the outlet guide vanes (OGV) and the fan. These issues are due to the distortion of the static pressure field at fan exit due to the presence of the pylon and its transmission through the OGV bladerow and are more pronounced the closer the components of the low pressure compression (LPC) system are. These issues make a rational and effective design of the LPC system of paramount importance for the success of very high-bypass ratio engines. At the preliminary design phase, methods that utilise computational fluid dynamics (CFD) are prohibitively expensive, particularly if they are used as part of optimisation processes involving highly three dimensional, non-axisymmetric OGV designs. An alternative method is being developed exploiting the simplicity and the accuracy of surface singularity element methods to investigate the sensitivity of the bypass system to changes in the design variables. Although the singularity method is based on simplified assumptions of inviscid, incompressible flow, it still performs remarkably well when combined with a tailored optimisation technique. This paper discusses the optimisation framework in detail, including the underlying mathematical models that describe the three-dimensional aerodynamic flowfield as well as the optimisation tools, variables and cost functions used within the optimisation process. The results show that the proposed approach can be used to explore quickly and efficiently a far wider design space than attempted so far in literature. Furthermore, the proposed method leads to non-axysymmetric cascade designs whereby every vane has the same load as the nominal vane whilst greatly reducing the static pressure distortion at fan exit.

Original languageEnglish
Title of host publicationASME Turbo Expo 2017:
Subtitle of host publicationTurbomachinery Technical Conference and Exposition
PublisherAmerican Society of Mechanical Engineers (ASME)
Pages1-10
Number of pages10
Volume2B
ISBN (Electronic)9780791850794
DOIs
Publication statusPublished - 1 Jan 2017
EventASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017 - Charlotte, USA United States
Duration: 26 Jun 201730 Jun 2017

Conference

ConferenceASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
CountryUSA United States
CityCharlotte
Period26/06/1730/06/17

ASJC Scopus subject areas

  • Engineering(all)

Fingerprint Dive into the research topics of 'Fast optimisation of a three-dimensional bypass system using a new aerodynamic design method'. Together they form a unique fingerprint.

Cite this