Interface Treatment for Harmonic Solution in Multi-Row Aeromechanic Analysis

Mohammad Rahmati, L. He, R. G. Wells

Research output: Chapter in Book/Report/Conference proceedingChapterpeer-review

16 Citations (Scopus)

Abstract

In the present work, an interface treatment method has been developed to extend a non-linear harmonic solution method for aeromechanic analysis in multiple blade row configurations. The main emphasis is two folds. Firstly the method will enable efficient and accurate analysis of blade aerodynamic forcing and damping characteristics under the influence of adjacent bladerows. Secondly, it will warrant that the same steady/mean base flow as defined by the aerothermal designers is used consistently in the aeromechanical analysis. For passing the harmonic disturbance across a rotor-stator interface, the present method employs the time series reconstruction in conjunction with a temporal Fourier transform. On the other hand, the consistency with a conventional steady multistage solution for the base flow is achieved by applying an extended mixing plane method. The validity and effectiveness of the method are examined and demonstrated.
Original languageEnglish
Title of host publicationProceedings of the ASME Turbo Expo 2010
Editors American Society of Mechanical Engineers
Place of PublicationNewYork
PublisherAmerican Society of Mechanical Engineers (ASME)
Pages1253-1261
Number of pages9
Volume6
ISBN (Print) 9780791844014
DOIs
Publication statusPublished - 22 Dec 2010
Externally publishedYes
EventASME Turbo Expo 2010: Power for Land, Sea, and Air - Glasgow, United Kingdom
Duration: 14 Jun 201018 Jun 2010

Conference

ConferenceASME Turbo Expo 2010
CountryUnited Kingdom
CityGlasgow
Period14/06/1018/06/10

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