Use this URL to cite or link to this record in EThOS: https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.789580
Title: Development of a methodology for performance optimisation and manufacturing sensitivity studies for radial flow turbocharger compressors for 21st century legislation
Author: Okhuahesogie, Osarobo Famous
ISNI:       0000 0004 8501 5331
Awarding Body: University of Lincoln
Current Institution: University of Lincoln
Date of Award: 2018
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Abstract:
The use of algorithmic optimisation techniques whereby several designs are evaluated automatically in batches using Computational Structural Mechanics (CSM) and or Computational Fluid Dynamics (CFD) modelling to improve performance, has become an integral part of turbomachinery design process. Designing radial compressors for better performance as well as manufacturing the impeller such that there are no discrepancies between the designed surface and machined surface represents a significant challenge for the industry. Accounting for geometric variability (to model manufacturing errors) during the design/optimisation phase where hundreds of candidate geometries are evaluated is costly due to the large number of calculations required to analyse the possible combinations of manufacture errors for each new geometry design. This thesis addressed the problem by separating the design phase from the manufacture uncertainty calculations phase, focusing on a common 5-axis milling type error - undercut; and using a low cost high throughput computing cluster to meet the computational requirements of both phases. A bespoke parametric CAD algorithm was developed to automate the geometry creation during the optimisation phase. The Differential Evolution for Multi-Objective Optimisation (DEMO) algorithm was used to drive the optimisation calculations. In-house meshing software from Napier Turbochargers Ltd, subsequently referred to as Napier, was used to mesh the computational domain, which was then solved using a commercial CFD solver. The compressor in the high-pressure (HP) stage of a two-stage turbocharger was optimised, and shows significant improvements in measured parameters - up to 1.6 points of efficiency gain and 20% increase in map width, respectively. The calculations were carried out on a HTCondor cluster of 8 Linux workstations. Moreover, a study on the sensitivity of radial compressor aerodynamic performance to the presence of an undercut on the impeller surface was also carried out. In-house software from Napier was used to create an undercut on the impeller surface by modifying the CAD geometry file. The impact of the undercut on performance was quantified using detail 3D CFD analysis. Various undercut height and width levels at 13 different locations on the blade surface were analysed for three compressor designs. A unique sensitivity distribution for each compressor impeller is calculated and used to create a variable tolerance map on the impeller surface. This approach was shown to facilitate savings in cost by reducing scrap rate. In addition, a bespoke 1-D algorithm for estimating the size of a radial compressor impeller required to meet a design mass flow and pressure ratio at a given rotor speed was developed. The model can be used PhD Thesis - O. F. Okhuahesogie Page 5 as a preliminary tool when designing a new compressor (where there is no previous experimental or numerical data). The algorithm is based on a combination of fundamental turbomachinery physics equations, correlations extracted from literature and statistical modelling. Finally, an algorithm for calculating the flow area and air mass flow of the low pressure (LP) and high pressure (HP) compressors and turbines in a two-stage turbocharger required to meet a diesel engine specification was developed. The algorithm was used to validate the flow specification of a two-stage turbocharger for a test diesel engine.
Supervisor: Not available Sponsor: Not available
Qualification Name: Thesis (Ph.D.) Qualification Level: Doctoral
EThOS ID: uk.bl.ethos.789580  DOI: Not available
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