Abstract
AbstractCompression systems of modern, civil aircraft engines consist of three components: Fan, low-pressure compressor (LPC) and high-pressure compressor (HPC). The efficiency of each component has improved over the last decades by means of rising computational power which made high level aerodynamic optimisations possible. Each component has been addressed individually and separated from the effects of upstream and downstream components. But as much time and effort has been spend to improve performance of rotating components, the stationary inter-compressor duct (ICD) has only received minor attention. With the rotating compression components being highly optimised and sophisticated their performance potential is limited. That is why more aggressive, respectively shorter, ICDs get more and more into the focus of research and engine manufacturers. The length reduction offers high weight saving and thus fuel saving potential as a shorter ICD means a reduction in aircraft engine length. This paper aims at evaluating the impact of more aggressive duct geometries on LPC and HPC performance. A multi objective 3D computational fluid dynamics (CFD) aerodynamic optimisation is performed on a preliminary design of a novel two spool compressor rig incorporating four different operating line and two near-stall (NST) conditions which ensure operability throughout the whole compressor operating range. While the ICD is free to change in length, shape and cross-section area, the blades of LPC and HPC are adjusted for changing duct aerodynamics via profile re-staggering to keep number of free parameters low. With this parametrisation length, reductions for the ICD of up to 40% are feasible while keeping the reduction in isentropic efficiency at aerodynamic design point for the compressor below 1%pt. Three geometries of the Pareto front are analysed in detail focusing on ICD secondary flow behaviour and changes of aerodynamics in LPC and HPC. In order to asses changes in stall margin, speedlines for the three geometries are analysed.
Publisher
Cambridge University Press (CUP)
Reference27 articles.
1. On the Coupling of Designer Experience and Modularity in the Aerothermal Design of Turbomachinery
2. [27] Cumpsty, N.A. Compressor Aerodynamics, Longman Scientific & Technical; John Wiley, 1989, Harlow, Essex, UK; New York.
3. [14] Karakasis, M.K. , Naylor, E.M.J., Miller, R.J. and Hodson, H.P. The effect of an upstream compressor on a non-axisymmetric S-duct, Volume 7: Turbomachinery, Parts A, B, and C. ASME Turbo Expo 2010: Power for Land, Sea, and Air, ASME, Glasgow, UK, 2010, pp 477–486.
4. [25] Reutter, O. , Ashcroft, G., Nicke, E. and Kuegeler, E. Unsteady full annulus multi-stage compressor calculations - details on CFD-experiment comparison, Aerospace Europe 6th CEAS Conference, 2017, p 9.
Cited by
2 articles.
订阅此论文施引文献
订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献