04 - Propulsion
MULTI-DISCIPLINARY DESIGN OF HIGH-SPEED COMPRESSORS FOR PROSPECTIVE TURBO-SHAFT ENGINE
A.N. Startsev¹, Y.M. Temis¹, E.G. Steshakov¹, D.A. Yakushev¹; ¹CIAM, Russia
Multi-Disciplinary Design of High-Speed Compressors for Prospective Turbo-Shaft Enginern A.N.Startsev*, Yu.?.??mis, ?u.G.Steshakov, D.?.Yakushev rnCentral Institute of Aviation Motors, ??scow, RUSSIA (* e-mail: aerora@bk.ru)rn In order to reduce fuel burn of prospective turbo-shaft engines, overall pressure ratio (OPR) and efficiency of its compressor must be increased (see [1]). This paper focuses on optimal multi-disciplinary design of a high-speed high pressure ratio and efficient compressor. The design is targeted to determine compressor configuration, flow-path and construction to provide excellent aerodynamics and meet mechanical requirements. rn This paper describes specifically aerodynamic and strength problems appearing in design of a high-speed compact compressors achieving OPR = 20 - 25 in 4 - 6 stages. In-house and commercial validated 3D numerical tools are used to assess the quality of design. rn One-spool axial-centrifugal compressor at the 7000 SHP level with corrected flow-rate of 11 kg/s and OPR ? 20 is the subject of investigation in this paper. It has to be mentioned that, usually, more complex two-spool configuration is preferred for OPR > 20 (see [2]). rnDuring multi-disciplinary optimization three configurations of axial-centrifugal compressor (consisting of an axial supersonic LPC with variable number of stages matched to a centrifugal HPC) were studied sequentially: 3 axial stages + 1 centrifugal stage, 4 axial stages + 1 centrifugal stage and 5 axial stages + 1 centrifugal stage. rnVariation of number of LPC stages allows to re-distribute work split between LPC and HPC. As a rule, (although sometimes not, see [3] and [4]), efficiency of a centrifugal compressor is lower than that of an axial compressor, therefore it is profitable to increase LPC work and to do that by adding of axial stages.rnDesign rotational speed has been chosen high (Rotor 1 tip speed equals to 490 m/s). A