Details
The first lectures focuses on the preliminary design of state of the art turbofan engine for the propulsion of civil aircrafts. Issues like thermodynamic cycle, mission analysis, and off design operation (operating line) are addressed. Practical examples are presented. Once this important phase is completed, the different design teams have the boundary conditions to start the design of each component.
This starts with the fan that must cope with a number of constraints in terms of mechanical resistance, noise and surge margin. The aerodynamic design involves both subsonic flow at the hub and supersonic flow at the tip.
The design of the booster (low pressure compressor) is then addressed where the multistage operation and the matching between successive stages are important concerns. Moving to the high pressure compressor, the lectures first describe the preliminary design based on througflow calculations. Then, airfoil design, from 2D sections to stage matching optimisation is addressed. Current trends for future HPC configurations are outlined.
The design of the combustion chamber involves a number of disciplines such as aerodynamics, fuel atomisation, chemistry of combustion and combustor cooling as well as environmental regulatory issues for emissions (NOx, CO, UHC, soot) along with future combustor technologies. Each of these topics is reviewed while addressing the design of the combustion chamber.
Concerns related to fuel consumption and environmentally friendliness has pushed the engine manufacturer community to look into innovative architectures. An overview of advanced concepts related to fuel burn reduction is addressed to improve thermal efficiency and propulsive efficiency, among which open rotor engines, boundary layer ingestion configurations, intercooled engines, non-Brayton cycles …
The high-pressure turbine has the particularity to be submitted to high levels of centrifugal force and exposure to very hot burned gases. The design process, involving successively 1D, 2D and 3D analysis is targeting the highest stage efficiency while accommodating for the cooling of the blades.
Finally, the low-pressure turbine design must satisfy high efficiency together with low weight, cost and noise. This is defined primarily by the load and flow coefficients and the number of airfoils. New lightweight/lowcost configurations tend to reduce the number of blades thanks to high lift designs that take advantage of the positive effects of the unsteady row interaction on the airfoil boundary layer behaviour.
- KURZKE, J. – GasTurb, Germany
Preliminary design - SMITH, N.H.S. – Rolls-Royce plc, Derby, United Kingdom
The aerodynamic design of the LPC system - OBRECHT, T. – Snecma, France
HP compressor preliminary design - DOMERCQ, O. – Snecma, France
HP compressor aerodynamics: 3D design and stage matching - DOERR, T. – Rolls-Royce Deutschland Ltd & Co Kg, Germany
Introduction to aero-engine gas turbine combustion - TANTOT, N. – Snecma, France
From turbofan to innovative architectures - HASELBACH, F. & TAYLOR, M. – Rolls-Royce plc, Derby, United Kingdom
Axial flow high pressure turbine aerodynamic design - VÁZQUEZ, R. – Industria de Turbopropulsores S.A. (ITP), Spain
Low-pressure turbine design
Additional Information
| Manufacturer | von Karman Institute for Fluid Dynamics |
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