NDLI: A CFD Model for Reacting Flows in an Aero-Engine Hot End Simulator

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Ma, L. Pourkashanian, M. C. Wilson, C. W.
Copyright Year	2005
Abstract	This paper presents a three-dimensional CFD model that numerically simulates the physical and chemical species transformations in the aero-engine turbine and nozzle aimed at contributing to an improved understanding of the minor species emitted by the aircraft, in particular the production of the gaseous aerosol precursors such as SO3, H2SO4 and HONO within the aircraft engine. The results presented are for the model applications to an aero-engine Hot End Simulator (HES). The HES was designed in the PARTEMIS programme to recreate the thermodynamic profile in the turbine and nozzle through which the hot gases pass after leaving the combustor so that detailed measurements can be made within the HES providing key boundary conditions and validations to the CFD model predictions. A detailed sulphur reaction mechanism has been incorporated in the numerical model, together with hydrocarbon-air and nitrogen chemistry, so that the effect of both engine condition and fuel sulphur content on the sulphur IV to VI conversion, as well as NOx/NOy conversion, in the post combustor region can be numerically predicted. For the two operational conditions studied, it is noted that there is still a significant portion of sulphur conversions taking place within the HES, although they are smaller when compared with the sulphur conversions that take place in the combustor. Overall conversion efficiencies of about 3.2% and 2.8% have been predicted for the Cruise and the Modern conditions studied, respectively, of which 0.6% and 0.7% were predicted occurring within the HES, respectively. The CFD predictions compared well with the available data from the HES measurements, although considerable uncertainties in the model input exist. The modelling results suggest that reasonable predictions can be obtained for the fluid flow, heat transfer and the chemical species transformations that occur in the turbine and nozzle, particularly for some of the unstable species that are not readily obtained through measurements. These results could also provide useful information/boundary conditions for the subsequent post engine modelling of the new particulate materials formed within the aircraft wake.
Sponsorship	International Gas Turbine Institute
Starting Page	29
Ending Page	39
Page Count	11
File Format	PDF
ISBN	079184725X
DOI	10.1115/GT2005-68077
e-ISBN	0791837548
Volume Number	Volume 2: Turbo Expo 2005
Conference Proceedings	ASME Turbo Expo 2005: Power for Land, Sea, and Air
Language	English
Publisher Date	2005-06-06
Publisher Place	Reno, Nevada, USA
Access Restriction	Subscribed
Subject Keyword	Bulk solids Uncertainty Computational fluid dynamics Computer simulation Fluid dynamics Aircraft engines Fuels Nitrogen Flow (dynamics) Modeling Engines Gases Chemistry Aerosols Wakes Nozzles Boundary-value problems Nitrogen oxides Sulfur Combustion chambers Aircraft Turbines Heat transfer
Content Type	Text
Resource Type	Article

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