Numerical Analysis of Supersonic and Hypersonic Intake Systems with Nanoparticle Injection
Date
2020-01-28
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Abstract
Inter-phase momentum and energy transfer interactions in gas-particle flows were studied for applications in high-speed airbreathing engines. The overall aim of the thesis is to investigate nanoparticle injection across high-speed intake systems. In the first stage, existing numerical strategies were assessed for the modeling of compressible, gas-nanoparticle flows. Based on a detailed literature review, a combination of quasi-1D and 3D computational fluid dynamic (CFD) approaches were selected. CFD simulations were conducted using a custom-modified, unsteady, compressible, Eulerian-Lagrangian gas-particle CFD solver in OpenFOAM. A novel solution verification method was developed for predicting numerical uncertainties in multiphase flow simulations with one-way coupling, which was used to verify the CFD solutions. In the second stage, the effect of nanoparticle injection on the performance of supersonic/hypersonic intake systems was investigated. A parametric study using Mach number (M), Stokes number (Stk), particle Eckert number (Ecp), particle mass loading ratio (SL), and thermal transport number (at) was conducted across a quasi-1D converging-diverging (C-D) supersonic intake at idealized and single-shock compression cases. Gains in pressure recovery were observed at specific combinations of the five input parameters, which was further investigated. The 1D study was followed by CFD simulations of a rectangular, mixed-compression intake at Mach 3. The CFD results predicted a 16% gain in pressure recovery, consistent with the 1D model predictions. In the final stage, starting and buzz characteristics of high-speed intakes were investigated with nanoparticle injection. Isentropic and Kantrowitz contraction limits were estimated at particle mass loading ratios of 0, 0.12 and 0.24. These results were followed by CFD simulations of a 2D, external compression intake with an operating Mach number of 2. The CFD study was conducted at particle mass loading ratios of 0, 0.12 and 0.24; and nozzle throttling ratios from 0.57 to 0.44. The effect of nanoparticle injection on the Ferri-type instability and unstart were investigated. The potential for nanoparticles to attenuate buzz, once the instabilities are triggered, was also assessed.
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Jagannathan, R. (2020). Numerical Analysis of Supersonic and Hypersonic Intake Systems with Nanoparticle Injection (Doctoral thesis, University of Calgary, Calgary, Canada). Retrieved from https://prism.ucalgary.ca.