RDE Nozzle Computational Design Methodology Development and Application

Kenji Miki; Daniel E Paxson; H. Douglas Perkins; Shaye Yungster

NASA NTRS · 20205004461

RDE Nozzle Computational Design Methodology Development and Application

Kenji Miki·Daniel E Paxson·H. Douglas Perkins·Shaye Yungster

Abstract

The Open National Combustion Code (OpenNCC) is used to simulate the aerospike exhaust nozzle region of a rotating detonation engine (RDE).The main objectives of the current study are twofold. The first goal is to validate the proposed computational methodology using the experimental data. The second goal is to demonstrate how the validated prediction tool can be used to optimize the nozzle geometry. To achieve a significant speed-up of computational time, the computational domain in divided into two parts: a combustion region and a throat-nozzle section. In the combustion region, a validated quasi-two-dimensional in-house code is utilized to generate an unsteady RDE flow field solution just upstream of the combustor throat. Subsequently, the unsteady flow data is fed into the three-dimensional throat-nozzle section as the inflow boundary condition. This facilitates the design optimization process since the unsteady inflow can be reused, and a relatively coarse mesh (i.e., larger time-step) can be used to analyze the flow fields around the nozzle. Five nozzle designs were studied and the predicted performance (i.e., thrust)compared. The optimized nozzle was found to produce 3.2% more overall thrust than a baseline nozzle design. Without the nozzle, there is a large low-pressure region at the throat exit, which significantly reduces the overall performance. This methodology is shown to be a promising approach to explore a wide variety of nozzle geometries in a relatively short amount of time.

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BibTeX RIS

Kenji Miki, Daniel E Paxson, H. Douglas Perkins, Shaye Yungster. RDE Nozzle Computational Design Methodology Development and Application. https://ntrs.nasa.gov/citations/20205004461

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