Accession Number:

AD1155201

Title:

Inlet Isolator and Combustor Physics at Take-Over Region of Scramjet Engines

Descriptive Note:

[Technical Report, Final Report]

Corporate Author:

UNIVERSITY OF ILLINOIS

Personal Author(s):

• Lee, Tonghun

Report Date:

2021-09-16

Pagination or Media Count:

35

Abstract:

This report outlines an effort to understand the impact of inlet isolator physics on the combustion of scramjet engines under actual flight relevant conditions in the take-over regime. We strive to answer the fundamental question what basic physics underlying the connection between inlet isolator physics and combustion stability in canonical axisymmetric andor rectangular geometries are applicable to more practical systems More specifically, the objective of the proposed work is to gain a fundamental understanding of the feedback mechanism between the boundary layer structures and separated flow in the isolator and the corresponding combustion dynamics that can lead to instabilities andor unstart. An experimental effort is proposed where unstart and combustion instabilities are investigated in an optically accessible axisymmetric scramjet model in a free flow high enthalpy flow tunnel. The effort will be coupled with advanced spatially resolved diagnostics of both the isolator and the combustor region to obtain critical insight into the key physics, and potentially evolve into a foundational platform numerical analysis in the future.

Descriptors:

• boundary layer
• fluid mechanics
• laser induced fluorescence
• flow visualization
• heat transfer
• pressure distribution
• fluid dynamics
• supersonic combustion
• turbulent mixing
• mechanical engineering
• mechanics
• pressure measurement
• combustion
• ignition
• supersonic flow
• dual mode
• heat energy

Subject Categories:

• Combustion and Ignition
• Jet and Gas Turbine Engines

Distribution Statement:

[A, Approved For Public Release]