Zero-dimensional Analysis of Thermal Choking in Arbitrary Duct with Application to Dual-mode Ramjet Combustor

TL;DR

This paper develops a generalized Rayleigh flow analysis method to study thermal choking in arbitrary ducts, accounting for real-world effects like heat transfer, friction, and area variation, aiding in combustor design.

Contribution

It introduces a comprehensive analytical framework for thermal choking analysis that includes multiple heat transfer effects and variable duct geometries, extending beyond standard assumptions.

Findings

The method accurately predicts thermal choking locations.

It can distinguish between scramjet and dual-mode combustor behaviors.

The analysis aligns well with existing literature data.

Abstract

Thermal choking in combustor ducts is a matter of great interest to researchers involved in the design and analysis of combustors. In case of scramjet combustors, a thermally choked state is undesirable whereas for a dual-mode combustor in the ram mode it is essential. Since real-life combustors feature volume heat addition due to combustion, area variation, wall heat loss and frictional losses, all of these effects must be included in the analysis. The standard Rayleigh flow assumes a constant-area duct with no frictional effects and a single heat addition/loss term without distinguishing between combustion and wall heat transfer effects. Instead, a generalized Rayleigh flow analysis is employed here which can account for all the above effects and also provide for different fuel injection rates and mixing efficiency. The forward and inverse heat transfer problems are stated and solutions are compared between Rayleigh flow in constant-area and variable-area ducts. The analysis is checked against a scramjet combustor in the literature and then used to study the occurrence of thermal choking in a dual-mode combustor geometry. The possibility of thermal choking and the location of the choking event can be easily detected by this method. The shift in the thermal choking location with variation in the duct heat and mass transfer state can be easily evaluated. In this manner, the present method provides a quick and accurate tool for preliminary design and analysis of ramjet and scramjet combustors.