The Calorimeter Nozzle Programme

Hagemann, G.; Alting, J.; Kretschmer, J.; Terhardt, M.; Frey, Manuel; Rydén, Roland; Stark, Ralf

doi:10.2514/6.2002-3998

Cited by 5 publications

(1 citation statement)

References 6 publications

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“…Therefore, the heat transfer rate of combustion products is very important to insulation erosion, engine thermal protection, etc. A large number of tests were undertaken on heat-flux measurement of liquid propellant rocket engine [1][2][3][4][5], and there are already many mature methods to obtain hot-firing tests data such as using heat flow meter and recording temperature changes directly. Despite abundant research, very little work on SRM was carried out in this respect [6][7][8] because the two-phase flow impingement would cause damage to heat flow meter and thermocouple, which delayed SRM measurement testing and development schedules.…”

Section: Introductionmentioning

confidence: 99%

Heat Flux Measurement Method of Two-Phase Flow in SRM

Zhang

Liu

et al. 2012

AMM

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Accurate information on heat transfer data of combustion products in the solid rocket motor chamber is a crucial prerequisite for the engine thermal protection. A measurement technique was well developed to acquire steady-state heat flux data of two-phase flow and was used successfully in the hostile environment. Experimental heat flux measurement has been obtained with an innovative designed instrument by simulating the flow field of complex charging configuration. The total heat flux of combustion products in the chamber was brought away by the coolant and calculated by its enthalpy rise in this device. The data could be used to analyze the heat transfer phenomena in SRMs and provide boundary condition for establishing insulation erosion model.

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Section: Introductionmentioning

confidence: 99%

Heat Flux Measurement Method of Two-Phase Flow in SRM

Zhang

Liu

et al. 2012

AMM

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Film Cooling in Rocket Nozzles

Ludescher

Olivier

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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In this project supersonic, tangential film cooling in the expansion part of a nozzle with rocket-engine like hot gas conditions was investigated. Therefore, a parametric study in a conical nozzle was conducted revealing the most important influencing parameter on film cooling for the presented setup. Additionally, a new axisymmetric film cooling model and a method for calculating the cooling efficiency from experimental data was developed. These models lead to a satisfying correlation of the data. Furthermore, film cooling in a dual-bell nozzle performing in altitude mode was investigated. The aim of these experiments was to show the influence of different contour inflection geometries on the film cooling efficiency in the bell extension.

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Experimental study of boundary layer separation in truncated ideal contour nozzles

Stark

Wagner

2008

Shock Waves

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The Calorimeter Nozzle Programme

Cited by 5 publications

References 6 publications

Heat Flux Measurement Method of Two-Phase Flow in SRM

Heat Flux Measurement Method of Two-Phase Flow in SRM

Film Cooling in Rocket Nozzles

Experimental study of boundary layer separation in truncated ideal contour nozzles

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