Test Specimen Design and Measurement Technique for Investigation of Heat Transfer Processes in Cooling Channels of Rocket Engines Under Real Thermal Conditions

Suslov, Dmitry; Woschnak, A.; Sender, Joachim; Oschwald, Michael

doi:10.2514/6.2003-4613

Cited by 23 publications

(9 citation statements)

References 2 publications

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“…The test specimen used for this investigation is the research combustor BKD [26,27] with the injector head L42, operated at the P8 test facility [2830] of the DLR Institute of Space Propulsion in Lampoldshausen. It consists of the injector head, the cylinder segment and the nozzle segment, as shown in Fig.…”

Section: Methodsmentioning

confidence: 99%

Measuring the phase between fluctuating pressure and flame radiation intensity in a cylindrical combustion chamber

Gröning

Hardi

Suslov

et al. 2019

Progress in Propulsion Physics – Volume 11

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The energy transfer from the heat release of the combustion to the acoustic pressure oscillations is the driving element of combustion instabilities. This energy transfer is described by the Rayleigh criterion and depends on the phase shift between the pressure and heat release rate oscillations. A research rocket engine combustor, operated with the propellant combination hydrogen/oxygen, was equipped with dynamic pressure sensors and fibre optical probes to measure the flame radiation. This setup has been used for a phase shift analysis study which showed that unstable operation is characterized by a phase shift leading to an energy transfer from the heat release to the acoustic pressure oscillations.

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Section: Methodsmentioning

confidence: 99%

Measuring the phase between fluctuating pressure and flame radiation intensity in a cylindrical combustion chamber

Gröning

Hardi

Suslov

et al. 2019

Progress in Propulsion Physics – Volume 11

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show abstract

“…The spring loading of the Figure 4 Thermocouple positions in the chamber wall thermocouples provides a constant force of about 2 N, which ensures a continuous contact between the thermocouples tip and the base of the hole. This setup aims to minimize the chance of potential loss of contact as the material undergoes expansion and contraction due to changes in temperature or vibrations during the hot run [12]. Moreover, in order to be able to reconstruct the temperature ¦eld in the chamber material, thermocouples are placed at di¨erent distances from the hot gas wall (Table 3).…”

Section: Methodsmentioning

confidence: 99%

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Celano

Silvestri

Schlieben

et al. 2016

Progress in Propulsion Physics

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The results from an experimental investigation on an oxygenmethane single-injector combustion chamber are presented. They provide detailed information about the thermal loads at the hot inner walls of the combustion chamber at representative rocket engine conditions and pressures up to 20 bar. The present study aims to contribute to the understanding of the thermal transfer processes and to validate the in-house design tool Thermtest and a base for an attempt to simulate the §ame behavior with large-eddy simulation (LES). Due to the complex §ow phenomena linked to the use of cryogenic propellants, like extreme variation of §ow properties and steep temperature gradients, in combination with intensive chemical reactions, the problem has been partially simpli¦ed by injecting gaseous oxygen (GOx) and gaseous methane (GCH 4 ). external combustion chamber width, m c speci¦c heat capacity, J/(kg·K)' E in total energy entering the control volume, W ' E out total energy leaving the control volume, W

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“…Additionally on the first segment, 0.5 mm type T thermocouples are mounted at 3 mm distance to the hot wall at 90 • angle and at the same axial positions of the other measurement points. A spring loaded system ensures a continuous contact between the thermocouples tip and the base of the hole, providing a constant force of about 2 N. 9) The thermocouple location pattern is shown in Fig. (3).…”

Section: Methodsmentioning

confidence: 99%

Investigation on Recess Variation of a Shear Coax Injector for a Single Element GOX-GCH4 Combustion Chamber

Silvestri

Celano

Kirchberger

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Test Specimen Design and Measurement Technique for Investigation of Heat Transfer Processes in Cooling Channels of Rocket Engines Under Real Thermal Conditions

Cited by 23 publications

References 2 publications

Measuring the phase between fluctuating pressure and flame radiation intensity in a cylindrical combustion chamber

Measuring the phase between fluctuating pressure and flame radiation intensity in a cylindrical combustion chamber

Injector characterization for a gaseous oxygen-methane single element combustion chamber

Investigation on Recess Variation of a Shear Coax Injector for a Single Element GOX-GCH4 Combustion Chamber

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