Experimental Investigations on Macro-Aerodynamics Within a Jet Engine Ground Test Facility

Bindl, Stefan; Muth, Bastian; Niehuis, Reinhard

doi:10.2514/6.2009-4828

Cited by 8 publications

(3 citation statements)

References 6 publications

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“…The experiments were performed on the engine test facility (ETF) at the Institute of Jet Propulsion (IJP) (Bindl et al (2009)). For investigations on aerodynamic intake compressor interactions, the Military Engine Intake Research Duct (MEIRD) was designed and built at the IJP (Rademakers et al (2016)) (Figure 1, Figure 2).…”

Section: Methodsmentioning

confidence: 99%

Unsteady flow phenomena in a highly bend engine intake with passive and active flow control

Max,

Stößel,

Kozulovic

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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Highly bent intake systems cause unsteady flow phenomena which have a negative impact on the performance of the compressor system. In the present study, a serpentine intake is investigated experimentally with and without flow-stabilizing measures. The timeaveraged measurement results show that the flow-stabilizing measures strongly reduce the separation bubble and the flow distortion in the intake. Unsteady pressure measurements indicate accordingly that dominant Strouhal numbers, associated with the Dean vortices, are weaker or not present at all in case of flow control. These unsteady phenomena are further analyzed in terms of their respective Strouhal numbers versus the power spectral density and compared to the configuration without any flow-stabilizing measures. The results demonstrate that without flow stabilizing measures, two dominant peaks occur at Strouhal numbers 0.32 ≤ Sr ≤ 0.39 and 0.18 ≤ Sr ≤ 0.24. Thereby, with increasing Reynolds numbers, the dominant Strouhal numbers decrease slightly. KEYWORDShighly bend engine intake, unsteady flow phenomena, active and passive flow control NOMENCLATURE γ relative radius of curvature r k radius of curvature r in radius at the inlet cross section Sr Strouhal number DIP duct inlet plane DOP duct outlet plane IJP Institute of Jet Propulsion ET F engine test facility M EIRD military engine intake research duct p rel relative static pressure p ∞ ambient pressure x, y, z Cartesian coordinates d Duct outlet diameter L total MEIRD lenght x rel , y rel relative cartesian coordinates P SD power spectral density v velocity f frequency s Position at the centerline, percentage wise n spool speed

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Section: Methodsmentioning

confidence: 99%

Unsteady flow phenomena in a highly bend engine intake with passive and active flow control

Max,

Stößel,

Kozulovic

et al. 2023

European Conference on Turbomachinery Fluid Dynamics and Thermodynamics

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“…The experiments were performed on the scaled engine test facility (SETF) (Fig. 1), which is a 1:7,6 scaled model of the ISA's engine test facility (Bindl et al, 2009). The SETF was built to perform a large variety of experimental studies in a time and cost effective manner.…”

Section: Methodsmentioning

confidence: 99%

Effectiveness of Active Flow Control Techniques in an Advanced S-Shaped Engine Intake

Max¹,

Stößel²,

Krummenauer³

et al. 2022

Proceedings of Global Power &Amp; Propulsion Society

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The development of modern military aircraft has to meet considerable requirements in terms of reducing the system weight, installation space, as well as radar signature. For fighter aircraft, serpentine intakes are commonly used since they reduce the radar visibility of the engine, the system weight, and allow the optimal use of the installation space. However, these intake systems cause flow disturbances for the engine. To avoid penalties in engine performance, active flow control methods can be implemented for controlling the flow through the intake. The experiments undertaken at the Institute of Jet Propulsion (ISA) at the Bundeswehr University Munich used a scaled model of a compact double s-shaped intake duct with flow control techniques utilizing air injection and suction for boundary layer control and separation suppression. Detailed total pressure measurements with a Kiel probe rake at the exit plane of the duct show the effectiveness of the individual flow control mechanisms. Suction is applied at three different locations. For each configuration, the suction port diameter and mass flow rate are varied. For tests with injection, air is blown into the intake duct through a Coanda nozzle at two specific positions. The Coanda nozzle slot width and the number of slots were varied. The results demonstrate which parameters must be set to effectively influence the flow and achieve favorable distortion parameters at the intake duct’s outlet.

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“…The EIS is designed for the application at the Larzac 04 tubofan engine, operated in the jet engine test facility of the Institute of Jet Propulsion. Further information on the test facility can be found in Bindl et al (2009b).…”

Section: Installation Prerequisitesmentioning

confidence: 99%

Ejector tip injection system for active aerodynamic compressor stabilization part I: design and experiment

Kern

Brehm

Niehuis

2017

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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The subject of compressor tip air injection in full jet engine test setups has been under investigation at the Institute of Jet Propulsion for many years. Latest experiments revealed that the utilization of the ejector effect can help to raise both effectiveness and efficiency of air injection systems. Based on the gathered experiences, an advanced Ejector Injection System (EIS) was designed from scratch and built most recently. The presented design process is focused especially on the optimal application of the ejector effect in order to achieve maximum performance. As the EIS features complicated 3D flow paths and utilizes not only the ejector but also the Coanda effect, its internal aerodynamics include complex interactions of multiple phenomena. Therefore, extensive stand-alone tests are performed before the ejector injection system is attached to the jet engine. The described test setup features high precision mass flow measurement devices and has created valuable results for a more detailed understanding of the ejector effect and the flow inside the EIS. The experimental work is accompanied by extensive CFD simulations with detailed focus on the internal flow phenomena in the second part of the paper.

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Experimental Investigations on Macro-Aerodynamics Within a Jet Engine Ground Test Facility

Cited by 8 publications

References 6 publications

Unsteady flow phenomena in a highly bend engine intake with passive and active flow control

Unsteady flow phenomena in a highly bend engine intake with passive and active flow control

Effectiveness of Active Flow Control Techniques in an Advanced S-Shaped Engine Intake

Ejector tip injection system for active aerodynamic compressor stabilization part I: design and experiment

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