Experimental Operating Range Extension of a Twin-Spool Turbofan Engine by Active Stability Control Measures

Scheidler, Stephan G.; Fottner, Leonhard

doi:10.1115/1.2031247

Cited by 9 publications

(3 citation statements)

References 3 publications

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“…The first injections system was developed by Leinhos et al (2002) and featured ten injection ducts with revolvable injection nozzles. His results and the following investigations by Scheidler and Fottner (2004) demonstrated the capabilities of tip injection in full jet engine applications. In the follow-up work by Bindl et al (2009a), a slightly modified and optimized injection system was used to realize an active compressor stabilization system.…”

Section: Nomenclaturementioning

confidence: 89%

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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Section: Nomenclaturementioning

confidence: 89%

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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“…4 The primary benefit explored here is in the reduction in engine SM conservatism. 12,13 In the aircraft engine research community, MBEC is recognized as a means to provide the necessary improved efficiency to reduce engine-specific fuel consumption. 5,7,14,15 The advancement proposed in this paper compared to previous work is the improved estimation across the engine life cycle, and the direct connection of controls into the engine design process.…”

Section: Mbec Control Architecturementioning

confidence: 99%

Advanced Control Considerations for Turbofan Engine Design

Connolly

Csank²,

Chicatelli³

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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This paper covers the application of a model-based engine control (MBEC) methodology featuring a self tuning on-board model for an aircraft turbofan engine simulation. The nonlinear engine model is capable of modeling realistic engine performance, allowing for a verification of the advanced control methodology over a wide range of operating points and life cycle conditions. The on-board model is a piece-wise linear model derived from the nonlinear engine model and updated using an optimal tuner Kalman Filter estimation routine, which enables the on-board model to self-tune to account for engine performance variations. MBEC is used here to show how advanced control architectures can improve efficiency during the design phase of a turbofan engine by reducing conservative operability margins. The operability margins that can be reduced, such as stall margin, can expand the engine design space and offer potential for efficiency improvements. Application of MBEC architecture to a nonlinear engine simulation is shown to reduce the thrust specific fuel consumption by approximately 1% over the baseline design, while maintaining safe operation of the engine across the flight envelope.

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“…Ffowcs Williams et al [11] report about investigations in a radial compressor of a stationary gas turbine and Freeman et al [12] in an axial compressor of a jet engine. Scheidler and Fottner [13] could establish a range extension in a Larzac-04-C5 engine and mentioned successful restabilization tests. Bindl et al [14] developed a stall detection algorithm in combination with an active compressor stabilization system using the same test rig.…”

Section: Introductionmentioning

confidence: 99%

Active flow control at a 1.5-stage low-speed research compressor with varying rotor tip clearance

Künzelmann

Urban

Mailach

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part A:

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The stable operating range of axial compressors is limited by the onset of rotating stall and surge. Mass injection upstream of the tip of an axial compressor rotor is a stability enhancement approach which can be effective in suppressing stall in tip-critical rotors, and thus increasing the operating range of compressors. In this article, investigations on active flow control related to the rotor tip gap sensitivity are discussed. The experiments were performed in a 1.5-stage low-speed research compressor. Measurements at part speed (80 per cent) and full speed (100 per cent) with varying injection rates are discussed. These tests were performed for two rotor tip clearances of 1.3 per cent and 4.3 per cent of rotor blade tip chord. Results on the compressor map, the flow field as well as transient measurements to identify the stall inception are discussed. Supplementary, the numerical results are compared to the experiments based on the configuration with the greatest benefit in operating range enhancement.

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Experimental Operating Range Extension of a Twin-Spool Turbofan Engine by Active Stability Control Measures

Cited by 9 publications

References 3 publications

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

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

Advanced Control Considerations for Turbofan Engine Design

Active flow control at a 1.5-stage low-speed research compressor with varying rotor tip clearance

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