Experimental and numerical investigation of a counter rotating open rotor flow field

Roosenboom, Eric; Schröder, Andreas; Geisler, Reinhard; Pallek, Dieter; Agocs, Janos; Stürmer, Arne; Gutierrez, Carlos Omar Marquez; Neitzke, Klaus-Peter

doi:10.2514/6.2011-3184

Cited by 7 publications

(3 citation statements)

References 16 publications

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“…Unfortunately, no flowfield measurements were available as YIN, STUERMER, AND AVERSANO validation data for the specific configuration under study here. However, the approach adhered to here in terms of mesh generation and CFD simulation draws heavily on that used for other applications [16,17]. In those studies, good agreement was found with available particle image velocimetry measurements, giving confidence in the quality of the results achieved here.…”

Section: Aerodynamic Analysismentioning

confidence: 64%

Aerodynamic and Aeroacoustic Analysis of Installed Pusher-Propeller Aircraft Configurations

Yin

Stuermer

Aversano

2012

Journal of Aircraft

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In this paper, the aeroacoustic phenomena characteristic of a pusher-propeller configuration and their aerodynamic causes are discussed and analyzed. The work was done in the framework of the European-funded project CESAR (for 'cost effective small aircraft'). The configuration under study is based on an industrially relevant business aircraft design with a wing-mounted pusher propeller, which features a close coupling of the turboshaftengine exhaust nozzles and a five bladed propeller. An established numerical analysis approach is applied in this study, which couples a high-fidelity unsteady aerodynamic simulation using the DLR unstructured finite volume flow solver (TAU) code with the DLR Ffowcs-Williams-Hawkings code APSIM for a subsequent aeroacoustic evaluation. A detailed analysis of the contributions of various components of the installation as well as flight-condition specific parameters toward the overall noise generation by the propeller is presented, which highlights the dominant role the engine-jet impingement on the propeller plays for the aeroacoustic characteristics of this type of aircraft configuration. A detailed analysis of specific aspects of the input surface used for the aeroacoustic analysis is made through a comparison between the results achieved using both impermeable and permeable Ffowcs-Williams-Hawkings formulations. The numerical error due to both jet exhaust and propeller wake impingement on the Ffowcs-Williams-Hawkings permeable surface as well as the impact of cutting a hole in this permeable surface to avoid possible issues of these effects are discussed. Nomenclature BPF= blade-passing frequency, Hz C D;L = drag and lift coefficient C T = thrust force coefficient p = pressure, N=m 2 R = propeller radius, m T = period length, s t = time, s u, v, w = velocity components in the Cartesian coordinate system, m=s = angle of attack, deg = density, kg=m 3 = azimuth angle, deg

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Section: Aerodynamic Analysismentioning

confidence: 64%

Aerodynamic and Aeroacoustic Analysis of Installed Pusher-Propeller Aircraft Configurations

Yin

Stuermer

Aversano

2012

Journal of Aircraft

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“…4 Assistant Professor, Wind Energy Section, Faculty of Aerospace Engineering, AIAA member. 5 Full Professor, Flight Performance and Propulsion Section, Faculty of Aerospace Engineering, AIAA member. 6 Full Professor, Head of Flight Performance and Propulsion Section, Faculty of Aerospace Engineering, AIAA member.…”

mentioning

confidence: 99%

“…However, some inherent flaws of the CROR concept impose a restriction for broader application of this type of engine. Examples are the high weight of the propulsion system due to the complex gear system required for obtaining the contra rotation, the additional interaction noise of the contra-rotating stage, and the complexity of its structural layout 5 .…”

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confidence: 99%

Towards Optimum Swirl Recovery Vanes for Propeller Propulsion Systems

Wang¹,

Li²,

Ragni³

et al. 2017

35th AIAA Applied Aerodynamics Conference

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Swirl Recovery Vanes (SRVs) are a row of stationary vanes located downstream of a single-rotating propeller to recover swirl losses and thereby enhance propulsive efficiency. This paper presents the development, application, and experimental validation of a low-order SRVs design tool. The design procedure consists of three steps: first the inflow velocities can be obtained either from the simulation of isolated propeller or from experimental measurements, after which the loading distribution is defined using lifting-line theory, and lastly an airfoil design routine is performed. The design method features both a short computation time useful in the preliminary design phase and parameter investigation, and a detailed vane-shape representation, such that the final overall blade shape can be determined. In this study the model is presented together with a test example, consisting of a set of SRVs designed for a six-bladed propeller operating at high disk-loading condition. Results from the computations are subsequently experimentally validated in a wind-tunnel test of the designed model. The additional thrust generated by the SRVs was measured at different propeller loading conditions. At the design point a 2.6% increase of thrust was reported, together with a similar amount of improvement in the propeller propulsive efficiency. Velocity profiles obtained with PIV fields in the propeller slipstream were used as validation of the numerical simulation, together with quantification of the swirl recovery by SRVs.

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Experimental and Numerical Investigation of a Contra Rotating Open-Rotor Flowfield

Stürmer

Gutierrez

Roosenboom

et al. 2012

Journal of Aircraft

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Experimental and numerical investigation of a counter rotating open rotor flow field

Cited by 7 publications

References 16 publications

Aerodynamic and Aeroacoustic Analysis of Installed Pusher-Propeller Aircraft Configurations

Aerodynamic and Aeroacoustic Analysis of Installed Pusher-Propeller Aircraft Configurations

Towards Optimum Swirl Recovery Vanes for Propeller Propulsion Systems

Experimental and Numerical Investigation of a Contra Rotating Open-Rotor Flowfield

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