The Effects of Swirl Recovery Vanes on Single-Rotation Propeller Aerodynamics and Aeroacoustics

Sinnige, Tomas; Kuijk, JJ van; Lynch, Kyle P.; Ragni, Daniele; Eitelberg, G.; Veldhuis, L.L.M.

doi:10.2514/6.2015-2358

Cited by 5 publications

(3 citation statements)

References 23 publications

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“…This was demonstrated by Witkowski [2] by averaging the sinusoidal effects on thrust and power of the propeller-wing configuration he tested in a wind tunnel, as well as by Samuelsson [52], who did not notice remarkable differences in propeller thrust by placing a propeller-wing configuration at different angles of attack. Sinnige [53] as well noticed no considerable effects of the installation of swirl recovery vanes on a propeller's thrust and power. All of the mentioned authors seem to agree on the fact that in a propeller-lifting body configuration measurable effects can be seen on the latter rather than on the propeller.…”

Section: Thrust and Drag Book-keeping And Relevancementioning

confidence: 99%

A Surrogate-Based Multi-Disciplinary Design Optimization Framework Exploiting Wing-Propeller Interaction

Alba

Elham

German

et al. 2017

18th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference

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The adoption of propellers is the oldest propulsive solution in aviation, and remains nowadays the preferred one in several segments of the market, being the greenest and most fuel-efficient choice for low-to-mid subsonic speeds. New paradigms of mobility envision the use of propeller powered aircrafts to provide an answer to the issue of future mass transportation in and between major cities.Common aircraft design procedures determine optimal wing design parameters pursuing low drag and weight solutions, but neglecting the influence that propellers' slipstreams have on lift and drag distributions, especially when mounted in tractor configurations.Considering such strong interest in propeller propulsion, and the apparent lack of insightful research in the multi-disciplinary design optimization (MDO) opportunities that propeller-wing integration brings along, the present Thesis was designed with the objective of building a surrogate-based MDO framework for a general aviation aircraft featuring wing mounted tractor propellers. Such objective was achieved by developing appropriate analysis tools to model the most relevant effects of wing-propellers interaction, and by integrating them in suitable optimization architectures enhanced by the adoption of surrogate models. Two research hypotheses underlay such approach, the first claiming that accounting for wing-propeller interaction effects could lead to better designs, and the second claiming that the adoption of surrogate modeling techniques could greatly improve overall optimization performances. The successful accomplishment of the described objective was demonstrated by applying the optimization on an existing aircraft and achieving sensitive fuel savings. The mentioned hypotheses were instead proven under several aspects through the multiple surrogate-based optimization frameworks adopted and the obtained optimal designs. The work proposed as well innovative solutions to perform a full interaction wing-propellers analysis, such as routines to assess and model the propeller streamtube deflection and the wing swirl recovery effects. It also provided guidance for the implementation of surrogate-based optimizations in problems featuring high numbers of design variables and multiple complex non-linear constraints, testing different surrogate models, as well as different frameworks, to achieve local and global optimal designs.iii ACKNOWLEDGEMENTSThe path leading to the achievement of my Master in Aerospace Engineering has been a challenging and rewarding one, along which all my professors and colleagues at TU Delft have been a huge source of motivation and improvement.This Thesis is the culmination of such journey, and would not have been possible without the support of the people I have been working with over the past year. I would first like to thank my supervisor Dr. Elham of TU Delft for his availability and precious contribution in several aspects of the work. A great thanks is due as well to Professor Brian German who hosted me at the Georgia Institute o...

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Section: Thrust and Drag Book-keeping And Relevancementioning

confidence: 99%

A Surrogate-Based Multi-Disciplinary Design Optimization Framework Exploiting Wing-Propeller Interaction

Alba

Elham

German

et al. 2017

18th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference

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“…Along with people's attentions to environment issues in recent decades, countries around the world are calling for reducing emissions from aircrafts; therefore, the demands of novel and efficient propeller systems have greatly increased. It is on this premise that CROR systems arouse people's interest as a possible fuel-efficient and environmentally friendly propulsion system for future aircrafts [4,5].…”

Section: Introductionmentioning

confidence: 99%

CFD Analysis of Contrarotating Open Rotor Aerodynamic Interactions

Shi

Yang

et al. 2018

International Journal of Aerospace Engineering

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High efficiency and low fuel consumption make the contrarotating open rotor (CROR) system a viable economic and environmentally friendly powerplant for future aircraft. While the potential benefits are well accepted, concerns still exist with respect to the vibrations and noise caused by the aerodynamic interactions of CROR systems. In this paper, emphasis is placed on the detailed analysis of the aerodynamic interactions between the front and aft propellers of a puller CROR configuration. For the first step, unsteady Reynolds-averaged Navier-Stokes (URANS) simulations coupled with dynamic patched grid technology are implemented on the isolated single-rotating propeller (SRP) configuration in various operating conditions in order to test the accuracy and feasibility of the numerical approach. The numerical results are verified by a wind tunnel test, showing good agreements with the experimental data. Subsequently, the URANS approach is applied to the CROR configuration. The numerical results obtained through the URANS approach help to improve the understanding of the complex flow field generated by the CROR configuration, and the comparison of SRP flow field and CROR flow field allows for a detailed analysis of the aerodynamic interactions of the front propeller blade wakes and tip vortices with the aft propeller. The main reason of the aerodynamic interactions is the mutual effects of the blade tip vortices, and the aft propeller reduces the strength of the blade tip vortices of the front propeller. Aerodynamic interactions will lead to the periodic oscillations of the aerodynamic forces, and the frequency of the oscillations is linked to the blade numbers. In addition, a CROR has a larger thrust and power coefficient than that of the SRP configuration in the same operating conditions. The URANS approach coupled with a dynamic patched grid method is tested to be an efficient and accurate tool in the analysis of propeller aerodynamic interactions.

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“…The unsteady interaction between the propeller and the SRVs was analyzed by Li et al 11 . Particle-image-velocimetry (PIV) measurements conducted at DNW-LLF led to a detailed description of the flowfield induced by the propeller and SRVs, and comparisons of the aeroacoustic performance were made before and after the installation of the vanes 12 .…”

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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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The Effects of Swirl Recovery Vanes on Single-Rotation Propeller Aerodynamics and Aeroacoustics

Cited by 5 publications

References 23 publications

A Surrogate-Based Multi-Disciplinary Design Optimization Framework Exploiting Wing-Propeller Interaction

A Surrogate-Based Multi-Disciplinary Design Optimization Framework Exploiting Wing-Propeller Interaction

CFD Analysis of Contrarotating Open Rotor Aerodynamic Interactions

Towards Optimum Swirl Recovery Vanes for Propeller Propulsion Systems

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