Measurements of Fan Response to Inlet Total Pressure and Swirl Distortions Produced by Boundary Layer Ingesting Aircraft Configurations

Frohnapfel, Dustin J.; Ferrar, Anthony M.; Bailey, Justin M.; O’Brien, Walter F.; Lowe, K. Todd

doi:10.2514/6.2016-0533

Cited by 12 publications

(6 citation statements)

References 15 publications

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“…The mean axial velocity profiles presented in Fig. 10 display a series of features related to structures introduced to the flow by the presence of the StreamVane, since they are not present in the design profile or in clean inlet results presented by Frohnapfel et al [22,23]. These features indicate total pressure losses, as previously described by the total-to-static pressure ratios calculated using the following relationship in Ref.…”

Section: Resultsmentioning

confidence: 63%

Complex Flow Generation and Development in a Full-Scale Turbofan Inlet

Guimarães

Lowe

O’Brien

2018

Journal of Engineering for Gas Turbines and Power

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The future of aviation relies on the integration of airframe and propulsion systems to improve aerodynamic performance and efficiency of aircraft, bringing design challenges, such as the ingestion of nonuniform flows by turbofan engines. In this work, we describe the behavior of a complex distorted inflow in a full-scale engine rig. The distortion, as in engines on a hybrid wing body (HWB) type of aircraft, is generated by a 21-in diameter StreamVane, an array of vanes that produce prescribed secondary flow distributions. Data are acquired using stereoscopic particle image velocimetry (PIV) at three measurement planes along the inlet of the research engine (Reynolds number of 2.4 × 106). A vortex dynamics-based model, named StreamFlow, is used to predict the mean secondary flow development based on the experimental data. The mean velocity profiles show that, as flow develops axially, the vortex present in the profile migrates clockwise, opposite to the rotation of the fan, and toward the spinner of the engine. The turbulent stresses indicate that the center of the vortex meanders around a preferred location, which tightens as flow gets closer to the fan, yielding a smaller radius mean vortex near the fan. Signature features of the distortion device are observed in the velocity gradients, showing the wakes generated by the distortion screen vanes in the flow. The results obtained shed light onto the aerodynamics of swirling flows representative of distorted turbofan inlets, while further advancing the understanding of the complex vane technology presented herein for advanced ground testing.

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Section: Resultsmentioning

confidence: 63%

Complex Flow Generation and Development in a Full-Scale Turbofan Inlet

Guimarães

Lowe

O’Brien

2018

Journal of Engineering for Gas Turbines and Power

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“…Once the method of StreamVane TM design and implementation in this facility is established, studies of fans behind StreamVanes TM can be utilized to gain initial understandings of the impact of various swirl structures on fan performance. Utilizing StreamVane TM technology allows the study of several components of BLI independently [15]. StreamVanes TM can be produced relatively quickly and relatively inexpensively based on CFD models of the flow.…”

Section: Streamvane Design Using Cfdmentioning

confidence: 99%

Swirl Distortion Using Stream Vanes for Boundary Layer Ingestion Research

Stephens

Celestina

Hughes

2019

Volume 2A: Turbomachinery

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The swirl distortion of a StreamVane™ was investigated in the NASA Glenn Research Center W8 test facility. The StreamVane™ was designed and generated by Virginia Tech based on CFD simulations and included a center body at the aerodynamic interface plane. The swirl pattern generated by the distortion was evaluated using a dense grid of 5-hole Pitot probe measurements captured using a rotating array of probes. Good agreement was found between the design intent and the results at 38.5 kg/s mass flow. The StreamVane™ swirl results were compared to clean facility flow at 5 inlet mass flows and found to be consistent. Additionally, the axial location of the StreamVane™ relative to the measurement plane was investigated to determine the impact on downstream total pressure loss generated by the vanes. The intent of this work was to assess the viability of using a StreamVane™ to generate a Type I or Type II distortion into a Boundary Layer Ingesting propulsor to assess its aerodynamic performance and aeromechanic response.

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“…Similarly, flow losses of axial flow at the inlet associated with turning under the swirl distortion for swirl distortion testing disturb the flow pressure field. The radial and tangential flow angles at the fan outlet are significantly influenced by the inlet-swirl distortion; whereas, the total and static pressure ratios of the fan are significantly influenced by the total pressure distortion at the inlet [6].…”

Section: Introductionmentioning

confidence: 99%

The Influences of Combined Distortions on Fan Performance

Quanyong¹,

Honghu²,

Hou³

2023

Advances in Turbomachinery

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Combined distortions negatively affect the aerodynamic stability of fans, but previous studies have limitations. The 3D CFD method was used to calculate the aerodynamic stability of fans under the total pressure and swirl distortion, total temperature and swirl distortion, and total pressure and total temperature distortion in the work. Rotor 67 was taken as the research object. According to the calculation results, the influences of variable distortion parameters on fan performance under combined distortions were summarized to establish the functional relationship between stability margin losses and distortion parameters.

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Measurements of Fan Response to Inlet Total Pressure and Swirl Distortions Produced by Boundary Layer Ingesting Aircraft Configurations

Cited by 12 publications

References 15 publications

Complex Flow Generation and Development in a Full-Scale Turbofan Inlet

Complex Flow Generation and Development in a Full-Scale Turbofan Inlet

Swirl Distortion Using Stream Vanes for Boundary Layer Ingestion Research

The Influences of Combined Distortions on Fan Performance

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