Active Control of Flow in Serpentine Inlets for Blended Wing-Body Aircraft

Ferrar, Anthony M.; O’Brien, Walter F.; Ng, Wing; Florea, Razvan; Arend, David J.

doi:10.2514/6.2009-4901

Cited by 10 publications

(5 citation statements)

References 4 publications

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“…NASA partnered with UTRC, Pratt & Whitney, and Virginia Polytechnic and State University (Virginia Tech) through the NRA to exploit the optimal design space and to design and build an integrated inlet and fan embedded system. A sampling of the relevant publications supporting this activity including the simulated aircraft boundary layer, the embedded inlet and distortion tolerant fan design, and the aeromechanics analysis is found in References [104][105][106][107][108][109][110]. NASA recently completed the testing of a distortion-tolerant fan with a relevant boundary layer inflow field in the 8-by 6-Foot Supersonic Wind Tunnel at GRC.…”

Section: Current and Future Nasa Collaborationsmentioning

confidence: 99%

NASA's Role in Gas Turbine Technology Development: Accelerating Technical Progress Via Collaboration Between Academia, Industry, and Government Agencies

Suder

2020

Journal of Turbomachinery

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Given the maturity of the gas turbine engine since its invention and considering the limited resources expected to be allocated for NASA aeronautics research and development, we ask the question are NASA technology investments still needed to enable future turbine engine-based propulsion systems? If so, what is NASA's unique role to justify NASA's investment? To address this topic, we first summarize NASA's role and contributions to turbine engine development, specific to both 1) NASA's role in conducting experiments to understand flow physics and provide relevant benchmark validation experiments for Computational Fluid Dynamics (CFD) code development, validation, and assessment; and 2) the impact of technologies resulting from NASA collaborations with industry, academia, and other government agencies. Note that the scope of the discussion is limited to the NASA technology contributions with which the author was intimately associated, and does not represent the entirety of the NASA contributions to turbine engine technology. The specific research, development, and demonstrations discussed herein were selected to both 1) provide a comprehensive review and reference list of the technology and its impact, and 2) identify NASA's unique role and highlight how NASA's involvement resulted in additional benefit to the gas turbine engine community. Secondly, we will discuss current NASA collaborations that are in progress and provide a status of the results. Finally, we discuss the challenges anticipated for future turbine engine-based propulsion systems for civil aviation and identify potential opportunities for collaboration where NASA involvement would be beneficial.

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Section: Current and Future Nasa Collaborationsmentioning

confidence: 99%

NASA's Role in Gas Turbine Technology Development: Accelerating Technical Progress Via Collaboration Between Academia, Industry, and Government Agencies

Suder

2020

Journal of Turbomachinery

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“…no inlet flow control present) distortion issuing from Inlet A. Data was acquired at conditions matching those at which CFD calculations 25 have been performed and experimental wind tunnel data 28,31 have been acquired by NASA Langley. The precision screen rotating mechanism permitted measurement of the fan's response to both inlet distortion intensity and angular extents with its radially plunging inter-stage high response probe.…”

Section: A Foundational Distortion Experimentsmentioning

confidence: 99%

“…To meet this need, Virginia Tech planned experimental investigations to examine the flow produced in and by a BLI inlet and to measure its JT15D engine fan's response to such distortions. [25][26][27] Owing to its part-span shroud which limited aeromechanical blade deflections, the JT15D engine was viewed as being well suited for this pioneering propulsion research. Initiated early in the Robust Design project before its inlet or fan were designed, this effort leveraged the high quality, computational and experimental database which resulted from prior research conducted by NASA Langley.…”

Section: Approachmentioning

confidence: 99%

Generation after Next Propulsor Research: Robust Design for Embedded Engine Systems

Arend

Tillman²,

O’Brien

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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have contracted to pursue multidisciplinary research into boundary layer ingesting (BLI) propulsors for generation after next environmentally responsible subsonic fixed wing aircraft. This Robust Design for Embedded Engine Systems project first conducted a high-level vehicle system study based on a large commercial transport class hybrid wing body aircraft, which determined that a 3 to 5 percent reduction in fuel burn could be achieved over a 7,500 nm mission. Both pylonmounted baseline and BLI propulsion systems were based on a low-pressure-ratio fan (1.35) in an ultra-high-bypass ratio engine (16), consistent with the next generation of advanced commercial turbofans. An optimized, coupled BLI inlet and fan system was subsequently designed to achieve performance targets identified in the system study. The resulting system possesses an inlet with total pressure losses less than 0.5%, and a fan stage with an efficiency debit of less than 1.5% relative to the pylon-mounted, clean-inflow baseline. The subject research project has identified tools and methodologies necessary for the design of nextgeneration, highly-airframe-integrated propulsion systems. These tools will be validated in future large-scale testing of the BLI inlet / fan system in NASA's 8 ft x 6 ft transonic wind tunnel. In addition, fan unsteady response to screen-generated total pressure distortion is being characterized experimentally in a JT15D engine test rig. These data will document engine sensitivities to distortion magnitude and spatial distribution, providing early insight into key physical processes that will control BLI propulsor design. Nomenclature 0 = free stream U = velocity difference  p = propulsive efficiency AEDC = Arnold Engineering Development Complex AIP = aerodynamic interface plane BLI = boundary layer ingesting BPF = blade passing frequency BWB = blended wing body CAEP = Committee on Aviation Environmental Protection 2 conv = conventional ERA = Environmentally Responsible Aviation (Project) EXTE = extended trailing edge FAR = Federal Aviation Regulations HWB = hybrid wing body ICAO = International Civil Aviation Organization, a United Nations Specialized Agency in = inlet ITAPS = Integrated Total Aircraft Power System j = jet (nozzle exhaust) LTO = landing and take-off m  = air mass flow rate MIT = Massachusetts Institute of Technology N+1 = next generation (similarly, N+2 = generation after next, and so forth) N2A = generation after next airframe designed for podded engines NASA = National Aeronautics and Space Administration NRA = NASA Research Announcement NPSS = Numerical Propulsion System Simulation P = power P&W = Pratt & Whitney, a United Technologies Company P&WC = Pratt & Whitney Canada, a United Technologies Company RANS = Reynolds averaged Navier Stokes SFW = Subsonic Fixed Wing (Project) SPL = sound power level T = thrust TSFC = thrust specific fuel consumption TWT = transonic wind tunnel U = velocity U = mass averaged velocity UCI = University of California, Irvine UHB = ultra-high bypass USAF = United States ...

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“…A blended-wing-body (BWB) aircraft is a highly viable and promising layout for commercial aircraft [1][2][3][4][5][6][7]. The high lift-to-drag ratio of BWB aircraft results in small fuel consumptions [8][9][10][11].…”

Section: Introductionmentioning

confidence: 99%

Power Fan Design of Blended-Wing-Body Aircraft with Distributed Propulsion System

Jia

2021

International Journal of Aerospace Engineering

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A blended-wing-body aircraft has the advantages of high lift-to-drag ratio, low noise, and high economy compared with traditional aircraft. It is currently a solution with great potential to become a future civilian passenger aircraft. However, most airplanes with this layout use distributed power, and the power system is on the back of the fuselage, with embedded or back-supported engines. This type of design causes the boundary layer suction effect. The boundary layer ingestion (BLI) effect can fill the wake of the aircraft and improve the propulsion efficiency of the engine. However, it causes huge design difficulties, especially when the aircraft and the engine are strongly coupled. In this paper, an aircraft with a coupled engine configuration is studied. The internal and external flow fields are calculated through numerical simulation. A realistic calculation model is obtained through the coupling of boundary conditions. On the basis of the influence of the external flow on the internal flow under the coupled condition, the influence of the BLI effect on the aerodynamic performance of the fan is investigated.

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Active Control of Flow in Serpentine Inlets for Blended Wing-Body Aircraft

Cited by 10 publications

References 4 publications

NASA's Role in Gas Turbine Technology Development: Accelerating Technical Progress Via Collaboration Between Academia, Industry, and Government Agencies

NASA's Role in Gas Turbine Technology Development: Accelerating Technical Progress Via Collaboration Between Academia, Industry, and Government Agencies

Generation after Next Propulsor Research: Robust Design for Embedded Engine Systems

Power Fan Design of Blended-Wing-Body Aircraft with Distributed Propulsion System

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