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Auralization of flyover noise from open-rotor engines using model-scale test data

Auralization of flyover noise from open-rotor engines using ...

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作者： Rizzi, Stephen A. Stephens, David B. Berton, Jeffrey J. Van Zante, Dale E. Wojno, John P. Goerig, Trevor W. NASA Langley Research Center HamptonVA23681 United States NASA John H. Glenn Research Center Lewis Field ClevelandOH44135 United States GE Aviation CincinnatiOH45215 United States Aeroacoustics Branch MS 463 United States Acoustics Branch MS 54-3 United States Multidisciplinary Design Analysis and Optimization Branch MS 5-11 United States Acoustics and Installation Aerodynamics 1 Neumann Way M/D G26 United States

A series of model-scale tests were recently completed using the open-rotor propulsion rig at the NASA John H. Glenn Research Center at Lewis Fieldinanefforttocharacterize the aeroacoustic performanceof several open-rotorpropulsor designs. These included the historical-baseline and second-generation blade sets. Subsequently, the second generation design was assessed to have significant cumulative margins relative to the International Civil Aviation Organization Chapter 4 noise regulations, whilst the historical blade set had a negative margin. However, integrated metrics, like effective perceived-noise level, are not intuitive to the layperson, and likely do not convey the noise benefits over earlier designs, for example, the acoustically unique unducted-fan demonstratorofthe 1980s. This paper develops the means of auralizing flyover-noise projections of full scale open-rotor engines using model-scale data in a manner that more readily communicates the noise benefit, and that is consistent with previously published aircraftsystem-noise assessments. The effects of thrust level, installation type, and rotor-inflow angle on the generated flyover noise are investigated for the historical-baseline blade set. Finally, the benefits of the modern open-rotor blade design are made apparent through comparisonof flyover noise from the second-generation and historical-baseline blade sets.

关键词： Engines

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A noise and emissions assessment of the N3-X transport 52

A noise and emissions assessment of the N3-X transport

引用

52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014

作者： Berton, Jeffrey J. Haller, William J. NASA Glenn Research Center Multidisciplinary Design Analysis and Optimization Branch MS 5-11 Cleveland OH 44135 United States

ISBN: (数字)9781624102561

ISBN: (纸本)9781624102561

Analytical predictions of certification noise and exhaust emissions for NASA's N3-X - a notional, hybrid wingbody airplane - are presented in this paper. The N3-X is a 300-passenger concept transport propelled by an array of fans distributed spanwise near the trailing edge of the wingbody. These fans are driven by electric motors deriving power from twin generators driven by turboshaft engines. Turboelectric distributed hybrid propulsion has the potential to dramatically increase the propulsive efficiency of aircraft. The noise and exhaust emission estimates presented here are generated using NASA's conceptual design systems analysis tools with several key modifications to accommodate this unconventional architecture. These tools predict certification noise and the emissions of oxides of nitrogen by leveraging data generated from a recent analysis of the N3-X propulsion system.

关键词： NASA

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Characterization of swirl-venturi lean direct injection designs for aviation gas turbine combustion

Characterization of swirl-venturi lean direct injection desi...

引用

作者： Heath, Christopher M. NASA John H. Glenn Research Center at Lewis Field ClevelandOH44135 United States Multidisciplinary Design Analysis and Optimization Branch MS 5-10 United States

Injector geometry, physical mixing, chemical processes, and engine cycle conditions together govern performance, operability, and emission characteristics of aviation gas turbine combustion systems. The present investigation explores swirl-venturi lean direct injection combustor fundamentals, characterizing the influence of key geometric injector parameters on reacting flow physics and emission production trends. In this computational study, a design space exploration was performed using a parameterized swirl-venturi lean direct injector model. From the parametric geometry, 20 three-element lean direct injection combustor sectors were produced and simulated using steady-state Reynolds-averaged Navier-Stokes reacting computations. Species concentrations were solved directly using a reduced 18-step reaction mechanism for Jet A. Turbulence closure was obtained using a nonlinear κ-Ε model. Results demonstrate sensitivities of the geometric perturbations on axially averaged flowfield responses. Output variables include axial velocity, turbulent kinetic energy, static temperature, fuel patternation, and minor species mass fractions. Significant trends have been reduced to surrogate model approximations, intended to guide future injector design trade studies and advance aviation gas turbine combustion research. Copyright © 2014 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Combustors

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Wedge shock and nozzle exhaust plume interaction in a supersonic jet flow 52

Wedge shock and nozzle exhaust plume interaction in a supers...

引用

52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014

作者： Castner, Raymond Zaman, Khairul Fagan, Amy Heath, Christopher NASA Glenn Research Center Inlet and Nozzle Branch 21000 Brookpark Road Cleveland OH 44135 United States NASA Glenn Research Center Optical Instrumentation Branch 21000 Brookpark Road Cleveland OH 44135 United States NASA Glenn Research Center Multidisciplinary Design Analysis Optimization Branch 21000 Brookpark Rd Cleveland OH 44135 United States

ISBN: (数字)9781624102561

ISBN: (纸本)9781624102561

Fundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with the nozzle exhaust plume. Aft body shock waves that interact with the exhaust plume contribute to the near-field pressure signature of a vehicle. The plume and shock interaction was studied using computational fluid dynamics and compared with experimental data from a coaxial convergent-divergent nozzle flow in an open jet facility. A simple diamond-shaped wedge was used to generate the shock in the outer flow to study its impact on the inner jet flow. Results show that the compression from the wedge deflects the nozzle plume and shocks form on the opposite plume boundary. The sonic boom pressure signature of the nozzle exhaust plume was modified by the presence of the wedge. Both the experimental results and computational predictions show changes in plume deflection.

关键词： Shock waves

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Auralization of flyover noise from open rotor engines using model scale test data 20

Auralization of flyover noise from open rotor engines using ...

引用

20th AIAA/CEAS Aeroacoustics Conference 2014

作者： Rizzi, Stephen A. Stephens, David B. Berton, Jeffrey J. Van Zante, Dale E. Wojno, John P. Goerig, Trevor W. NASA Langley Research Center Hampton VA 23681 United States NASA Glenn Research Center Cleveland OH 44135 United States GE Aviation Acoustics and Installation Aerodynamics 1 Neumann Way M/D G26 Cincinnati OH 45215 United States Aeroacoustics Branch MS 463 United States Multidisciplinary Design Analysis and Optimization Branch MS 5-11 United States

ISBN: (数字)9781624102851

ISBN: (纸本)9781624102851

A series of model scale tests were recently completed using the Open Rotor Propulsion Rig at the NASA Glenn Research Center in an effort to characterize the aero/acoustic performance of several open rotor propulsor designs. These included the historical baseline and second generation (Gen-2) blade sets. Subsequently, the Gen-2 design was assessed to have significant cumulative EPNdB margins relative to Chapter 4 noise regulations, whilst the historical blade set had a negative margin. However, integrated metrics like EPNdB are not intuitive to the layperson, and likely do not convey the noise benefits over earlier designs, for example, the acoustically unique UnDucted Fan (UDF®) Demonstrator of the 1980s. This paper develops the means of auralizing flyover noise projections of full-scale open rotor engines using model scale data in a manner that more readily communicates the noise benefit and that is consistent with previously published system noise assessments. The effect of thrust level, installation type, and rotor inflow angle on the generated flyover noise are investigated for the historical baseline blade set. Finally, the benefits of the modern open rotor blade design are made apparent through comparison of flyover noise from the Gen-2 and historical baseline blade sets.

关键词： Engines

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Modeling the deterioration of engine and low pressure compressor performance during a roll back event due to ice accretion 50

Modeling the deterioration of engine and low pressure compre...

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50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014

作者： Jorgenson, Philip C. E. Veres, Joseph P. Jones, Scott M. Turbomachinery and Heat Transfer Branch NASA Glenn Research Center 21000 Brookpark Rd /Mail Stop 5-11 ClevelandOH44135 United States Engine Icing Technical Challenge Turbomachinery and Heat Transfer Branch NASA Glenn Research Center 21000 Brookpark Rd /Mail Stop 5-11 ClevelandOH44135 United States Aerospace Engineer Multidisciplinary Design Analysis and Optimization Branch NASA Glenn Research Center 21000 Brookpark Rd /Mail Stop 5-11 ClevelandOH44135 United States

ISBN: (数字)9781624103032

ISBN: (纸本)9781624103032

The main focus of this study is to apply a computational tool for the flow analysis of the engine that has been tested with ice crystal ingestion in the Propulsion Systems Laboratory (PSL) of NASA Glenn Research Center. A data point was selected for analysis during which the engine experienced a full roll back event due to the ice accretion on the blades and flow path of the low pressure compressor. The computational tool consists of the Numerical Propulsion System Simulation (NPSS) engine system thermodynamic cycle code, and an Euler-based compressor flow analysis code, that has an ice particle melt estimation code with the capability of determining the rate of sublimation, melting, and evaporation through the compressor blade rows. Decreasing the performance characteristics of the low pressure compressor (LPC) within the NPSS cycle analysis resulted in matching the overall engine performance parameters measured during testing at data points in short time intervals through the progression of the roll back event. Detailed analysis of the fan-core and LPC with the compressor flow analysis code simulated the effects of ice accretion by increasing the aerodynamic blockage and pressure losses through the low pressure compressor until achieving a match with the NPSS cycle analysis results, at each scan. With the additional blockages and losses in the LPC, the compressor flow analysis code results were able to numerically reproduce the performance that was determined by the NPSS cycle analysis, which was in agreement with the PSL engine test data. The compressor flow analysis indicated that the blockage due to ice accretion in the LPC exit guide vane stators caused the exit guide vane (EGV) to be nearly choked, significantly reducing the air flow rate into the core. This caused the LPC to eventually be in stall due to increasing levels of diffusion in the rotors and high incidence angles in the inlet guide vane (IGV) and EGV stators. The flow analysis indicating compresso

关键词： Stators

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Characterization of swirl-venturi lean direct injection designs for aviation gas-turbine combustion 49

Characterization of swirl-venturi lean direct injection desi...

引用

49th AIAA/ASME/SAE/ASEE Joint PropulsionConference

作者： Heath, Christopher M. Multidisciplinary Design Analysis and Optimization Branch NASA Glenn Research Center MS 5-10 Cleveland OH 44135 United States

ISBN: (数字)9781624102226

ISBN: (纸本)9781624102226

Injector geometry, physical mixing, chemical processes, and engine cycle conditions together govern performance, operability and emission characteristics of aviation gas-turbine combustion systems. The present investigation explores swirl-venturi lean direct injection combustor fundamentals, characterizing the influence of key geometric injector parameters on reacting flow physics and emission production trends. In this computational study, a design space exploration was performed using a parameterized swirl-venturi lean direct injector model. From the parametric geometry, 20 three-element lean direct injection combustor sectors were produced and simulated using steady-state, Reynolds-averaged Navier-Stokes reacting computations. Species concentrations were solved directly using a reduced 18-step reaction mechanism for Jet-A. Turbulence closure was obtained using a nonlinear κ -Ε model. Results demonstrate sensitivities of the geometric perturbations on axially averaged flow field responses. Output variables include axial velocity, turbulent kinetic energy, static temperature, fuel patternation and minor species mass fractions. Significant trends have been reduced to surrogate model approximations, intended to guide future injector design trade studies and advance aviation gas-turbine combustion research.

关键词： Combustors

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Updated assessments of an open rotor airplane using advanced blade designs 49

Updated assessments of an open rotor airplane using advanced...

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49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, JPC 2013

作者： Hendricks, Eric S. Berton, Jeffrey J. Haller, William J. Tong, Michael T. USA Multidisciplinary Design Analysis & Optimization Branch NASA Glenn Research Center ClevelandOH44135 United States Aeronautics Systems Analysis Branch NASA Langley Research Center HamptonVA23681 United States

ISBN: (纸本)9781624102226

Application of open rotor propulsion systems (historically referred to as \advanced turboprops" or \propfans") to subsonic transport aircraft received significant attention and research in the 1970s and 1980s when fuel efficiency was the driving focus of aeronautical research. Recent volatility in fuel prices and concern for aviation’s environmental impact have renewed interest in open rotor propulsion, and revived research by NASA and a num- ber of engine manufacturers. Over the last few years, NASA has revived and developed analysis capabilities to assess aircraft designs with open rotor propulsion systems. These ef- forts have been described in several previous papers along with initial results from applying these capabilities. The initial results indicated that open rotor engines have the potential to provide large reductions in fuel consumption and emissions. Initial noise analysis indicated that current noise regulations can be met with modern baseline blade designs. Improved blades incorporating low-noise features are expected to result in even lower noise levels. This paper describes improvements to the initial assessment, plus a follow-on study using a more advanced open rotor blade design to power the advanced single-aisle transport. The predicted performance and environmental results of these two advanced open rotor concepts are presented and compared. © 2013, American Institute of Aeronautics and Astronautics Inc. All rights reserved.

关键词： NASA

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Updated assessments of an open rotor airplane using advanced blade designs

Updated assessments of an open rotor airplane using advanced...

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49th AIAA/ASME/SAE/ASEE Joint PropulsionConference

作者： Hendricks, Eric S. Berton, Jeffrey J. Haller, William J. Tong, Michael T. Guynn, Mark D. Multidisciplinary Design Analysis and Optimization Branch NASA Glenn Research Center MS 5-11 Cleveland OH 44135 United States NASA Langley Research Center Aeronautics Systems Analysis Branch Mail Stop 442 Hampton VA 23681 United States

ISBN: (纸本)9781624102226

Application of open rotor propulsion systems (historically referred to as "advanced tur-boprops" or "propfans") to subsonic transport aircraft received significant attention and research in the 1970s and 1980s when fuel efficiency was the driving focus of aeronautical research. Recent volatility in fuel prices and concern for aviation's environmental impact have renewed interest in open rotor propulsion, and revived research by NASA and a number of engine manufacturers. Over the last few years, NASA has revived and developed analysis capabilities to assess aircraft designs with open rotor propulsion systems. These efforts have been described in several previous papers along with initial results from applying these capabilities. The initial results indicated that open rotor engines have the potential to provide large reductions in fuel consumption and emissions. Initial noise analysis indicated that current noise regulations can be met with modern baseline blade designs. Improved blades incorporating low-noise features are expected to result in even lower noise levels. This paper describes improvements to the initial assessment, plus a follow-on study using a more advanced open rotor blade design to power the advanced single-aisle transport. The predicted performance and environmental results of these two advanced open rotor concepts are presented and compared.

关键词： NASA

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Advanced single-aisle transport propulsion design options revisited

Advanced single-aisle transport propulsion design options re...

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2013 Aviation Technology, Integration, and Operations Conference

作者： Guynn, Mark D. Berton, Jeffrey J. Tong, Michael T. Haller, William J. NASA Langley Research Center Aeronautics Systems Analysis Branch Mail Stop 442 Hampton VA 23681 United States NASA Glenn Research Center Multidisciplinary Design Analysis and Optimization Branch MS 5-11 Cleveland OH 44135 United States

ISBN: (数字)9781624102257

ISBN: (纸本)9781624102257

Future propulsion options for advanced single-aisle transports have been investigated in a number of previous studies by the authors. These studies have examined the system level characteristics of aircraft incorporating ultra-high bypass ratio (UHB) turbofans (direct drive and geared) and open rotor engines. During the course of these prior studies, a number of potential refinements and enhancements to the analysis methodology and assumptions were identified. This paper revisits a previously conducted UHB turbofan fan pressure ratio trade study using updated analysis methodology and assumptions. The changes in propulsion, airframe, and noise modeling are described and discussed. The impacts of these changes are then examined by comparison to the previously reported results. The changes incorporated have decreased the optimum fan pressure ratio for minimum fuel consumption and reduced the engine design trade-offs between minimizing noise and minimizing fuel consumption. Nacelle drag and engine weight are found to be key drivers in determining the optimum fan pressure ratio from a fuel efficiency perspective. The revised noise analysis results in the study aircraft being 2 to 4 EPNdB (cumulative) quieter due to a variety of reasons explained in the paper. With equal core technology assumed, the geared engine architecture is found to be as good as or better than the direct drive architecture for most parameters investigated. However, the engine ultimately selected for a future advanced single-aisle aircraft will depend on factors beyond those considered here.

关键词： Propulsion

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