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Comparison of Overwing and Underwing Nacelle Aeropropulsion Optimization for Subsonic Transport Aircraft

JOURNAL OF AIRCRAFT 2024年第2期61卷 638-653页

作者： Ahuja, Jai Lee, Chung Hyun Perron, Christian Mavris, Dimitri N. Georgia Inst Technol Sch Aerosp Engn Aerosp Syst Design Lab Atlanta GA 30332 USA

This research compares a forward-mounted overwing nacelle configuration to a conventional underwing nacelle for a single-aisle transport aircraft. We focus on characterizing the impact of the overwing placement on cruise fuel burn. To this end, we optimize both configurations under similar constraints and design processes. We use coupled computational fluid dynamics and propulsion cycle analysis with Gaussian process-based adaptive sampling in a multistage design process. The particular overwing design has a 4% higher fuel flow than the underwing design at cruise conditions. However, a postoptimization nacelle placement study illustrates that this fuel burn difference can drop to 2-3% if the overwing nacelle is moved farther forward in our design space without accounting for any resulting structural weight changes.

关键词： numerical propulsion system simulation Cumulative Distribution Function Aerodynamic Interference Aerodynamic Performance Multidisciplinary Design Analysis and Optimization Computational Modeling Computational Fluid Dynamics Aircraft Overwing Nacelle

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propulsion system Modeling and Reduction for Conceptual Truss-Braced Wing Aircraft Design

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INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES 2017年第4期18卷 651-661页

作者： Lee, Kyunghoon Nam, Taewoo Kang, Shinseong Pusan Natl Univ Busan 46241 South Korea Toyota Res Inst North Amer Ann Arbor MI 48105 USA

A truss-braced wing (TBW) aircraft has recently received increasing attention due to higher aerodynamic efficiency compared to conventional cantilever wing aircraft. For conceptual TBW aircraft design, we developed a propulsion-and-airframe integrated design environment by replacing a semi-empirical turbofan engine model with a thermodynamic cycle-based one built upon the numerical propulsion system simulation (NPSS). The constructed NPSS model benefitted TBW aircraft design study, as it could handle engine installation effects influencing engine fuel efficiency. The NPSS model also contributed to broadening TBW aircraft design space, for it provided turbofan engine design variables involving a technology factor reflecting progress in propulsion technology. To effectively consolidate the NPSS propulsion model with the TBW airframe model, we devised a rapid, approximate substitute of the NPSS model by reduced-order modeling (ROM) to resolve difficulties in model integration. In addition, we formed an artificial neural network (ANN) that associates engine component attributes evaluated by object-oriented weight analysis of turbine engine (WATE++) with engine design variables to determine engine weight and size, both of which bring together the propulsion and airframe system models. Through propulsion-and-airframe design space exploration, we optimized TBW aircraft design for fuel saving and revealed that a simple engine model neglecting engine installation effects may overestimate TBW aircraft performance.

关键词： numerical propulsion system simulation Reduced-order modeling Artificial neural networks propulsion-and- airframe integrated design Truss-braced wing aircraft

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An Approach to Evaluating the Impact of Small-core Turbofan Technologies on Engine and Aircraft Performance

An Approach to Evaluating the Impact of Small-core Turbofan ...

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AIAA SciTech Forum

作者： Bennett, Michael A. Chapman, Jeffryes W. Wells, Douglas P. NASA Glenn Res Ctr Prop Syst Anal Branch 21000 Brookpk Rd Cleveland OH 44135 USA NASA Langley Res Ctr Aeronaut Syst Anal Branch Mail Stop 442 Hampton VA 23681 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

NASA's Hybrid Thermally Efficient Core (HyTEC) project aims to accelerate the development of small-core turbofan engine technologies to enable a fuel burn reduction of 5 to 10 percent for next-generation aircraft, compared to 2020s best-in-class technology. This paper presents a demonstration of methods for evaluating the potential performance impact of small-core engine technologies developed under Phase 1 of the HyTEC project. The approach involves model-based systems analysis, where small-core innovations are integrated into baseline turbofan and aircraft systems models, creating a notional vision system. Performance of the vision system is examined at both the engine and vehicle level. The examined performance metrics include: engine bypass ratio, overall pressure ratio, high pressure compressor exit corrected mass flow, and aircraft fuel burn. The CFM LEAP-1B28 and Boeing 737 MAX 8 are chosen as the baseline state-of-the-art systems. Preliminary results map a design space for the small-core vision system and quantify the distinct effects of technologies on the key metrics.

关键词： Turbofan Engines Aircraft Performance Mass Flow Overall Pressure Ratio Commercial Aircraft Turbine Inlet Temperature numerical propulsion system simulation Aerodynamic Design Flight Optimization system Turbomachinery

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Methodology for Development of Complete Engine Deck for a Low Bypass Turbofan Engine 18

Methodology for Development of Complete Engine Deck for a Lo...

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18th International Bhurban Conference on Applied Sciences and Technologies (IBCAST)

作者： Ahmed, Sabih Sajjad Zeb, Muhammad Kamran Salamat, Shuaib Univ Leicester Sch Engn Leicester Leics England Air Univ Dept Aerosp Engn Kamra Pakistan

ISBN: (纸本)9781665405164

This paper presents a parametric and performance cycle analysis of a high performance aircraft engine using numerical propulsion system simulation (NPSS). NPSS is an object oriented tool developed for the modeling and analysis of propulsion systems based on aerothermodynamic equations. A low bypass mixed-flow turbofan engine with data for both design and off-design performance parameters available in literature is modeled in the numerical environment. The component characteristics are iterated as part of the modeling procedure. The design and off design simulations are carried out for the entire flight envelope and the performance deck is validated using the data of the modeled engine presented in the literature. The presented model may serve as a baseline for modeling and simulation of jet engines for academic and research purposes.

关键词： numerical propulsion system simulation low bypass turbofan performance deck

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Engine Cycle Adaptation Method for Aircraft On-Board systems Evaluation Considering system-Engine Interaction

Engine Cycle Adaptation Method for Aircraft On-Board Systems...

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AIAA SciTech Forum

作者： Kriewall, Vivian Junemann, Marc Thielecke, Frank Hamburg Univ Technol Inst Aircraft Syst Engn D-21129 Hamburg Germany

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

In the assessment of different aircraft on-board systems (OBS) using mission-level metrics like fuel burn, typically the same engine performance model is employed. One example is the comparison of conventional versus bleedless architectures with respect to their impact on mission block fuel. However, especially with the application of ultra-high bypass ratio (UHBR) turbofans, the cycle performance of such engines increasingly varies depending on the power offtakes (POT) requirements of the considered OBS architecture. This paper proposes a method for adapting the thermodynamic engine cycle to accommodate OBS POT requirements based on a given reference cycle. The method iteratively adjusts relevant engine design parameters by employing physical and semi-empirical correlations. The gas turbine simulation software NPSS is embedded into this process, ultimately posing the adapted cycle design point based on the input design parameters. The presented method is applied in the scope of an OBS architecture trade study for a modern mid-range concept aircraft. The results show a -0.7% reduction in block fuel mass for a bleedless OBS architecture with an adapted bleedless engine compared to the same bleedless architecture in combination with a conventional reference engine designed for bleed offtakes. This highlights the importance of integrated OBS architecture studies, for which the engine's cycle design point and the employed engine performance model is adapted to the POT requirements for more accurate evaluation results.

关键词： Aircrafts numerical propulsion system simulation Thrust Specific Fuel Consumption Turbofan Engines Gas Turbine simulation Software Thermodynamic Engine Mass Flow Rate Bleed Air system Architectures

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Influence of Turbofan Engine Design Parameters on Aircraft Environmental Impact

Influence of Turbofan Engine Design Parameters on Aircraft E...

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AIAA SciTech Forum

作者： Lee, Kanghyun Bobadilla, Diego A. Salgado Prashanth, Prakash Speth, Raymond L. Sabnis, Jayant S. Eastham, Sebastian D. Barrett, Steven R. H. MIT Dept Aeronaut & Astronaut Cambridge MA 02139 USA MIT Ctr Global Change Sci Cambridge MA 02139 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Despite the emergence of new energy carriers and propulsion systems, turbofan engines continue to power the majority of commercial aircraft and drive aviation's environmental impacts. Hence, turbofan engines should be designed with an understanding of each design parameter's environmental implications. By modeling aircraft, engines, operations, emissions, and the climate and air quality impacts, we can evaluate the environmental outcomes of an engine design change. This paper presents sensitivities of environmental impacts to engine design parameters, focusing on free design variables such as overall pressure ratio (OPR), fan pressure ratio (FPR), and turbine entry temperature (TET), as well as technology level indicators such as material temperature capability, cooling requirements, and component efficiencies. Sensitivities are calculated for three reference baseline engines, and the differences in trends between the engines are analyzed. Finally, we also explore how the derived sensitivities can provide guidance to stakeholders when making decisions on technological investments, design space change, and environmental regulations.

关键词： Turbofan Engines Commercial Aircraft Overall Pressure Ratio numerical propulsion system simulation Aviation Contrails Fuel Consumption Cooling Technology Astronautics Aeronautics

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Failure Behavior and Control-Based Mitigation for a Parallel Hybrid propulsion system

Failure Behavior and Control-Based Mitigation for a Parallel...

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AIAA SciTech Forum

作者： Kratz, Jonathan L. Simon, Donald L. NASA Glenn Res Ctr Intelligent Control & Auton Branch Cleveland OH 44135 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

NASA is pursuing research to advance Electrified Aircraft propulsion (EAP) technologies that address fuel burn and emission reduction goals. EAP brings the potential for improved performance over the state-of-the-art. However, for these systems to be practical and certifiable, they need to possess adequate robustness to adverse conditions including a variety of system failures that are not applicable to conventional turbofans today. Numerous EAP concepts interface gas turbine engines with an electrical power system that includes electric machines and sometimes electrical energy storage. The expansion of the powertrain increases the probability of encountering a failure and introduces new failure modes. Failures within the electrical power system may also impact the gas turbine engine(s) to which the electrical powertrain is coupled. This effort investigates failures originating in the electrical power system and their impact on the parallel hybrid propulsion system. Reversionary control strategies are also demonstrated to reduce the impact of the failures. Failure mitigation strategies were devised and employed in simulation. Various failure scenarios were simulated including those occurring during steady-state operation, transients, and takeoff and landing scenarios. The timing of the failure and delay in failure identification and activation of mitigation strategies are noteworthy variables in the study. While the system remained stable throughout all failure scenarios, delays in failure identification could result in undesirable conditions such as increased operating temperatures and reduced stall margin. The results demonstrate successful mitigation of failures through reversionary control modes and help to generate confidence in the robustness of the conceptual parallel hybrid propulsion system.

关键词： numerical propulsion system simulation Electrified Aircraft propulsion Electrical Energy Storage Power system Variable Bleed Valve Turbofan NASA Take off and Landing Auxiliary Power Unit Turbine Inlet Temperature

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A Performance Model for High-BPR Turbofan Engines

A Performance Model for High-BPR Turbofan Engines

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AIAA SciTech Forum

作者： Lord, Wesley K. South Glastonbury 06073 CT United States

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

A performance model for high bypass ratio turbofan engines is described. Overall system performance comprises three power conversion steps: 1) conversion of fuel heat release power to hot gas power;2) conversion of hot gas power to shaft power;3) conversion of shaft power to propulsive power. Physical control volumes within the engine system are associated with each of the power conversion processes, and power conversion efficiencies are defined - thermal, transfer, and propulsive. A shaft power efficiency, the net effect of the first two steps, is also defined. Example applications of the performance model and some performance trends over a range of engine design space are presented. This approach is thought to be useful for purposes of understanding the basic physics that drives performance trends and for comparison of gas turbine engine performance to other types of aircraft propulsion systems, for example hydrogen fuel cell with electric drive train.

关键词： Turbofan Engines numerical propulsion system simulation Thrust Specific Fuel Consumption Aeroderivative Gas Turbines Fuel Heating Hydrogen Fuels Heat Capacity Ratio Disk Loading Mass Flow Isentropic Expansion

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Evaluation of a Subsonic Fluidic Thrust Vectoring Concept - Part II: Impact on propulsion system and Mission Performance

Evaluation of a Subsonic Fluidic Thrust Vectoring Concept - ...

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AIAA Aviation Forum

作者： Remiger, Jonas Schwagerus, N. Stoessel, M. Kozulovic, D. Krummenauer, M. Univ Bundeswehr Munich Inst Jet Prop Dept Aeronaut Engn Werner Heisenberg Weg 39 D-85577 Neubiberg Germany Bundeswehr Tech Ctr Aircraft & Aeronaut Equipment Flugpl D-85077 Manching Germany

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

This paper presents an investigation into the feasibility and performance of fluidic thrust vector control based on the Coanda effect for smaller aircraft. The study focuses on medium-mass unmanned airborne systems and demonstrates that fluidic thrust vector nozzles are viable at both the engine and aircraft level. A fully coupled simulation between the aircraft and its engine is conducted for an example generic mission with two variants to deflect the thrust vector. The results show that using fluidic thrust vectoring systems can lead to slight improvements in aerodynamic characteristics while reducing control surface size and thereby drag and radar cross-section. However, this comes at the cost of a slight increase in fuel consumption and a loss in the available engine thrust during flight situations with high power demand. The aerodynamic parameters used to model the fluidic thrust vector nozzle are obtained from CFD calculations. This paper is the subsequent paper of "Evaluation of a subsonic fluidic thrust vectoring concept - Part I: numerical investigation of the steady and transient behaviour.

关键词： Thrust Vector Control numerical propulsion system simulation Aerodynamic Characteristics Unmanned Airborne system Control Surface Sizing Fuel Consumption RADAR Mass Flow Centrifugal Compressor Simulink

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Hybrid-Electric Aero-propulsion Controls Testbed Results with Energy Storage

Hybrid-Electric Aero-Propulsion Controls Testbed Results wit...

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AIAA Aviation Forum

作者： Bianco, Santino J. Kratz, Jonathan L. Culley, Dennis E. Buescher, Halle E. Horning, Marcus A. Saus, Joseph R. Sachs-Wetstone, Jonah J. Connolly, Joseph W. NASA Glenn Res Ctr Intelligent Control & Auton Branch Cleveland OH 44135 USA HX5 LLC Brookpark OH 44142 USA

ISBN: (数字)9781624107047

ISBN: (纸本)9781624107047

Electrified aircraft propulsion (EAP) research is a priority of the National Aeronautics and Space Administration (NASA) for its potential to increase propulsion system efficiency, performance, and operability at the subsystem and vehicle levels while decreasing emissions. These EAP systems demand more advanced control algorithms due to increased complexity. NASA has developed a reconfigurable, hardware-in-the-loop rig to verify control algorithm performance using a sub-scale electro-mechanical system. A novel capability of this rig is the ability to test full scale EAP control algorithms on a sub-scale representation of the electromechanical system without turbomachinery/rotors. A novel feature is the use of a physical energy storage device within the electro-mechanical system. A dual spool, parallel hybridelectric turbofan architecture and energy management control system is tested with the goal of verifying the ability to obtain turbomachinery model operability benefits while controlling sub-scale electro-mechanical hardware. Pre-test predictions of the turbofan model, control, and rig performance were obtained through simulation using a software model of the rig. Theoretical results showing the true performance of the turbofan model were obtained through a software simulation using full-scale mechanical shaft models. The paper compares theoretical, predicted, and actual test results from the turbofan model, energy management control and rig perspectives. The results show that the presence of sub-scale electromechanical hardware did not inhibit the energy management algorithm from achieving turbomachinery operability benefits.

关键词： Energy Storage Turbomachinery Design Turbofan Engines Algorithm Performance numerical propulsion system simulation Energy Management National Aeronautics and Space Administration Real Time system propulsion Control Aircraft propulsion

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