NASA Environmentally Responsible Aviation Project's Propulsion Technology Phase I Overview and Highlights of Accomplishments

Suder, Kenneth L.; DeLaat, John C.

doi:10.2514/6.2013-414

Cited by 17 publications

(12 citation statements)

References 14 publications

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“…Unique to ERA, NASA required substantial industry cost share and was constrained to a 6 year period of performance. See References [91][92][93] for more background on the ERA project. This section of the paper will highlight the propulsion elements of the ERA technology portfolio inclusive of the core compressor, propulsor, and combustor technology demonstrations.…”

Section: Nasa Collaborations and Technology Demonstrations That Are Making Their Way In To Future Productsmentioning

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: Nasa Collaborations and Technology Demonstrations That Are Making Their Way In To Future Productsmentioning

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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“…The results of the previous generation (LDI-1) efforts were summarized by [Lee 2007] and , and some highlights of current generation (LDI-2) efforts have been reported by and [Suder 2013]. …”

Section: Introductionmentioning

confidence: 98%

CFD Computations of Emissions for LDI-2 Combustors with Simplex and Airblast Injectors

Ajmani¹,

Mongia²,

Lee³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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An effort was undertaken to perform CFD analysis of fluid flow in Lean-Direct Injection (LDI) combustors with axial swirl-venturi elements for the next-generation LDI-2 design. The National Combustion Code (NCC) was used to perform non-reacting and reacting flow computations on several LDI-2 injector configurations in a thirteen-element injector array for different operating conditions. All computations were performed with a consistent approach of mesh-optimization, spray-modeling, ignition and kinetics-modeling with the NCC. Computational predictions of emissions (EINOx, EICO and UHC) were compared with the two sets of experimental data representing respectively low-pressure and highpressure engine cycle conditions.

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“…Recent trends in civil aviation engines indicate an increasing bypass ratio (BPR) in order to improve fuel efficiency of the aircraft engine (Suder, 2013). A high BPR means a large fan diameter that would require a larger and heavier nacelle.…”

Section: Introductionmentioning

confidence: 99%

Design and Optimization of a Nacelle for a UHBR Turbofan engine using a Class Shape Transformation based parameterization

Benjamin¹,

Heykena²,

Friedrichs³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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This paper deals with the design of an isolated axisymmetric nacelle for an Ultra-High Bypass Ratio (UHBR) engine. The intake, fan cowl, bypass duct and bypass nozzle are designed and optimized using a nacelle design system, established by combining an automated CFD analysis framework with an optimization algorithm. The optimization algorithm is based on an adaptive response surface methodology (RSM), which uses Kriging approximation to generate the surface model. The entire nacelle is parameterized using an intuitive Class shape transformation (iCST) approach. The optimization was conducted separately for the intake-cowl and exhaust system assuming minimal aerodynamic interactions between the two. The final optimized design had 26.9 Drag counts at cruise. The response surface was able to predict the cruise drag to 6% accuracy. The optimized bypass nozzle gave a maximum velocity coefficient (C V) of 0.9914 at a corresponding discharge coefficient (C D) of 0.995.

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NASA Environmentally Responsible Aviation Project's Propulsion Technology Phase I Overview and Highlights of Accomplishments

Cited by 17 publications

References 14 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

CFD Computations of Emissions for LDI-2 Combustors with Simplex and Airblast Injectors

Design and Optimization of a Nacelle for a UHBR Turbofan engine using a Class Shape Transformation based parameterization

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