Stability Analysis of Reacting Wakes: Flow and Density Asymmetry Effects

Emerson, Benjamin; Jagtap, Swapnil S.; Lieuwen, Tim

doi:10.2514/6.2015-0429

Cited by 7 publications

(3 citation statements)

References 23 publications

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“…In terms of propulsion, there are advanced technologies like ultra-high bypass ratio turbofan engines, hybrid-electric and full-electric concepts [12]. The future aircraft engines will have cleaner/lowemissions and improved combustors [13], [14]. Such combustors will control combustion instabilities, a phenomenon observed in present-day aircraft combustors [13], [14].…”

Section: Future Aviation Technologiesmentioning

confidence: 99%

“…The future aircraft engines will have cleaner/lowemissions and improved combustors [13], [14]. Such combustors will control combustion instabilities, a phenomenon observed in present-day aircraft combustors [13], [14]. These next generation of improved combustors further increase the safety aspect of an aircraft [13], [14].…”

Section: Future Aviation Technologiesmentioning

confidence: 99%

“…Such combustors will control combustion instabilities, a phenomenon observed in present-day aircraft combustors [13], [14]. These next generation of improved combustors further increase the safety aspect of an aircraft [13], [14]. Alternative fuels viz.…”

Section: Future Aviation Technologiesmentioning

confidence: 99%

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Systems Evaluation of Subsonic Hybrid-Electric Propulsion Concepts for NASA N+3 Goals and Conceptual Aircraft Sizing

Jagtap

2019

IJAME

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The air-travel demand is anticipated to grow in future and therefore the worldwide airtraffic is forecast to increase significantly. This growth in demand further increases the concerns pertaining to environmental and human health, which results in stringent aviation policies. Emission regulations have been set for the aviation sector to reduce its climate change impacts, and these support the efforts to meet the goals of the UN’s Paris treaty on climate change. The aviation sector is exploring sustainable and improved technologies to become more energy and cost efficient. Along these lines, NASA has developed the concept of ‘N+i’ goals to decrease fuel consumption, noise, and landing and take-off (LTO) oxides of nitrogen (NOx) emissions, and to enhance aircraft performance. The ‘N+3’ represents three technology generations into the future, where ‘N’ represents the current aircraft generation, with a forecasted technology readiness level 4-6, in year 2025 timeframe which will enable year 2035 service-entry. To meet NASA’s N+3 goals, significant improvements must be made in the air transportation system, airframe, mission design, and propulsion systems. A pivotal element to achieve these goals, is the propulsion system. This is because the role of propulsion system can be crucial in reducing emissions, noise, and fuel burn. This work evaluates the N+3 concepts in detail, based on the systems engineering approaches and selects the best of those concepts. A detailed analysis is presented for phase one of such a project using Georgia Institute of Technology’s Integrated Product-Process Development (IPPD) method. This work finds that the NASA N3-X turbo-electric distributed propulsion (TeDP) is the best concept for meeting the NASA N+3 goals, based on the systems engineering approach.

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Section: Future Aviation Technologiesmentioning

confidence: 99%

Section: Future Aviation Technologiesmentioning

confidence: 99%

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Systems Evaluation of Subsonic Hybrid-Electric Propulsion Concepts for NASA N+3 Goals and Conceptual Aircraft Sizing

Jagtap

2019

IJAME

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Assessment of feedstocks for blended alcohol-to-jet fuel manufacturing from standalone and distributed scheme for sustainable aviation

Jagtap

2019

AIAA Propulsion and Energy 2019 Forum

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Correction: Assessment of feedstocks for blended alcohol-to-jet fuel manufacturing from standalone and distributed scheme for sustainable aviation

Jagtap

2019

AIAA Propulsion and Energy 2019 Forum

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There is typographical error in Figure 3 for PM 10 of Standalone forest residue (S.FR) case. There should be a ( -) sign instead of (+) sign. The figure now reads -1.6% instead of +1.6% for S.FR case. The corrected Figure 3 is as follows, which is followed by change in description of the said figure. Additionally, based on this correction there is a slight correction to the conclusion section, which is listed below the above corrections.

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Stability Analysis of Reacting Wakes: Flow and Density Asymmetry Effects

Cited by 7 publications

References 23 publications

Systems Evaluation of Subsonic Hybrid-Electric Propulsion Concepts for NASA N+3 Goals and Conceptual Aircraft Sizing

Systems Evaluation of Subsonic Hybrid-Electric Propulsion Concepts for NASA N+3 Goals and Conceptual Aircraft Sizing

Assessment of feedstocks for blended alcohol-to-jet fuel manufacturing from standalone and distributed scheme for sustainable aviation

Correction: Assessment of feedstocks for blended alcohol-to-jet fuel manufacturing from standalone and distributed scheme for sustainable aviation

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