Exergy-Based Performance Analysis of a Turbojet Engine

Abbas, Mohammad; Riggins, David W.

doi:10.2514/6.2016-4638

Cited by 7 publications

(3 citation statements)

References 11 publications

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“…The present work is also related to previous investigations ( [9,10]) that sought to characterize gas turbine (turbojet and ramjet) transient behavior by employing energy utilization/entropy generation analysis. Abbas and Riggins [11] in prior work investigated energy utilization and entropy generation for a turbojet engine model without airframe considerations; focusing primarily on presenting uninstalled performance and providing related energy utilization information.…”

Section: Introductionmentioning

confidence: 99%

“…This work (along with earlier complementary work described in [11]) is unique in employing a control volume/energy utilization analysis that explicitly includes the wake (and the entropy generation occurring therein) for the analysis of a gas turbine engine from a second-law/exergetic perspective. It is also the first exergy analysis of a turbojet engine utilizing that approach that analyzes a given engine over a range of 'off-design' conditions, as opposed to employing cycle analysis assumptions and limitations.…”

Section: Introductionmentioning

confidence: 99%

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Analysis of Energy Utilization and Losses for Jet-Propelled Vehicles

Abbas

Riggins

2021

Aerospace

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The global control volume-based energy utilization balance for an aerospace vehicle is extended to allow for the analysis of jet-propelled vehicles. The methodology is first developed for analyzing the energy utilization and entropy generation characteristics of jet engines without airframe considerations. This methodology, when combined with separate energy utilization analysis for an unpowered airframe, allows for the assessment of a powered vehicle. Wake entropy generation for a powered vehicle is shown to be the summation of the wake entropy generation associated with the propulsion system (no airframe) and the unpowered airframe. The fundamental relationship between overall entropy generation and the flight conditions required for maximum range and endurance of a powered vehicle are also derived. Example energy utilization results obtained for a modeled turbojet engine in off-design operation are provided; wake and engine component entropy generation characteristics are directly related to engine operation and flight conditions. This engine model is then integrated with a legacy (twin-engine) Northrop F-5E Tiger II airframe. The overall entropy generation temporal rate for the vehicle is minimized, as predicted by our analysis, at flight conditions corresponding to maximum endurance. For flight conditions corresponding to maximum range, the overall entropy spatial rate is minimized.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Analysis of Energy Utilization and Losses for Jet-Propelled Vehicles

Abbas

Riggins

2021

Aerospace

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“…[1,2] In aerospace application, systems exergy has mainly been applied to aircraft design, analysis, and optimization. It has been applied in various system contexts including lunar base thermal energy designs [3], aircraft system design [4,5,6,7], analysis, and optimization, aircraft engine analysis [8,9,10,11,12], aircraft environmental control [13], pulsed detonation power devices [14], and hypersonics [1,15]. Interesting comparisons between exergy S balance equation and the Breguet range equation have also been done for aircraft [16].…”

Section: Introductionmentioning

confidence: 99%

System Exergy: System Integrating Physics of Launch Vehicles and Spacecraft

Watson

2018

Journal of Spacecraft and Rockets

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System Engineering of launch vehicles and spacecraft is a challenging and complex under taking. There are many diverse systems which must be integrated and balanced to produce an effective design. This involves a multiplicity of individual engineering relationships that are difficult to integrate and even more difficult to define in a best balance. Integration efforts involve many different approaches from process management to mass balance. But these approaches either do not directly address the launch vehicle or spacecraft performance or require many adjustments to be made to discover a balance. The system integrating physics, derived from the fundamental physics of the system, is the key to identifying a fully integrated system performance measure. Launch vehicles and spacecraft are thermodynamic systems with performance defined by thermodynamic properties. Thus, thermodynamic exergy, which integrates all of the systems thermodynamic properties, provides the system integrating relationships. This provides a basis for determining the most efficient design from among many different configuration options and for guiding the design activities from an integrated system level. This paper explores the current physics relationships used in launch vehicle system design and demonstrates that thermodynamic exergy provides a more explicit and complete approach to system integration.

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