On the exergetic effectiveness of combined-cycle engines for high speed propulsion

Fernandez-Villace, Victor; Paniagua, Guillermo

doi:10.1016/j.energy.2012.11.051

Cited by 29 publications

(3 citation statements)

References 15 publications

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“…ULB, VKI and GDL undertook a preliminary design review upon inception of the project. The pre-cooled ATR cycle analysis was assessed both in a broad way by ULB [12] [13] and in a detailed manner by VKI and is discussed extensively in [14][15] [16] [17][18] [19] . The GDL trajectory code, ABSyS, was employed to model the trajectory.…”

Section: A2 Vehicle Structural Design and Aero-elasticity Assessmentmentioning

confidence: 99%

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Steelant¹,

Varvill²,

Defoort³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The design of hypersonic airbreathing vehicles is a challenging objective due to the intrinsic complexity of propulsion-airframe integration in combination with an engine cycle design able to operate over a wide Mach number range. This is one of the objectives of EC co-funded project LAPCAT-II aiming to reduce antipodal flights to less than 2 to 4 hours. Among the several studied vehicles in the preceding project LAPCAT-I, only aircraft designs for Mach 5 and 8 flights were retained in the present project. Starting from the available Mach 5 vehicle and its related pre-cooled turbo-ramjet, assumed performance figures of different components were now assessed in more detail numerically and experimentally. Though the cruise flight of the Mach 8 vehicle based on a scramjet seemed feasible, further refinement was needed. In support to the integrated vehicle design, dedicated aerodynamic and propulsive experiments were done for the different components as well as for the complete vehicle. This included also the mutual verification of the windtunnels within Europe. In parallel, modelling implementation and validation on high-speed aerodynamics and propulsion were performed. The validated tools gave confidence to assess the performances of the fully integrated vehicles to comply with the mission goals. Finally, the impact of the emissions onto the climate was evaluated. Nomenclature

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Section: A2 Vehicle Structural Design and Aero-elasticity Assessmentmentioning

confidence: 99%

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Steelant¹,

Varvill²,

Defoort³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…Scimitar engine has been the topic of many studies. Villace and Paniagua (2013) carried out an analysis of the engine to determine its energy-based performance indicators of propulsive efficiency and thermal effectiveness. The energy and NOx emissions of the engine was studied by Tanbay et al ( 2020) through a thermodynamic model, while an exergy-based ecological analysis of the system was performed by .…”

Section: Introductionmentioning

confidence: 99%

Energy Efficiency Evaluation and Forecasting of the Sussex Ports to Address Climate Change Concerns: a Data-driven Decision Model

AYMELEK,

Kurt

2023

SSRN Journal

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“…Numerous research studies have been conducted on pre-cooling combined engines inspired by the progress of the SABRE engine (Zhengping, 2015;Zhang et al, 2017;Yuan, 2020;Zheng-ping, 2021). Fernández- Villacé and Paniagua (2013) indicated that a pre-cooled engine based on a closed cycle improves efficiency by recovering thermal energy from the freestream and aeroshell. However, the classic efficiency figures based on firstprinciple analyses were inaccurate performance indicators for the resulting combined cycle.…”

Section: Introductionmentioning

confidence: 99%

Effects of key parameters on performance of a pre-cooled core engine based on the closed helium cycle

Tong-Ling,

Xue-Feng,

Guo-Dong

et al. 2023

Front. Mech. Eng.

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A pre-cooled combined engine based on a closed helium (He) cycle offers high specific thrust and high specific impulse. Therefore, evaluation of the performance of such an engine is crucial for engine applications and key technology research. This study employs an analytical approach to investigate the effects of key parameters on the performance of a pre-cooled core engine, assuming a perfect gas model. The findings revealed that the specific thrust and specific impulse of the pre-cooled core engine are related to the pressurized coefficient of the airflow passage and equivalence ratio (ER). An increase in the pressurized coefficient leads to an increase in both specific thrust and specific impulse. However, within a certain range, although the specific thrust is positively correlated with the ER, the specific impulse is greatly reduced. With specific component parameters and a fixed thermodynamic cycle, a minimum ER exists, which satisfies the cycle-matching requirement. Moreover, the value of the minimum ER is related to the closed-cycle efficiency. For a pre-cooled core engine with a simple closed He cycle, the minimum ER is approximately 2.5–3.5.

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On the exergetic effectiveness of combined-cycle engines for high speed propulsion

Cited by 29 publications

References 15 publications

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Achievements Obtained for Sustained Hypersonic Flight within the LAPCAT-II project

Energy Efficiency Evaluation and Forecasting of the Sussex Ports to Address Climate Change Concerns: a Data-driven Decision Model

Effects of key parameters on performance of a pre-cooled core engine based on the closed helium cycle

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