Simulation of a Combined Cycle for High Speed Propulsion

Fernandez-Villace, Victor; Paniagua, Guillermo

doi:10.2514/6.2010-1125

Cited by 14 publications

(6 citation statements)

References 2 publications

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“…While N P R increases, both the standard gross thrust and base drag increase. This results in a region where drag forces are dominant as M ∞ approaches the supersonic regime (1.1-1.2) at low to medium N P Rs (5)(6)(7)(8)(9)(10)(11)(12)(13)(14)(15). At M ∞ <0.8, even for low N P Rs, the GP F is positive due to the drag forces being low.…”

Section: Impact Of Cavity On the Aerodynamic Performancementioning

confidence: 99%

“…This class of engines features a heat exchanger which is incorporated to deeply cool down the incoming air prior to compression, thus extending the operational range of the downstream turbomachinery. Several concepts based on this principle have been investigated theoretically and experimentally over the years [8] and have been found to exhibit significant efficiency improvements compared to contemporary chemical rocket engines [9,10,11]. Studies on the conceptual development of propulsive architectures that are derived from the aforementioned pre-cooled concepts, but are tailored to sustainable high-speed flight rather than space access, have also been reported in the public domain [12].…”

Section: Introductionmentioning

confidence: 99%

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Propulsion Aerodynamics for a Novel High-Speed Exhaust System

Tsentis,

Goulos,

Prince

et al. 2023

Journal of Engineering for Gas Turbines and Power

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A key requirement to achieve sustainable high-speed flight and efficiency improvements in space access lies in the advanced performance of future propulsive architectures. Such concepts often feature high-speed nozzles, similar to rocket engines, but employ different configurations tailored to their mission. Additionally, they exhibit complex interaction phenomena between high-speed and separated flow regions at the base, which are not yet well understood. This paper presents a numerical investigation on the aerodynamic performance of a representative, novel exhaust system, which employs a high-speed nozzle and a complex-shaped cavity region at the base. Reynolds-Averaged Navier–Stokes computations are performed for a number of nozzle pressure ratios (NPRs) and freestream Mach numbers in the range of 2.7 < NPR < 24 and 0.7 < M∞ < 1.2, respectively. The corresponding Reynolds number lies within the range of 1.06 × 106 < Red < 1.28 × 106 based on the maximum diameter of the configuration. The impact of the cavity is revealed by direct comparison to an identical noncavity configuration. Results show a consistent trend of increasing base drag with increasing NPR for both configurations, owing to the jet entrainment effect. Cavity is found to have no impact on the incipient separation location of the nozzle flow. At conditions of M∞ = 1.2 and high NPRs, the cavity has a significant effect on the aerodynamic performance, transitioning nozzle operation to underexpanded conditions. This results in approximately 12% higher drag coefficient compared to the noncavity case and shifts the minimum NPR required for positive gross propulsive force to higher values.

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Section: Impact Of Cavity On the Aerodynamic Performancementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Propulsion Aerodynamics for a Novel High-Speed Exhaust System

Tsentis,

Goulos,

Prince

et al. 2023

Journal of Engineering for Gas Turbines and Power

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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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“…When it reaches the inlet of the turbine, the enthalpy must be sufficient so that the turbine can produce enough shaft power for the compressor and fuel pump. In the case the heat exchangers cannot heat up fuel flow or/and the flow cannot be expanded through the turbine stages, the thrust will decrease immediately [4,5]. This means that there is a trade-off between the regenerator and turbine complexity.…”

Section: Introductionmentioning

confidence: 99%

Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory

2019

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Hypersonic civil aviation is an important enabler for extremely shorter flight durations for long-haul routes and using unexploited flight altitudes. Combined cycle engine concepts providing extended flight capabilities, i.e. propelling the aircraft from take-off to hypersonic speeds, are proposed to achieve high-speed civil air transportation. STRATOFLY project is a continuation of former European efforts in hypersonic research and aims at developing a commercial reusablevehicle for cruise speed of Mach 8 at stratospheric altitudes as high as 35 km above ground level. The propulsion plant of STRATOFLY aircraft consists of combination of two different type of engines: an array of air turbo rockets and a dualmode ramjet/scramjet. In the present study, 1D transient thermodynamic simulations for this combined cycle propulsion plant have been conducted between Mach 0 to 8 by utilizing 1D inviscid flow transport relations, numerical tools availablein EcosimPro software platform and the European Space Propulsion System Simulation libraries. The optimized engine parameters are achieved by coupling EcosimPro software with Computer Aided Design Optimization which is a differential evolution algorithm developed at the von Karman Institute.

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Simulation of a Combined Cycle for High Speed Propulsion

Cited by 14 publications

References 2 publications

Propulsion Aerodynamics for a Novel High-Speed Exhaust System

Propulsion Aerodynamics for a Novel High-Speed Exhaust System

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

Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory

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