Installed performance evaluation of an air turbo-rocket expander engine

Fernandez-Villace, Victor; Paniagua, Guillermo; Steelant, Johan

doi:10.1016/j.ast.2014.03.005

Cited by 41 publications

(16 citation statements)

References 12 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…10) indicates the best agreement is obtained with the compressible Spalart-Allmaras turbulence model used within SPARK (turb SA0 in table. Forsythe, Hoffmann and Squires [5]). All ESTEC nose-to-tail simulations have been performed by using the original version of the SpalartAllmaras turbulence model.…”

Section: Nose-to-tail Simulationsmentioning

confidence: 94%

“…In particular, for the present simulations Jachimowski air-hydrogen combustion chemical schemes have been used including the Zel'dovich mechanisms for NO x formation (Jachimowski [11]). Several turbulence models are available inside the SPARK code for eddy viscosity calculation: the one-equation Spalart-Allmaras model both in incompressible (SA, Spalart and Allmaras [16]) and compressible (SA0, Forsythe et al [5]) version, and the two-equation k-ε turbulence model. For all the models the laminar-to-turbulence transition can be imposed across surface lines (i.e.…”

Section: Numerical Modelingmentioning

confidence: 99%

“…After take-off, a subsonic cruise up to 400 km shall enable to reach the coast, after which the airplane is allowed to accelerate to supersonic speeds overseas, hence avoiding sonic boom impact overland. This is performed by means of air-turborocket (ATR) engines operating up to a Mach number of about 4.5 after which the cycle is then switched to the Dual-Mode Ramjet/Scramjet engine [4]. The cruise conditions are reached at about 50 min after take-off.…”

Section: Vehicle and Mission Descriptionmentioning

confidence: 99%

“…A combination of different propulsion systems is employed for the acceleration phase of the mission, including turbojet engines based on an air-turborocket cycle (ATR) for Mach below 4.5 [14,15,4].…”

Section: Vehicle and Mission Descriptionmentioning

confidence: 99%

See 3 more Smart Citations

Numerical simulations and performance assessment of a scramjet powered cruise vehicle at Mach 8

Roncioni

Natale

Marini

et al. 2015

Aerospace Science and Technology

View full text Add to dashboard Cite

Section: Nose-to-tail Simulationsmentioning

confidence: 94%

Section: Numerical Modelingmentioning

confidence: 99%

Section: Vehicle and Mission Descriptionmentioning

confidence: 99%

Section: Vehicle and Mission Descriptionmentioning

confidence: 99%

See 2 more Smart Citations

Numerical simulations and performance assessment of a scramjet powered cruise vehicle at Mach 8

Roncioni

Natale

Marini

et al. 2015

Aerospace Science and Technology

View full text Add to dashboard Cite

“…The design of innovative turbo-machinery components for compact high-speed flight vehicles required a reduction in the number of stages to save weight, whilst increasing the efficiency of every single component. In this regard, VKI have been examining high pressure ratio single stage fans [39][40] [41], and contra-rotating fans [42][43] [44] for their potential application in the ATR engine [45] [46][47] [48]. The fan geometry provided a pressure ratio of 2.11 with an efficiency of 89%.…”

Section: Gtow [Ton] 400mentioning

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

View full text Add to dashboard Cite

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

show abstract

Reduced Order Computational Methods for the Development of Propulsive Technologies for Supersonic Aviation to Achieve Climate Neutrality

Van den Borre,

Ispir,

Cakir

et al. 2024

Advanced Computational Methods and Design for Greener Aviation

View full text Add to dashboard Cite

Installed performance evaluation of an air turbo-rocket expander engine

Cited by 41 publications

References 12 publications

Numerical simulations and performance assessment of a scramjet powered cruise vehicle at Mach 8

Numerical simulations and performance assessment of a scramjet powered cruise vehicle at Mach 8

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

Reduced Order Computational Methods for the Development of Propulsive Technologies for Supersonic Aviation to Achieve Climate Neutrality

Contact Info

Product

Resources

About