CFD Computation for Rocket Engine Start-Up Simulation

Boccaletto, Luca; Lequette, Laurent

doi:10.2514/6.2005-4438

Cited by 8 publications

(4 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The total number of grid points is 3,653,299, or 4,421,166 cells for all four cases. The total cell numbers used in this study is higher than the 2,058,192 cells used in the nozzlette configuration [W1], and much higher than the 1,275,120 cells used in the SSME benchmark [9], and the 145,500, 145,500, and 405,900 points used on LE-7, LE-7A, and CTP50-R5-L [10], and the 85,000 cells used on Vulcain 2 [11], respectively. It is noted that although the cross-sectional flow areas of the four thrusters do not have to be the same, they are kept the same such that the results are compared based on the same flow area.…”

Section: Computational Grid Generationmentioning

confidence: 98%

Transient Three-Dimensional Side Load Analysis of Out-of-Round Film Cooled Nozzles

Wang

Lin

Ruf

et al. 2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

Section: Computational Grid Generationmentioning

confidence: 98%

Transient Three-Dimensional Side Load Analysis of Out-of-Round Film Cooled Nozzles

Wang

Lin

Ruf

et al. 2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

“…As a result, grids 3d2 and 3d3 were selected for the transient computations. The total grid points used in these 3-D grids are higher than the 1,286,934 points used for the SSME benchmark [9] and much higher than the 85,000 cells used on Vulcain 2 [11] and the 145,500-405,900 points used for the side-load calculations for the LE-7, LE-7A, and CTP-50-R5-L engines [10].…”

Section: Computational Grid Generationmentioning

confidence: 99%

“…With the advances of computer technology and computational methods, three-dimensional (3-D) timeaccurate CFD methodologies have emerged as a useful tool that can simulate asymmetric shock evolutions and predict the associated peak side loads. For example, Yonezawa et al [10] simulated the startup transient for the LE-7A engine, Boccaletto and Lequette [11] simulated the startup transient for the Vulcain 2 engine, and Wang [9] benchmarked the startup transient for the SSME. Other relevant computational efforts can be found in [3,12,13].…”

mentioning

confidence: 99%

Transient Three-Dimensional Side-Load Analysis of a Film-Cooled Nozzle

Wang

Guidos

2009

Journal of Propulsion and Power

View full text Add to dashboard Cite

Transient three-dimensional numerical investigations on the side load physics for an engine encompassing a film cooled nozzle extension and a regeneratively cooled thrust chamber, were performed. The objectives of this study are to identify the three-dimensional side load physics and to compute the associated aerodynamic side load using an anchored computational methodology. The computational methodology is based on an unstructuredgrid, pressure-based computational fluid dynamics formulation, and a transient inlet history based on an engine system simulation. Ultimately, the computational results will be provided to the nozzle designers for estimating of effect of the peak side load on the nozzle structure.Computations simulating engine startup at ambient pressures corresponding to sea level and three high altitudes were performed. In addition, computations for both engine startup and shutdown transients were also performed for a stub nozzle, operating at sea level. For engine with the full nozzle extension, computational result shows starting up at sea level, the peak side load occurs when the lambda shock steps into the turbine exhaust flow, while the side load caused by the transition from free-shock separation to restricted-shock separation comes at second; and the side loads decreasing rapidly and progressively as the ambient pressure decreases. For the stub nozzle operating at sea level, the computed side loads during both startup and shutdown becomes very small due to the much reduced flow area.

show abstract

“…A large body of experimental 1,3,4,10 and numerical [11][12][13] works have focused on shock-boundary layer interactions in rocket nozzles. Importantly, all existing evidence suggest that under the overexpanded flow conditions producing shocks, crossstream shock structures -typically normal shocks or Mach discs -only exist as single entities, never, for example, in pairs or triples.…”

Section: Introductionmentioning

confidence: 99%

Millisecond-scale shock-train evolution in high-pressure ratio nozzles: Schlieren imaging and qualitative analysis of shock–boundary layer interaction

Keanini

Tkacik

Srivastava

et al. 2013

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The classical picture of shock evolution in nozzles holds that under over-expanded flow conditions, a single, nominally normal shock exists within the nozzle. Focusing on the highly dynamic flow produced during blow-down of an experimental, high-nozzle pressure ratio, planar nozzle, this article presents visual evidence that shock-trains – here, a pair of parallel, nominally normal shocks – dominate the rapidly evolving flow field. Three principal results are presented in this study. First, high-speed schlieren images of the evolving nozzle flow are reported. Second, a simple qualitative model of shock–boundary layer/recirculation zone interaction is proposed and used to explain observed millisecond-scale shock-train structure. Third, limited wall pressure measurements and schlieren images are combined to propose a second qualitative model of shock-train–boundary layer/recirculation zone evolution on the longer blow-down process time-scale. The results provide insight into millisecond-scale compressible flow dynamics within high-nozzle pressure ratios .

show abstract

CFD Computation for Rocket Engine Start-Up Simulation

Cited by 8 publications

References 0 publications

Transient Three-Dimensional Side Load Analysis of Out-of-Round Film Cooled Nozzles

Transient Three-Dimensional Side Load Analysis of Out-of-Round Film Cooled Nozzles

Transient Three-Dimensional Side-Load Analysis of a Film-Cooled Nozzle

Millisecond-scale shock-train evolution in high-pressure ratio nozzles: Schlieren imaging and qualitative analysis of shock–boundary layer interaction

Contact Info

Product

Resources

About