The TICTOP nozzle: a new nozzle contouring concept

Frey, Manuel; Makowka, Konrad; Aichner, T.

doi:10.1007/s12567-016-0139-z

Cited by 11 publications

(4 citation statements)

References 3 publications

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“…To understand what actually happens in TOC nozzles, several experimental studies, carried out on optimized nozzles with subscale (Nave and Coffey (1973), Nguyen et al (2003), Hadjadj et al (2015) and Ijaz Rajesh ( 2019)) or full-scale (Nave and Coffey (1973)), confirmed by various numerical simulations (Frey and Hagemann (1998), Aghababaie and Theunissen (2015), Maicke et al (2013)) and experiments (Frey et al (2017), Meng and Ye (2017), Changsoo et al (2020), Martelli et al (2020), Ruyan et al (2016)), and Stark Genin (2016), have an FSS separation kind, the flow boundary layer separated from the nozzle wall and is not reattached (see Fig. 3a), while a restricted shock separation is marked by closed recirculation bubbles that are re-attached to the wall nozzle behind the point of separation (see Fig.…”

Section: Findings and Discussionmentioning

confidence: 99%

“…Nasuti and Onofri (1996) demonstrated by numerical simulations the effect of the vortex in deflecting the central flow towards the walls. An analytical model for the cap shock structure associated with the RSS phase and for FSS-RSS transition prediction was provided by Frey et al (2017). Reverse flow in TOC nozzle plume has latterly been experimentally demonstrated (Wang et al (2013), Stark and Génin (2016), Steger and Warming (1979)).…”

Section: Introductionmentioning

confidence: 99%

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Numerical Investigation of Supersonic Flow Separation in Thrust-Optimized Contour Rocket Nozzle

Bensayah¹,

Khadidja²

2022

JSSCM

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The difficulties associated with thrust-optimized contour nozzles have led to significant advances in our knowledge of the physical phenomena associated with flow separation. In this study, a fully implicit scheme is implemented using a combined weight function for splitting the flux to analyze the shock patterns in the optimized contour (TOC) that occur during the process of separation, leading to free (FSS) or restricted (RSS) shock separation. The switching FSS/RSS hysteresis at startup and shutdown is also investigated. To better understand and validate the findings and study the properties of the oscillating flow during the start-up procedure, an axisymmetric two-dimensional numerical simulation was performed for the TOC nozzle. A code was developed to solve the unsteady Navier-Stokes equations for compressible nozzle flow with boundary layer/shock wave interactions with the implementation of a full RSM-Omega turbulence model. These findings were used to analyze the separation structures, shock wave interactions, and hysteresis phenomena.

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Section: Findings and Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Supersonic Flow Separation in Thrust-Optimized Contour Rocket Nozzle

Bensayah¹,

Khadidja²

2022

JSSCM

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“…where: K -factor [dm 3 /(min·bar 0,5 )] Q -flow nozzle [dm 3 /min] p -nozzle supply pressure [bar] Three types of nozzles were tested: spiral nozzle TF 6, impact nozzle P 54, swirl axis nozzle with tangent inlet holes in the disc CW-50 F (Fig.2). In the TF 6 nozzle, water flows down the spiral part under pressure and is centrifugally thrown away [50][51][52][53]. In the P 54 jet nozzle water is disrupted by a deflector.…”

Section: (2)mentioning

confidence: 99%

The impact of fog nozzle type on the distribution of mass spray density

2018

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This study was undertaken to analyze the influence of nozzle type on a mass spray density. The results indicated that the most uniform droplet distribution and spraying area was observed for the impact nozzle P 54. The highest mass spray density and the lowest spraying were noticed for the spiral nozzle TF 6. The high values of mass spray density for TF 6 nozzle were associated with the high K-factor value and the low spray angle. The results also showed that the construction of spiral nozzles influence the stream structure. The value of average mass spray density was twice as low for CW-50 F nozzle compared to TF 6. Material and MethodsThe experiments were performer on a dedicated set-up, composed of a cubic chamber with a nozzle localized in the middle, upper part (Fig.1).

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“…To expand a flow to match near vacuum conditions, one would need a near infinite nozzle [6]. The length of an ideal nozzle can be decreased by permitting all the expansion to occur just at the throat (amid a sharp corner) and then constructing the nozzle contour to turn the flow such that it can attain an axial uniform flow at the exit [7]. This nozzle is referred to as a minimum-length nozzle.…”

Section: Introductionmentioning

confidence: 99%

A shape design optimization methodology based on the method of characteristics for rocket nozzles

2023

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Even though shape optimization is a powerful tool for designing aerospace vehicles, it can be time-consuming when high-fidelity models are employed. Thus, lower-fidelity simulations covering a wider design space can be a solution for shape optimization in the early design phases. With this in mind, the present work aims to develop a low-fidelity and fast method to conduct nozzle shape optimization. This method consists in using the free-form deformation (FFD) parameterization technique to control the nozzle shape by means of an optimization algorithm to maximize the coefficient of thrust determined by a two-dimensional method of characteristics (MoC). To verify the reliability of the proposed method, a similar optimization process is carried out, recurring to high-fidelity simulations, namely using an Euler solver, in the open-source framework $$\text {SU}^2$$ SU 2 . This latter optimization process is established as a surrogate-based optimization (SBO) not only to mitigate the $$\text {SU}^2$$ SU 2 framework limitations in performing shape optimization on nozzles, but also as a way to reduce the computational power. A good agreement between the results from both methods is achieved, displaying solely a small offset concerning the optimal contour width and the coefficient of thrust. Hence, this proves the usefulness of the developed shape optimization strategy based on the MoC for the preliminary design of nozzles.

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The TICTOP nozzle: a new nozzle contouring concept

Cited by 11 publications

References 3 publications

Numerical Investigation of Supersonic Flow Separation in Thrust-Optimized Contour Rocket Nozzle

Numerical Investigation of Supersonic Flow Separation in Thrust-Optimized Contour Rocket Nozzle

The impact of fog nozzle type on the distribution of mass spray density

A shape design optimization methodology based on the method of characteristics for rocket nozzles

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