Performance characteristics of a pintle nozzle using the conformal sliding mesh technique

Sung, Hong-Gye; Jeong, Kiyeon; Heo, Junyoung

doi:10.1016/j.ast.2016.11.022

Cited by 14 publications

(5 citation statements)

References 8 publications

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“…In order to save computing resources for the propeller, which has rotational periodicity, a volume that had one third of a cylinder was selected as the computational domain, as shown in Figure 4. The computational domain is composed of an inner rotating domain and an outer stationary domain [22]. The radius of the stationary domain is 5D, where D is the nominal diameter of the propeller.…”

Section: Meshing and Boundary Conditionsmentioning

confidence: 99%

Performance of a Propeller Coated with Hydrophobic Material

Pan

Zeng

Tian

et al. 2022

JMSE

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Computational and experimental methods were used to study a propeller coated with hydrophobic material and a propeller with a conventional surface for comparison. In CFD simulations, the blade surface mesh was arranged in a way to set non-slip or free slip wall boundary conditions with different proportions to define the level of surface slip. The conventional and the hydrophobic material propellers defined by different surface slip rates were simulated under different advance speed coefficients and different rotational speeds. Propeller performance results, blade pressure, and the Liutex vorticity distribution were studied. An experimental platform was established to study the velocity field around the propeller using a Particle Image Velocimetry (PIV) device. The CFD calculation results were compared with the PIV results. It was found that the calculation results using a 75% surface slip rate were closer to the experimental results. The calculation results show that the propeller coated with hydrophobic material has improved thrust and efficiency compared with the propeller with conventional material. The hydrophobic material can significantly reduce the low-speed region downstream of the propeller hub. The hub and the tip vortices shown by the Liutex are also significantly reduced. Those changes help to improve the propulsion efficiency.

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Section: Meshing and Boundary Conditionsmentioning

confidence: 99%

Performance of a Propeller Coated with Hydrophobic Material

Pan

Zeng

Tian

et al. 2022

JMSE

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“…From 2013 to 2017, H.-G. Sung [6,7] conducted a transient numerical simulation study on reciprocating the pintle using dynamics mesh, and obtained certain results on the pressure and thrust and their sensitivity. Song [8] used RNG k-ε to verify the results of the cold flow experiment and showed that the burning rate response characteristics of solid propellant have an important impact on the operation of the pintle.…”

Section: Introductionmentioning

confidence: 99%

“…The pintle itself in the motor, however, will cause a complex wave structure, flow separation, and vortex backflow [6,7], while the solid propellent has the pressure-burning rate response characteristic, which makes the pintle motor have a typical unstable characteristic during operation. The secondary flow not only makes the transient characteristics of the flow field in the motor more complicated, but also interferes with the strong unsteady characteristics of the flow field during the opening and closing of the secondary flow [14].…”

Section: Introductionmentioning

confidence: 99%

Transient Characteristics of Fluidic Pintle Nozzle in a Solid Rocket Motor

Yan,

Zhao,

Song

et al. 2024

Aerospace

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The fluidic pintle nozzle, a new method to control the thrust of a solid rocket motor, has been proposed in recent years by combining the pintle with the aerodynamic throat (fluidic throat). The study of static characteristics has proved that it has a remarkable effect on thrust control. To study the transient characteristics of the fluidic pintle nozzle, 2D transient simulations of a fluidic pintle nozzle propulsion system were conducted, employing dynamic meshing techniques. The Reynolds-averaged Navier–Stokes equations were meticulously solved, implementing a k–ω SST turbulence model. The thrust control principle of the fluid pintle nozzle was studied, and the wave structure was summarized. The transient characteristics of the secondary flow opening, secondary flow closing, pintle moving forward (pressure rise), and pintle moving backward (pressure drop) were obtained, and the effects of the injection angle and injection port position were studied. The response process after injection can be roughly divided into three stages: pressure propagation, pressure oscillation, and equilibrium stability, with time distributions of 0.4%, 5.39%, and 94.21%, respectively. In the process of the pintle moving forward, the rate of combustion chamber pressure increases and thrust decreases gradually because of the arc wall of the nozzle throat upstream, and the process of throats moving backward is just the opposite. Compared with the condition with a maximum throat opening and no secondary flow, the thrust of the condition with a minimum throat opening and a 0.3-flow-ratio secondary flow is increased by 80.95%. Under conditions of constrained flow ratio, the injection angle of the secondary flow ostensibly exerts negligible influence on the dynamic modulation of thrust. Nevertheless, it remains evident that a reduction in throat opening accentuates the impact of reverse injection. Furthermore, the proximity of the injection port to the head of the pintle is directly proportional to the efficacy of thrust control.

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“…Thrust vectoring can be accomplished using either the mechanical or the fluid systems. A mechanical system such as a moving pintle, used for changing the throat area of a convergent-divergent nozzle, requires a drivemechanism (Sung et al 2017;Lee et al 2013). There are other more effective mechanical mechanisms which include the use of vanes or tubular nozzle extensions (compression deflection) or the use of beveled-exit nozzles (expansion deflection), though these require some change from conventional nozzle designs and increase the manufacturing complexity (Abdullatif and El-Sharkawy 1977).…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigations on the Strut Controlled Thrust Vectoring of a Supersonic Nozzle

Bhale

Kaushik

2020

JAFM

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The attitude control of a rocket engine using the control surfaces becomes cumbersome particularly in larger rockets with high payload. In such cases, a more effective means of producing forces for controlling the flight is the deflection of exhaust gases, referred to as the gas-dynamic steering or the thrust vector control. In this study, the effect of a strut on the exhaust gas deflection, deployed at the locations; 0.62 L, 0.72 L and 0.8 L in the divergent-portion of a Mach 1.84 nozzle at over-expanded, correctly-expanded and under-expanded states of the jet, has been experimentally investigated. The level of expansion at the nozzle exit is varied by changing the settling chamber pressures from 4 bar to 8 bar, in steps of 2 bar. Further, to study the effect of aspect ratio, the height of strut is varied as 1.5 mm, 2.5 mm and 3.5 mm. The strut of height 3.5 mm, deployed at x/L = 0.72, is found to be the most effective thrust vector control at overexpanded conditions; with a maximum jet deflection of about 3.6 o , obtained at a settling chamber pressure of 4 bar. The Schlieren flow visualization images confirm the findings of wall static pressure data.

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Performance characteristics of a pintle nozzle using the conformal sliding mesh technique

Cited by 14 publications

References 8 publications

Performance of a Propeller Coated with Hydrophobic Material

Performance of a Propeller Coated with Hydrophobic Material

Transient Characteristics of Fluidic Pintle Nozzle in a Solid Rocket Motor

Experimental Investigations on the Strut Controlled Thrust Vectoring of a Supersonic Nozzle

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