Dual-Bell Nozzle Design

Génin, Chloe; Schneider, Dirk; Stark, Ralf

doi:10.1007/978-3-030-53847-7_25

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

2020

DOI: 10.1007/978-3-030-53847-7_25

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Dual-Bell Nozzle Design

Chloe Génin

Dirk Schneider

Ralf Stark

Abstract: The dual-bell nozzle is an altitude adaptive nozzle concept that offers two operation modes. In the framework of the German Research Foundation Special Research Field SFB TRR40, the last twelve years have been dedicated to study the dual-bell nozzle characteristics, both experimentally and numerically. The obtained understanding on nozzle contour and inflection design, transition behavior and transition prediction enabled various follow-ups like a wind tunnel study on the dual-bell wake flow, a shock generator… Show more

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Cited by 4 publications

References 15 publications

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Effect of the length of truncated nozzle with a tip on its thrust characteristics

Ternova¹

2022

Teh. Meh.

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Nowadays, for solving new problems, rocket engine nozzle developers are increasingly turning to non- traditional nozzle configurations that differ from the classic Laval one. A relatively new line in the design of supersonic nozzles is the development of the so-called bell-shaped nozzle, which, unlike the classical Laval nozzle, has a larger angle of entry into the supersonic part of the nozzle. In this case, dual bell nozzles, which have two flow expansion sections in their supersonic part, are considered. However, the effect of the length ratio of the two flow expansion sections of a truncated nozzle on its characteristics has not yet been studied. The goal of this work is to determine the effect of the length of the upstream conical supersonic section on the static pressure distribution in the nozzle and its thrust characteristics with the shape of the bell-shaped tip kept unchanged. The nozzle characteristics were studied using the ANSYS Fluent computing package. It was shown that the flow patterns in the nozzle (velocity fields) change with the length of the conical part upstream of the tip and the underexpansion degree. Under terrestrial conditions (Pн = 1 bar), all variants show a developed separation zone that starts from the corner point where the tip is connected to the conical part. In this case, the pressure on the nozzle wall is nearly equal to the ambient pressure. At a large flow underexpansion degree (P0 = 300 bar) and in low-pressure conditions conditions (Pн =0.1 bar), the flow in the tip is adjacent to the wall. At a large flow underexpansion degree, the pressure in the nozzle increases from the corner point to the tip exit, and the pressure at the tip exit increases with decreasing tip length. The nozzle thrust coefficient decreases with increasing flow underexpansion degree, and it reaches a constant value after the flow becomes adjacent to the tip wall downstream of the corner point where the tip is connected to the nozzle. At high flow underexpansion degrees, the nozzle thrust coefficient is higher for a nozzle with a longer conical part. The calculated results are in good agreement with experimental data on nozzles of this type.

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Effect of the length of truncated nozzle with a tip on its thrust characteristics

Ternova¹

2022

Teh. Meh.

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The Influence of the Angle of Entry Into the Bell-Shaped Tip of a Shortened Round Supersonic Nozzle of a Rocket Engine on Its Impulse Characteristics

Prуadko,

Strelnikov,

Ternova

2024

Kosm. nauka tehnol.

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In gas-dynamic studies of rocket engines, much attention is paid to the characteristics of the nozzle — its geometry, momentum, losses, and manifestation of traction characteristics under various operating conditions. This work is devoted to the study of the influence of the entry conditions into the bell-shaped tip of a shortened nozzle on its gas-dynamic and impulse characteristics. We consider shortened nozzles with the same conical supersonic parts and the same total length of the nozzle but with different angles of connection of the conical part of the nozzle with the bell-shaped tip. When working at sea level, changing the angle of inclination of the forming bell-shaped tip does not significantly change the value of the static pressure at the corner point and the coefficient of nozzle impulse. This is due to the occurrence of flow separation at the corner point and the presence of a large-scale vortex. With a continuous flow in the nozzle during the operation of the rocket engine at altitude, the nature of the pressure distribution on the nozzle wall at the corner point differs when the angle of connection of the conical part with the tip changes, and the maximum value at the nozzle section is approximately the same. This fact is explained by the appearance of a hanging shock wave near the tip wall at small entrance angles (30°). The study examines the flow’s impulse characteristics in the nozzle under different pressure values at the inlet and the surrounding environment. The impulse coefficient in terrestrial conditions depends little on changing the tip and decreases with increasing pressure at the nozzle inlet. When working at height, there is a weak effect of changing the angle of entry into the nozzles on the momentum coefficient.

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Conceptual Design and Study of Flow Through a Dual Bell Nozzle at Different Altitudes Using Computational Fluid Dynamics

JITHENDRA¹,

RAM²,

SASHENDRA³

et al. 2021

JME

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Dual-Bell Nozzle Design

Cited by 4 publications

References 15 publications

Effect of the length of truncated nozzle with a tip on its thrust characteristics

Effect of the length of truncated nozzle with a tip on its thrust characteristics

The Influence of the Angle of Entry Into the Bell-Shaped Tip of a Shortened Round Supersonic Nozzle of a Rocket Engine on Its Impulse Characteristics

Conceptual Design and Study of Flow Through a Dual Bell Nozzle at Different Altitudes Using Computational Fluid Dynamics

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