Experimental and Numerical Studies of Secondary Injection in Nozzle
                        Divergence for Thrust Augmentation

Anugrah, G.; Raja, Pramod; Deepu, M.; Sadanandan, Rajesh

doi:10.29252/jafm.12.05.29842

Cited by 7 publications

(5 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The secondary injection causes a rise in wall static pressure, which has a positive association with injection pressure When there is a secondary injection, thrust augmentation occurs. In the current research, it has also been proven to be effective in delaying flow separation toward the outlet [35]. The bell outperforms the linear nozzle by just 3%, despite having a 10% bigger subsonic layer at the nozzle output plane than the 30° linear expander [51].…”

Section: …… (1)mentioning

confidence: 78%

“…Pressure oscillations begin to build up over the nozzle wall during the transition phenomena with modifying the Mach number of the injected secondary flow, which may cause significant quantities of unfavorable side loads. [35] Film cooling theory: The investigation of tangential, supersonic film cooling in a nozzle flow under supersonic conditions The following assumptions are also presumed to be true: In terms of temperature, Mach number, and velocity, the coolant, which is gas, differs significantly from the hot gases. Its composition also differs from that of the nozzle hot gas.…”

Section: Thermal Characteristics Of Bell Nozzle In Supersonic Enginementioning

confidence: 99%

See 1 more Smart Citation

Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine

Guram¹,

Jadhav²,

Sawant³

et al. 2023

jame

View full text Add to dashboard Cite

The nozzle is an important component of the rocket motor system, and a rocket’s overall performance is highly reliant on its aerodynamic design. The nozzle contour can be meticulously shaped to improve performance significantly. The design and shape of rocket nozzles have evolved over the last several decades as a result of extensive research. The nozzle design is composed of two components, an integrated throat, an entry and an exit cone, and a thermal protection system. The Bell Nozzle is designed to provide clearance space for placing the ITE and exit cone, with a cone inflection angle of 16 and a thermal protection system. This paper intends to review and summarize all such developments. Small-scale engine testing allows for the analysis of rocket nozzle materials, but the history of nozzle surface temperature and thermal stress may be adversely affected by side effects. The review focuses primarily on the nozzle shape which has the largest radiative flux past the neck, but the nozzle shape has the highest heat flux in the throat due to the mass-flow rate per unit area. The distribution of nozzle wall pressure is strongly influenced by the Mach number of the injected secondary flow, leading to undesirable side loads. Finally, future development possibilities are suggested.

show abstract

Section: …… (1)mentioning

confidence: 78%

Section: Thermal Characteristics Of Bell Nozzle In Supersonic Enginementioning

confidence: 99%

Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine

Guram¹,

Jadhav²,

Sawant³

et al. 2023

jame

View full text Add to dashboard Cite

show abstract

“…This is owing to the kinetic energy that affects the total energy enhancement released along the nozzle cavity. The flow reaches a supersonic speed after reaching the throat section, causing the kinetic energy to be higher in the divergent section [58]. Hence, it can be concluded that the most significant convergent angle generates the highest total energy.…”

Section: Resultsmentioning

confidence: 98%

Optimizing nozzle convergent angle using central composite design on the particle velocity and acoustic power level for single-hose dry ice blasting nozzle

Mat

Asmuin

Basir

et al. 2020

J Therm Anal Calorim

View full text Add to dashboard Cite

One of the important parameters in developing dry ice blasting nozzle is the high-speed dry ice pellets. However, many studies focus primarily only on its performance without considering the noise emission that comes from an operating nozzle. In this method, the central composite optimization tool has been used. The two-way mass momentum and energy exchange are successfully modeled using the two-way mass momentum model. As an attempt to theoretically verify the model accuracy, a comparison is conducted on the density, pressure, temperature, as well as Mach number ratios corresponding to various ratios of nozzle area. In return, the smallest value of the convergent angle results in the highest velocity of 516.75 m s −1 , as well as the highest level of the acoustic power level of 144.36 dB. Besides, one of the vital influencing factors on the emitted acoustic power level is the turbulence intensity, which can achieve a maximum of 1% intensity for an angle of 20° at the throat section. Besides, the same negative sensitivity of around − 0.99% is provided by the velocity and acoustic power level, which is highly responsive toward the convergent angle variation. Furthermore, the optimum nozzle convergent angle for the minimization of the acoustic power level and maximization of the velocity is 7.03°. The novelty of this research lies in the findings on the effective convergent angle of the dry ice blasting nozzle that accelerates the particle flow and minimizes the noise emission from the operating nozzle.

show abstract

“…A rise in static pressure by the wall of the nozzle because of secondary fuel injection, showing compatibility with fuel injection pressure. It can be seen for sufficient chamber pressure, secondary injection system causes thrust augmentation [3]. Ankit et.al reviewed about pintle injector mentioning about spray patterns and the effect of thrust based on total momentum ratio as well as length to duct ratio.…”

Section: Icdmme-2021mentioning

confidence: 99%

Analysis and optimization of Dual secondary fuel injector for Thrust vector control

Sharma¹,

Manohar

Mishra³

2022

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

The motive of this analysis is to compare the performance parameters of a single secondary fuel injector and performance of Dual Secondary fuel injector system for Thrust Vector Control (SITVC) in a supersonic nozzle for different distances between the two ports. With the help of Computational Fluid Dynamics (CFD) the performance characteristics of SITVC has been analyzed. Experimental and numerical investigations have been done with various circumstances to examine the performance augmentations of the 2-D nozzle.

show abstract

Experimental and Numerical Studies of Secondary Injection in Nozzle Divergence for Thrust Augmentation

Cited by 7 publications

References 19 publications

Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine

Review Study on Thermal Characteristics of Bell Nozzle used in Supersonic Engine

Optimizing nozzle convergent angle using central composite design on the particle velocity and acoustic power level for single-hose dry ice blasting nozzle

Analysis and optimization of Dual secondary fuel injector for Thrust vector control

Contact Info

Product

Resources

About