Computational study on flow through truncated conical plug nozzle with base bleed

Nair, Prasanth P.; Suryan, Abhilash; Kim, Heuy Dong

doi:10.1016/j.jppr.2019.02.001

Cited by 37 publications

(12 citation statements)

References 29 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In 2019, Suryan et al did a two-dimensional axisymmetric numerical analysis on flow through truncated conical plug nozzles with the introduction of a base bleed. They found that the introduction of the base bleed compensates for the loss of thrust due to the truncation of the conical supersonic plug nozzle [22]. In 2020, numerical simulations on an annular nozzle fed by a toroidal combustion chamber were carried out by Ferlauto et al [23], in order to understand what are the main phenomena that affect the interaction between the primary flow and the injection of secondary flow on the truncated plug.…”

Section: The Literature Reviewmentioning

confidence: 99%

Design and Numerical Analysis of a Plug Nozzle

HAIF¹,

Kbab²,

Bnekhedda³

2022

AiMT

View full text Add to dashboard Cite

The purpose of this study is to simulate the flow in the plug nozzle. Further, the evolution of the parameters of this flow was studied. The mass of the nozzle and of the exhaust gases was calculated by the simulation. In addition, all these results are then compared with those obtained by the numerical calculations. In the second part of the study, the method of an approximate method was used to generate the profile of the plug nozzle for different values of heat capacity ratio γ and the number of exit Mach. Finally, our results are com-pared with those obtained numerically and experimentally (available in open literature).

show abstract

Section: The Literature Reviewmentioning

confidence: 99%

Design and Numerical Analysis of a Plug Nozzle

HAIF¹,

Kbab²,

Bnekhedda³

2022

AiMT

View full text Add to dashboard Cite

show abstract

“…Table 3 presents Since both dual-stream jets were at sonic conditions (M = 1), weak shock waves were observed near the exhaust sections and edges (Figure 9(b)); similar behavior was reported at nozzle-exit flows. 55,56 A flow separation on the central plug can be seen in the core flow due to the over-expansion shock. The velocity contours in Figure 9(a) show that the potential core length was about 5D b ; this distance is comparable to both experimental (5.4D b ) 52 and numerical (5D b ) 57 values.…”

Section: Contrail Formation In the Cfm56-3 Exhaust Jetmentioning

confidence: 99%

Eulerian–Lagrangian CFD-microphysics modeling of a near-field contrail from a realistic turbofan

Cantin

Chouak

Morency

et al. 2021

International Journal of Engine Research

View full text Add to dashboard Cite

Aircraft contrails contribute to climate change through global radiative forcing. As part of the general effort aimed at developing reliable decision-making tools, this paper demonstrates the feasibility of implementing a Lagrangian ice microphysical module in a commercial CFD code to characterize the early development of near-field contrails. While engine jets are highly parameterized in most existing models in a way that neglects the nozzle exit-related aspects, our model accounts for the geometric complexity of modern turbofan exhausts. The modeling strategy is based on three-dimensional URANS simulations of an aircraft nozzle exit involving a bypass and a core jet (Eulerian gas phase). Solid soot and ice particles (dispersed phase) are individually tracked using a Lagrangian approach. The implemented microphysical module accounts for the main process of water-vapor condensation on pre-activated soot particles known as heterogeneous condensation. The predictive capabilities of the proposed model are demonstrated through a comprehensive validation set based on the jet-flow dynamics and turbulence statistics in the case of compressible, turbulent coaxial jets. Simulations of contrail formation from a realistic nozzle-exit geometry of the CFM56-3 engine (short-cowl nozzle delivering a dual stream jet with a bypass rate of 5.3) were also carried out in typical cruise flight conditions ensuring contrail formation. The model provides reliable predictions in terms of the plume dilution and ice-particle properties as compared to available in-flight and numerical data. Such a model can then be used to characterize the impact of nozzle-exit parameters on the optical and microphysical properties of near-field contrails.

show abstract

“…The baseline solver was selected as double-precision coupled solver in order to obtain a fast converging and accurate solution for high-speed flows. 32,34,35 Leastsquares cell-based spatial discretization in which the solution was assumed to vary linearly was used. The second-order upwind interpolation scheme was used to solve convective terms.…”

Section: Flow Solvermentioning

confidence: 99%

“…The total pressure loss at the exit of the combustor in the decreasing order are 30 × 10, 15 × 10, 25 × 10, 20 × 10, 10 × 10, 5 × 10, and single strut; the corresponding values in percentage are 47. 35…”

Section: Performance Characteristics Of Reacting Flow With Injectiomentioning

confidence: 99%

Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

et al. 2020

Self Cite

View full text Add to dashboard Cite

Supersonic combustion ramjet (scramjet) is a variant of ramjet in which the combustion takes place at supersonic velocity. The flow physics inside the scramjet combustor is quite complex due to the fact that the mixing and completion of the combustion take place in a short time, which is of the order of milliseconds. This study focuses on flow characteristics within the combustion chamber of the scramjet engine that is designed to improve energy efficiency by enhancing combustion efficiency. The effect on combustion performance and thereby the energy efficiency on using strut-based flame stabilizer is evaluated at different positions. Reynolds averaged Navier-Stokes equations are solved with the Shear Stress Transport k-ω turbulence model. Single strut configuration is used to validate with the experimental data. Single strut is then compared with three-strut configuration. In the three-strut configuration, the location of the primary strut is kept constant, and the secondary struts are relocated in x and y directions. Combustion performance was evaluated for the cases of flow from primary strut only and through three struts. It was found that the placement of secondary strut in a three-strut configuration plays a vital role in improving energy efficiency. A maximum of 33.86% improvement in combustion efficiency was observed in comparison to the single strut combustor. A reduction in unburned fuel was observed, making the system more energy efficient. If the struts are not placed optimally, the combustion performance of the combustor was observed to be lower than that of a single-strut configuration. The shock reflection and expansion fans within the primary combustion zone and the secondary strut region enhance the combustion efficiency. The wall static pressure was observed to increase with the addition of secondary struts. For certain strut configurations, flow separation was seen on the combustor walls. If the secondary strut was placed close to the primary strut, combustion efficiency was found to enhance. It was seen that

show abstract

Computational study on flow through truncated conical plug nozzle with base bleed

Cited by 37 publications

References 29 publications

Design and Numerical Analysis of a Plug Nozzle

Design and Numerical Analysis of a Plug Nozzle

Eulerian–Lagrangian CFD-microphysics modeling of a near-field contrail from a realistic turbofan

Investigation of flow characteristics in supersonic combustion ramjet combustor toward improvement of combustion efficiency

Contact Info

Product

Resources

About