scholarly journals Numerical study on a new design of solid-fuel ramjet combustor with swirl flow

2019 ◽  
Vol 8 (2) ◽  
pp. 72-79
Author(s):  
Omer Musa ◽  
Chen Xiong ◽  
Guoping Huang
Keyword(s):  
Heat Transfer ◽  
Parallel Computing ◽  
Fluid Mechanics ◽  
Chemical Kinetics ◽  
Solid Fuel ◽  
Numerical Study ◽  
Swirl Flow ◽  
Ramjet Combustor ◽  
Afterburning Chamber ◽  
Transfer Thermodynamics

A new design of solid-fuel ramjet is proposed and examined numerically in this paper. Multi-physics coupling code is developed using FORTRAN and parallel computing to solve the problems of multi-physics coupling of fluid mechanics, solid pyrolysis, heat transfer, thermodynamics, and chemical kinetics. Simulations are carried out for the proposed design then the results are compared with the classic design of the solid-fuel ramjet. It is found that the proposed design has improved the regression rate significantly; besides, the amount of released solid fuel is increased for the same size. A new flame has been observed inside the combustion chamber of the proposed design then the two flamed were emerged in the afterburning chamber.

scholarly journals Numerical Investigation of the Effect of Sudden Expansion Ratio of Solid Fuel Ramjet Combustor with Swirling Turbulent Reacting Flow

Energies ◽  
2019 ◽  
Vol 12 (9) ◽  
pp. 1784 ◽  
Author(s):  
Weixuan Li ◽  
Xiong Chen ◽  
Wenxiang Cai ◽  
Omer Musa
Keyword(s):  
Heat Transfer ◽  
Solid Fuel ◽  
Expansion Ratio ◽  
Swirl Flow ◽  
The Self ◽  
Sudden Expansion ◽  
Reacting Flow ◽  
Reattachment Point ◽  
Regression Rate ◽  
Ramjet Combustor

In this paper, the effect of sudden expansion ratio of solid fuel ramjet (SFRJ) combustor is numerically investigated with swirl flow. A computational fluid dynamics (CFD) code is written in FORTRAN to simulate the combustion and flow patterns in the combustion chamber. The connected-pipe facility is used to perform the experiment with swirl, and high-density Polyethylene (HDPE) is used as the solid fuel. The investigation is performed with different sudden expansion ratios, in which the port and inlet diameters are independently varied. The results indicated that the self-sustained combustion of the SFRJ occurs around the reattachment point at first, and then the heat released in reattachment point is used to achieve the self-sustained combustion in the redevelopment zone. The average regression rate is proportional to the sudden expansion ratio for the cases with a fixed port diameter, which is mainly dominated by the enhancement of heat transfer in backward-facing step. However, the average regression rate is inversely proportional to the sudden expansion ratio for the cases with fixed inlet diameter, which is influenced by the heat transfer mechanism of developed turbulent flow in the redevelopment zone.

Heat transfer in a solid fuel ramjet combustor

1990 ◽  
Author(s):  
F. VINNEMEIER ◽  
J. DE WILDE
Keyword(s):  
Heat Transfer ◽  
Solid Fuel ◽  
Ramjet Combustor

scholarly journals Numerical study of heat transfer and chemical kinetics of solar thermochemical reactor for hydrogen production

2018 ◽  
Author(s):  
Achmad Rofi Irsyad ◽  
Byunggi Kim ◽  
Doan Hong Duc ◽  
Saiful Hasmady bin Abu Hassan ◽  
Kazuyoshi Fushinobu
Keyword(s):  
Heat Transfer ◽  
Hydrogen Production ◽  
Chemical Kinetics ◽  
Numerical Study ◽  
Solar Thermochemical ◽  
Kinetics Of

The Effect of Radiation on Turbulent Convective Heat Transfer Over an Ablating Solid

2000 ◽  
Author(s):  
K. M. Akyuzlu ◽  
A. Antoniou ◽  
R. Kagoo
Keyword(s):  
Heat Transfer ◽  
Convective Heat Transfer ◽  
Convective Heat ◽  
Solid Fuel ◽  
Gas Flow ◽  
Numerical Study ◽  
Flame Temperature ◽  
Linearization Method ◽  
Algebraic Equations ◽  
Operational Parameters

Abstract A numerical study is conducted to investigate the effect of thermal radiation on turbulent flow (upstream of the flame front) inside a subscale planar hybrid rocket motor. The physical model adopted for the study is based on an unsteady two-domain (solid fuel and gaseous oxidizer) concept where both domains are assumed to be two-dimensional. Furthermore, the oxidizer gas flow is assumed to be incompressible and turbulent with boundary layer approximations. The radiative heat transfer is incorporated to the energy equation for the oxidizer using the Rosseland diffusion approximation. Fuel is assumed to be a nontransparent isotropic solid. The two domains are coupled through an energy balance at the interface that includes heat transfer due to radiation, conduction, and ablation. The solution to the governing differential equations of the present model is obtained by first linearizing the equations using Newton linearization method, discretizing them by a fully implicit finite-difference technique, and then solving the resulting set of algebraic equations by a block tridiagonal matrix solver. Finally, the proposed mathematical model is used in a parametric study to determine the effect of various operational parameters, such as flame temperature and oxidizer mass flow rate, on heat transfer from the solid fuel. Results indicate the significance of radiation on turbulent convective heat transfer over an ablating solid.

Study of Flow and Convective Heat Transfer in a Simulated Scaled Up Low Emission Annular Combustor

2010 ◽  
Author(s):  
Teddy Sedalor ◽  
Sunil Patil ◽  
Srinath Ekkad ◽  
Danesh Tafti ◽  
Yong Kim ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Convective Heat Transfer ◽  
Convective Heat ◽  
Swirling Flow ◽  
Numerical Study ◽  
Infrared Camera ◽  
Swirl Flow ◽  
Annular Combustor ◽  
Fuel Nozzle ◽  
Different Characteristics

Modern Dry Low Emissions (DLE) combustors are characterized by highly swirling and expanding flows that makes the convective heat load on the gas side difficult to predict and estimate. A coupled experimental-numerical study of swirling flow inside a DLE annular combustor model is presented. A simulated scaled up annular combustor shell was designed with a generic fuel nozzle model to create the swirl in the flow. The experiment was simulated with a cold flow and heated combustor walls in a low speed wind tunnel. An infrared camera was used to obtain the temperature distribution along the liner wall. The experiment was conducted at various Reynolds numbers to investigate the effect on the convective heat transfer peak locations. A CFD study performed using FLUENT was used to get a better understanding of high swirl flow field and its effect on the heat transfer on liner walls. Results show that the heat transfer distributions in the annulus have slightly different characteristics for the concave and convex walls. Results also show a much slower drop in heat transfer coefficient enhancement with increasing Reynolds number compared to can combustor liner walls.

scholarly journals Analysis of temperature distribution in the heating boiler equipped with afterburning chamber

2019 ◽  
Vol 128 ◽  
pp. 01009
Author(s):  
Wojciech Judt ◽  
Bartosz Ciupek ◽  
Rafał Urbaniak
Keyword(s):  
Heat Transfer ◽  
Heat Exchanger ◽  
Temperature Distribution ◽  
Transfer Process ◽  
Solid Fuel ◽  
Heat Transfer Process ◽  
Heating Device ◽  
Afterburning Chamber ◽  
Vertical Tubes ◽  
Heating Boiler

Analysis of a heat transfer process for construction of solid fuel heating boiler equipped with additional afterburning chamber is presented. Analyzed construction of the heating device is intended for shouse heating and preparation of hot utility water. A heat exchanger in the analyzed boiler is composed of vertical tubes divided into three boiler draughts. Afterburning chamber connects main combusting chamber of the heating boiler with second and third boiler draught. The aim of this analysis is to identify the character of heat transfer through the heating boiler

scholarly journals Numerical Investigation of Inlet Thermodynamic Conditions on Solid Fuel Ramjet Performances

2021 ◽  
Vol 2021 ◽  
pp. 1-20
Author(s):  
Weixuan Li ◽  
Dan Zhao ◽  
Xiong Chen ◽  
Liang Zhu ◽  
Siliang Ni
Keyword(s):  
Heat Transfer ◽  
Chemical Reaction ◽  
Solid Fuel ◽  
Swirl Flow ◽  
Navier Stokes ◽  
Inlet Temperature ◽  
Combustion Heat ◽  
Flow Recirculation ◽  
Flow Field Characteristics ◽  
Inlet Conditions

In this work, 2D numerical RANS (Reynolds Average Navier-Stokes) simulations were carried out to investigate the thermodynamic performance of a solid fuel ramjet (SFRJ) with different inlet conditions. This is achieved by using an in-house FORTRAN code to simulate a 2D turbulent, reacting, unsteady flow in the ramjet engine. The inlet conditions are characterized by three key parameters: (1) swirl number ( S N ), (2) mass flow rate ( m ̇ air ), and (3) inlet temperature ( T in ). With the code numerically validated by benchmarking with a number of computed cases, it is applied to perform systematic studies on the turbulent flow recirculation, combustion, and heat transfer characteristics. It is found that increasing S N , m ̇ air , or T in can dramatically enhance the combustion heat release rate, regression rate, and combustor average temperature. Furthermore, the analysis on the chemical reaction intermediate (CO) reveals that the chemical reaction is more sufficient with increased m ̇ air , but S N = 0 . In addition, a secondary vortex is generated at the corner of the backward facing step in the presence of a swirl flow resulting from the instability of the shear layer. Finally, the nonlinear correlations between the heat transfer, combustion characteristics, and flow field characteristics and the corresponding inlet thermodynamic parameters are identified.

Sign in / Sign up

Export Citation Format

Share Document