Mixing and combustion enhancement of Turbocharged Solid Propellant Ramjet

Liu, Shichang; Li, Jiang; Zhu, Gen; Wang, Wei; Liu, Yang

doi:10.1016/j.actaastro.2017.11.017

Cited by 9 publications

(2 citation statements)

References 24 publications

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“…During combustion in the combustion chamber, part of the oxygen of the air flow is used to prevent the aerodynamic structure of the turbine blades from deforming beyond certain limits with temperature [9,10]. Advances in cooling technology, application of thermal protection coatings and super alloy technology have increased the turbine inlet temperature [11,12], but the conditions are still far from the stoichiometric combustion limit of fuels [13,14]. For all these reasons, oxygen-rich air flow continues to exist at the nozzle inlet today.…”

Section: Introductionmentioning

confidence: 99%

Preliminary design and analysis of an afterburner module

Sönmez,

Karabacak,

Ozgoren

2023

International Journal of Aeronautics and Astronautics

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In this study, design calculations and calculations of afterburner used in jet engines are presented by evaluating the results of analytical and computational analysis. Afterburner inlet values of 1050 K temperature, 300 kPa pressure and 3.6 kg/s mass flow rate are taken as the design conditions. Maximum length and diameter are 500 mm and 200 mm, respectively, for the sections to be designed as length constraints within the scope of the conceptual design. The two-ring vee-gutter has 1.33 cm in diameter and 4.25 cm high. Jet A fuel is assumed to be injected into the core flow (90 degrees) from the spray bars. The spray is mounted in line with the vee-gutter to optimize the mixing of the flow. Analyses are performed for 4 cm between the spray bar and the vee-gutter. For the study, the GE J79 engine was examined from the literature and taken as a basis for the aerodynamic transition section design. Within the scope of TEKNOFEST 2023 Jet Engine Design Competition, a preliminary design of an afterburner module that can produce 700 pounds of thrust and has a life capacity of 25 hours should be realized in line with the design requirements and constraints. In the light of geometric constraints, one-dimensional combustion calculations of the module are made, and the parts are modelled using the relevant SolidWorks CAD program and these modelled parts are then transferred to ANSYS™ environment and the results and analyses are verified. The afterburner module flow analysis software program ANSYS™ is used to analyse the afterburner operation in both cold operating ranges (i.e. without combustion) using compressible, viscous and standard k-epsilon turbulence model. As a result, the effect of afterburner length on combustion performance is found to be significant. As a result of the calculations, afterburner length is found as 28.14 cm. It is found that the combustion efficiency is 81.5% and the temperature can be increased from 1050 K to 2044 K. The total pressure loss is 14.96% as pressure drop due to the geometric parameters and heat addition. The blockage ratio calculated due to the use of vee-gutter geometry is the most important parameter in the pressure drop. It is found that the jet engine producing 670 lbs (2981 N) of thrust when the afterburner is not working whereas it can provide a significant amount of power increment at the expense of a 50% increase in specific fuel consumption when the afterburner is active as well as providing a 738 lbs (3238 N) with a 10.1% thrust increase. The reason of the enhancement is mainly coming from the mixing effect of the vee-gutter on the flow structure.

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Section: Introductionmentioning

confidence: 99%

Preliminary design and analysis of an afterburner module

Sönmez,

Karabacak,

Ozgoren

2023

International Journal of Aeronautics and Astronautics

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show abstract

“…For engine component studies, Refs. [13,14] discussed the gas generator and ram combustor performances. Liu et al proposed the matching model of an intake-compressor interaction for the GG-ATR engine and numerically assessed its viability [17].…”

Section: Introductionmentioning

confidence: 99%