Topic
Afterburner
About: Afterburner is a research topic. Over the lifetime, 811 publications have been published within this topic receiving 5944 citations.
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01 Apr 1984
TL;DR: In this paper, a real time computer program was implemented on a F-15 jet fighter to monitor in-flight engine performance of a Digital Electronic Engine Controlled (DEES) F-100 engine.
Abstract: A real time computer program was implemented on a F-15 jet fighter to monitor in-flight engine performance of a Digital Electronic Engine Controlled (DEES) F-100 engine. The application of two gas generator methods to calculate in-flight thrust real time is described. A comparison was made between the actual results and those predicted by an engine model simulation. The percent difference between the two methods was compared to the predicted uncertainty based on instrumentation and model uncertainty and agreed closely with the results found during altitude facility testing. Data was obtained from acceleration runs of various altitudes at maximum power settings with and without afterburner. Real time in-flight thrust measurement was a major advancement to flight test productivity and was accomplished with no loss in accuracy over previous post flight methods.
1 citations
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05 Dec 2013TL;DR: In this article, the afterburner liner metal temperature prediction and comparison with measured metal temperature during aero engine testing at reheat condition was discussed. But, the authors did not consider the thermal transfer modes of heat transfer, conduction due to presence of low conductivity thermal barrier coating and convection due to higher gas velocities.
Abstract: Military aero engines employ afterburner system for increasing the reheat thrust required during combat and takeoff. During reheat the gas temperature in the afterburner is of the order of 2100K.The afterburner liner has to be cooled with the available bypass air to maintain metal temperature within allowable limits. The liner has cooling rings at the rear to cool the liner with tangential film cooling.This paper discusses the methodology of afterburner liner metal temperature prediction and comparison with measured metal temperature during aero engine testing at reheat condition. All the modes of heat transfer are considered for thermal analysis, radiation due to higher level of gas temperature during reheat, conduction due to presence of low conductivity thermal barrier coating and convection due to higher gas velocities are considered.At different steady state reheat conditions metal temperature are predicted and compared with measured data during aero engine testing. The predicted skin temperatures and measured temperatures are in good agreement. Empirical correlations are used for estimating the heat loads coming on the liner and adiabatic film temperature near screech holes and cooling rings. Metal temperature and thermal loads coming onto the liner are predicted with 1D code. The estimated thermal loads are applied on 3D FE model to obtain nodal temperature distribution. The thermal Analysis is carried using ANSYS software in which thermal barrier coating is also modeled.The parameters like gas temperature, thermal barrier coating thickness, coating conductivity, and coolant mass flow distribution are considered for carrying out a sensitivity analysis of liner metal temperature.Copyright © 2013 by ASME
1 citations
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TL;DR: In this paper, the k-equation subgrid-scale model is used for the large-eddy simulation(LES) of turbulent chemically reacting flows in the model afterburner with the V-gutter flame holder.
Abstract: In this paper, the k-equation subgrid-scale model is used for the large-eddy simulation(LES) of turbulent chemically reacting flows in the model afterburner with the V-gutter flame holder. Two dimensional body-fitted grid is generated by using the zonal methods, the EBU combustion subgrid-scale model is employed to determine the chemical reaction rate, the heat flux model is applied to prediction of the heat flux, SIMPLE algorithm and hybrid scheme are used with the staggered grid system, wall function is applied to treating near wall region. Prom the results of the numerical simulation, the recirculation zone is found behind the V-gutter flame holder. The experiments are preformed in the combustion laboratory. The numerical results are well agreement with experimental measurements of temperature. The results show that the large-eddy simulation method by body-fitted grid may be used to investigate reacting flows and combustion process in practical combustors.
1 citations
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01 Jun 1982TL;DR: In this article, a simplified gross thrust calculation method was evaluated on its ability to predict the gross thrust of a modified J85-21 engine using tailpipe pressure data and ambient pressure data.
Abstract: A simplified gross thrust calculation method was evaluated on its ability to predict the gross thrust of a modified J85-21 engine. The method used tailpipe pressure data and ambient pressure data to predict the gross thrust. The method's algorithm is based on a one-dimensional analysis of the flow in the afterburner and nozzle. The test results showed that the method was notably accurate over the engine operating envelope using the altitude facility measured thrust for comparison. A summary of these results, the simplified gross thrust method and requirements, and the test techniques used are discussed in this paper.
1 citations
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23 Nov 2018
TL;DR: In this article, an afterburner with a circular arc-shaped fan-shaped nozzle and a concave cavity structure is presented, where the fuel space atomization effect of the forced inner cone in the circumferential direction is enhanced.
Abstract: The invention discloses an afterburner with a circular arc-shaped fan-shaped nozzle and a concave cavity structure, and belongs to the field of aero-engines. Flame can be stabilized by utilizing a concave cavity structure formed by a supporting plate and a forced inner cone, the fuel space atomization effect of the forced inner cone in the circumferential direction is enhanced by adopting the circular arc-shaped fan-shaped nozzle, the fuel spray expansion angle in the circumferential direction of the forced inner cone can be increased, so that the distribution of the fuel space in the circumferential direction is more uniform. According to the afterburner, the afterburner can be smoothly ignited under various complex working conditions, and flame propagation is realized along the concave cavity in the circumferential direction of the forced inner cone, so that the combustion stability in the afterburner is effectively improved; and meanwhile, the length of the afterburner is shortened,the total pressure recovery coefficient is improved, the flow loss is reduced, the combustion efficiency is increased, the generation of pollutants such as NOx and CO are effectively reduced, and theoverall performance of the engine is improved.
1 citations