Generic Geometry Definition of the Aircraft Engine Combustion Chamber

2004 ◽  
Author(s):  
Savad A. Shakariyants ◽  
Jos P. van Buijtenen ◽  
Wilfried P. J. Visser
Keyword(s):  
Combustion Chamber ◽  
Aircraft Engine ◽  
Working Environment ◽  
Combustion Chambers ◽  
Turbofan Engine ◽  
Empirical Relations ◽  
Size Constraints ◽  
Engine Combustion ◽  
Definition Of ◽  
Aircraft Application

The type and layout of a particular gas turbine combustion chamber are largely determined by engine specifications and, peculiarly for the aircraft application, by the effort to use the available space as effectively as possible. Therefore, large commercial turbofan engine combustors exhibit a great degree of commonality. This commonality is a result of the similarity in working environment, size constraints and also safety, performance, and weight requirements. The objective of the present work is to propose generic relations between combustor overall performance and geometry, in order to develop accurate models for combustion quality and emission studies. Therefore, an algorithm has been developed to produce a generic combustion chamber layout. The algorithm is based on a set of empirical relations, semi-analytical methods, statistical figures and design philosophy. Results have been validated in a case study, showing accurate correspondence with modern turbofan engine combustors. An alternate application of the models may be preliminary sizing or design of aero-engine combustion chambers.

Predicting Lean Blowout and Emissions of Aircraft Engine Combustion Chamber Based on CRN

2019 ◽  
Vol 36 (2) ◽  
pp. 147-156 ◽  
Author(s):  
Yinli Xiao ◽  
Zhengxin Lai ◽  
Zupeng Wang ◽  
Kefei Chen
Keyword(s):  
Combustion Chamber ◽  
Initial Conditions ◽  
Aircraft Engine ◽  
Chemical Reactor ◽  
Pollutant Emissions ◽  
Chemical Mechanism ◽  
Lean Blowout ◽  
Operating Modes ◽  
Engine Combustion ◽  
Set Up

Abstract To predict the pollutant emissions and lean blowout, chemical reactor network (CRN) model is applied to the modern aircraft engine combustion chamber. In this study, the CRN which represent the major features of aerodynamics and combustion in the combustion chamber is set up based on the OpenFOAM simulation results. The boundary and the initial conditions used for the CRN derive from the operating modes of typical aircraft engine cycle. A 21 species 30 steps chemical mechanism of kerosene is employed in the CRN method. The levels of pollutant emissions are obtained under four ICAO engine power settings of idle, approach climb and take off. The lean blowout equivalent ratio is evaluated at the idle power setting. The results will be helpful to predict the aircraft engine exhaust emissions and lean blowout (LBO).

Phenomenological Model for Swirl-Squish Interactions in Combustion Chamber Geometries of DI Diesel Engines

2002 ◽  
Author(s):  
Rajesh Sharma ◽  
Pramod S. Mehta
Keyword(s):  
Combustion Chamber ◽  
Direct Injection ◽  
Phenomenological Approach ◽  
Temporal Variations ◽  
Wall Friction ◽  
Combustion Chambers ◽  
Piston Bowl ◽  
Engine Combustion ◽  
Air Mixing ◽  
Good Agreement

The intake generated mean motion is generally augmented by the piston bowl configurations to result into desired level of fuel-air mixing in an engine combustion chamber. The swirl and squish are the two in-cylinder air motions identified in direct injection diesel engine combustion chambers. In this paper, an attempt is made to model swirl and squish interactions through a phenomenological approach considering the temporal variations of wall friction and moment of inertia of the fluids inside the piston bowl and the annular space. The model predictions are found to be in good agreement with the available experimental data.

Flame Stabilization of Jet Engine Combustors for Jet Fuel with Blended Biofuels

2021 ◽  
Vol 13 (3) ◽  
Author(s):  
R. Asad Ahmed ◽  
A. Surya ◽  
R. Tamil Selvan ◽  
V. Ramaiah ◽  
K. Vignesh
Keyword(s):  
Economic Benefits ◽  
Jet Fuel ◽  
Flame Stabilization ◽  
Flame Speed ◽  
Combustion Chambers ◽  
Turbofan Engine ◽  
Jet Engine ◽  
Ansys Analysis ◽  
Engine Combustion ◽  
Online Software

Biofuel usage has good environmental and economic benefits but at the same time it has weak performance and fuel efficient when compared to usage jet fuel in aircraft similarly release of sulphur particles will end solar radiation. In additionally to these barriers, flame speed of biofuel is very low compared to jet fuel flame speed so a new task is arrived here that is flame stabilization in combustion chambers while using blended biofuel with jet fuel. Hence, we are analysing aircraft turbofan engine combustion chambers both by theoretical and analytical manner about its working when using blended biofuel. Using NASA CEA online software, the combustor data are gathered and are compared with analysis of designed combustor in ANSYS analysis software. The flame analysis is more important when using the blended biofuel in different ratio.

The Sampling of Rocket Combustion Gases

1964 ◽  
Vol 68 (647) ◽  
pp. 759-764
Author(s):  
R. Bryan
Keyword(s):  
Combustion Chamber ◽  
Rocket Engine ◽  
Operating Conditions ◽  
Combustion System ◽  
Combustion Chambers ◽  
Ratio Distribution ◽  
Mixture Ratio ◽  
Combustion Gases ◽  
Engine Combustion ◽  
Combustion Phase

Summary:—In the past, attempts have been made to evaluate injectors for rocket engine combustion chambers by the use of water analogy rigs and model combustion systems that simulated the injection and combustion phase change occurring in the actual engine. To confirm that conditions in the engine were being correctly simulated, a technique was evolved for determining the mixture ratio distribution achieved by the combustion system of a Spectre variable thrust rocket engine. Gas samples extracted from the rocket-efflux were analysed, and the technique has been applied to evaluate the Spectre's standard central mushroom type injector and also a multi-head injector.Tests have been conducted over a thrust range of 2000 lb to 8000 lb and at oxidant/fuel ratios from 7·5 to 13·0.In parallel with this external sampling, a probe has been designed and developed for extracting gas samples from selected points across a diameter of the combustion chamber itself. This probe has been successfully operated for several minutes under combustion conditions of 500 p.s.i.a. and 2600°K, without sustaining any damage.Analysis of the oxidant/fuel ratio pattern within the combustion chamber and in the efflux, at comparable operating conditions, indicates that little change in distribution occurs between these two points of the system. Also, the distribution found with the standard injector was that for which the combustion system was designed. It is demonstrated that loss of performance depends on the degree of non-uniformity of mixing. A 5 per cent loss in performance at full thrust and optimum mixture ratio occurs with the standard injector.

scholarly journals Modeling of Spray Combustion with a Steady Laminar Flamelet Model in an Aeroengine Combustion Chamber Based on OpenFOAM

2018 ◽  
Vol 2018 ◽  
pp. 1-13
Author(s):  
Yinli Xiao ◽  
Zupeng Wang ◽  
Zhengxin Lai ◽  
Wenyan Song
Keyword(s):  
Combustion Chamber ◽  
High Performance ◽  
Numerical Models ◽  
Spray Combustion ◽  
Combustion Chambers ◽  
Flamelet Model ◽  
Steady Laminar ◽  
Good Agreement ◽  
Laminar Flamelet ◽  
Laminar Flamelet Model

The development of high-performance aeroengine combustion chambers strongly depends on the accuracy and reliability of efficient numerical models. In the present work, a reacting solver with a steady laminar flamelet model and spray model has been developed in OpenFOAM and the solver details are presented. The solver is firstly validated by Sandia/ETH-Zurich flames. Furthermore, it is used to simulate nonpremixed kerosene/air spray combustion in an aeroengine combustion chamber with the RANS method. A comparison with available experimental data shows good agreement and validates the capability of the new developed solver in OpenFOAM.

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