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.

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.

Effect of fuel on gas corrosion of jet engine combustion chambers

1972 ◽  
Vol 8 (4) ◽  
pp. 292-295
Author(s):  
V. N. Zrelov ◽  
V. S. Kurinov ◽  
L. V. Boiko
Keyword(s):  
Combustion Chambers ◽  
Jet Engine ◽  
Engine Combustion ◽  
Gas Corrosion

The Civic: A Concept in Vortex Induced Combustion for the Solar Gemini 10 kW Gas Turbine

1981 ◽  
Vol 103 (1) ◽  
pp. 34-42 ◽  
Author(s):  
J. R. Shekleton
Keyword(s):  
Gas Turbine ◽  
Diffusion Flames ◽  
Reynolds Numbers ◽  
Flame Stabilization ◽  
Fuel Injector ◽  
Combustion Chambers ◽  
Turbine Generator ◽  
Fuel Injectors ◽  
Swirl Flame ◽  
Combustion Processes

The Radial Engine Division of Solar Turbines International, an Operating Group of International Harvester, under contract to the U.S. Army Mobility Equipment Research & Development Command, developed and qualified a 10 kW gas turbine generator set. The very small size of the gas turbine created problems and, in the combustor, novel solutions were necessary. Differing types of fuel injectors, combustion chambers, and flame stabilizing methods were investigated. The arrangement chosen had a rotating cup fuel injector, in a can combustor, with conventional swirl flame stabilization but was devoid of the usual jet stirred recirculation. The use of centrifugal force to control combustion conferred substantial benefit (Rayleigh Instability Criteria). Three types of combustion processes were identified: stratified and unstratified charge (diffusion flames) and pre-mix. Emphasis is placed on five nondimensional groups (Richardson, Bagnold, Damko¨hler, Mach, and Reynolds numbers) for the better control of these combustion processes.

Practical Bypass Mixing Systems for Fan Jet Aero Engines

1966 ◽  
Vol 17 (2) ◽  
pp. 141-160 ◽  
Author(s):  
T. H. Frost
Keyword(s):  
Gas Turbines ◽  
Minimum Weight ◽  
Jet Engines ◽  
Metal Interface ◽  
Combustion Chambers ◽  
Propulsion Systems ◽  
Jet Engine ◽  
Aero Engines ◽  
Corrugated Metal ◽  
Constant Static Pressure

SummaryMixing systems have many applications in gas turbines and aircraft jet propulsion, e.g. mixing zones in combustion chambers, ejectors for jet lift thrust augmentors and supersonic propulsion systems. A further application similar to that of combustion chamber mixing is that of mixing the cold and hot exhausts of a bypass jet engine. These are both characterised by mixing at constant static pressure and approximately constant total pressure as opposed to the more general case of unequal pressures in ejector systems (Fig. 1).The exhaust mixing process as used in Rolls-Royce bypass jet engines, e.g. Spey and Conway, enables the potential of the bypass principle, in terms of minimum weight and fuel consumption, to be exploited by a simple practical device.This is achieved by mixing the two streams in a common duct of fairly short dimensions with a corrugated metal interface on the inlet side. The consideration of these practical systems forms the main topic of this paper.

An experimental and reduced modeling study of the laminar flame speed of jet fuel surrogate components

Fuel ◽  
2013 ◽  
Vol 113 ◽  
pp. 586-597 ◽  
Author(s):  
J.D. Munzar ◽  
B. Akih-Kumgeh ◽  
B.M. Denman ◽  
A. Zia ◽  
J.M. Bergthorson
Keyword(s):  
Laminar Flame ◽  
Jet Fuel ◽  
Flame Speed ◽  
Laminar Flame Speed ◽  
Reduced Modeling ◽  
Fuel Surrogate ◽  
Modeling Study

Simulation of Two-Dimensional Turbulent Recirculating Flow Field Behind a V-Shaped Bluff Body

1994 ◽  
Author(s):  
Z. Gu ◽  
M. A. R. Sharif
Keyword(s):  
Flow Field ◽  
Bluff Body ◽  
Flame Stabilization ◽  
Bluff Bodies ◽  
Two Dimensional ◽  
Combustion Chambers ◽  
Recirculating Flow ◽  
Conservative Form ◽  
Curvilinear Grid ◽  
Predictor Corrector

Abstract The two-dimensional turbulent recirculating flow fields behind a V-shaped bluff body have been investigated numerically. Similar bluff bodies are used in combustion chambers for flame stabilization. The governing transport equations in conservative form are solved by a pressure based predictor-corrector method. The standard k-ϵ turbulence closure model and a boundary fitted multi-block curvilinear grid system are used in the computation. The code is validated against turbulent flow over a backward facing step problem. The predicted flow field behind the bluff body is also compared with experiment. It is found that while the qualitative features of the flow are well predicted, there is quantitative disagreement between the measurement and prediction. This disagreement can be partially attributed to the k-ϵ turbulence model which is known to be inadequate for recirculating flows. Parametric investigation of the flow field by varying the shape and size of the bluff body is also performed and the results are reported.

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