CFD Study of Cooled Flow in Annular Combustor of Aircraft-Engine

2017 ◽  
Keyword(s):  
Aircraft Engine ◽  
Annular Combustor

Development of an Aeroderivative Gas Turbine Dry Low Emissions Combustion System

1994 ◽  
Vol 116 (3) ◽  
pp. 542-546 ◽  
Author(s):  
G. Leonard ◽  
J. Stegmaier
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
System Component ◽  
Test Results ◽  
Combustion System ◽  
Fuel Delivery ◽  
Component Test ◽  
Engine Combustion ◽  
Annular Combustor ◽  
New System

This paper gives the development status of GE’s new aeroderivative premixed combustion system. This system consists of a new fuel staged annular combustor, compressor rear frame, first-stage turbine nozzle, electronic staging controller, and fuel delivery system. Component test results along with a description of the combustion system are presented. This new system will reduce NOx emissions by 90 percent relative to the original aircraft engine combustion system while maintaining low emissions of CO and UHCs. Tests of a LM6000 gas turbine equipped with the new system are planned for early 1994.

Characterising Mixing and Soot Production Using a Lagrangian Statistical Method

2020 ◽  
Author(s):  
Vasileios Kampanas ◽  
Maxwell Williams ◽  
Andrew Garmory
Keyword(s):  
Statistical Method ◽  
Mixture Fraction ◽  
Aircraft Engine ◽  
Processing Technique ◽  
Reacting Flows ◽  
Residence Times ◽  
Engine Model ◽  
Air Mixing ◽  
Annular Combustor ◽  
Annular Sector

Abstract An understanding of fuel-air mixing, along with the link between turbulent fluid flows and soot production is vital for the design of an efficient, low emissions gas turbine combustor. This paper uses a Lagrangian statistical method to investigate the time histories of mixing hence and soot development for massless parcels tracked within an LES calculation. This provides the advantage of investigating soot development using an inexpensive post-processing technique. The method comprises tracking massless parcels through the flow and recording the local temperature and composition at the parcel location, as well as the age of the parcel. This can be used to give statistical information about various aspects of mixing and soot production, such as distributions of mixture fraction or residence times. The history for each parcel can then be used in a postprocessing step to predict the soot development in time for that parcel path. This has been used to compare Large Eddy Simulations (LES) of reacting flows in both a laboratory aero-engine model combustor and a geometry representative of an annular sector from an aircraft engine combustor. It was found, that when normalized by a reference time scale based on combustor length and bulk velocity, the residence times for the annular sector were considerably shorter and mixture fraction distributions wider. This was due to a much higher chance of parcels being recirculated within the primary zone of the laboratory combustor. Further analysis of the annular combustor sector showed that very different mixing is found between the oxidation ports on the centre of the sector compared to those at the edge. The instantaneous mixing is seen to be less effective for those ports at the edge of the sector and this leads to higher soot levels in these regions.

Verification of Low NOx Performance of Simple Primary Rich Combustion Approach by a Newly Established Full Annular Combustor Test Facility

2008 ◽  
Author(s):  
Mitsumasa Makida ◽  
Hideshi Yamada ◽  
Kazuo Shimodaira ◽  
Seiji Yoshida ◽  
Yoji Kurosawa ◽  
...  
Keyword(s):  
Pressure Ratio ◽  
Aircraft Engine ◽  
Test Facility ◽  
Nox Emissions ◽  
Temperature Profiles ◽  
Experimental Facility ◽  
Lean Combustion ◽  
Annular Combustor ◽  
Exit Temperature ◽  
The Rich

In the TechCLEAN project of JAXA, experimental research has been being conducted to develop a combustor for a small aircraft engine (with pressure ratio of about 20). The combustor was tuned to show the behavior of the Rich-Lean combustion through tests under atmospheric and practical conditions. And in 2006, by a designed multi-sector combustor, NOx emissions were reduced to lower than 42% of the ICAO CAEP4 standard. Based on the tuned combustor, full annular combustors were designed. In parallel, an experimental facility to test the full annular combustors under practical conditions was newly constructed in the spring of 2007. The inlet air conditions were set to the ICAO LTO cycle conditions of the target engine; 0.3–1.8MPa for pressure, 400–700K for temperature and 4–18kg/s for air mass flow rate. Through the full annular combustion experiments under practical conditions, the combustors were tuned to keep good combustion performance which was verified by the multi-sector combustors. The optimized full annular combustor finally achieved the following performance; NOx emissions were reduced to lower than 40% of the ICAO CAEP4 standard, maintaining low CO and THC emissions, good exit temperature profiles (P.T.F. = 0.19 at the take-off condition) and good lean blow-out performance (AFR>200 at the idle condition). The process of the optimization is discussed in this report.

Prediction of the Total Sound Level of the Annular Combustor Noise of Aircraft Engine Based on SVR

2014 ◽  
Vol 687-691 ◽  
pp. 33-36
Author(s):  
Lian Jun Zhu ◽  
Yu Cai Dong ◽  
Jian Guang Yuan ◽  
Liang Hai Yi ◽  
Ge Hua Fan
Keyword(s):  
Influence Factors ◽  
Projection Pursuit ◽  
Aircraft Engine ◽  
Sound Level ◽  
Effect Factor ◽  
Engine Design ◽  
Annular Combustor ◽  
Set Up ◽  
The Relationship ◽  
Better Than

Because of the high temperature and high pressure environment inside the annular combustor of an aircraft engine, the direct measurement of the burner noise is very difficult. This paper set up the model of the total sound level and the effect factor SVR though analyzing the relationship between the total sound level and noise parameters of the combustion chamber the annular combustor an aircraft engine and the influence factors,, and it is better than multiple regression mode and the projection pursuit regression model, and predict the predicting samples so it is important for aero-engine design and reliability analysis.

Assessment of Aero-Thermal Design Methodology for Effusion Cooled Lean Burn Annular Combustors

2014 ◽  
Author(s):  
A. Andreini ◽  
B. Facchini ◽  
L. Mazzei ◽  
L. Bellocci ◽  
F. Turrini
Keyword(s):  
Film Cooling ◽  
Cooling System ◽  
Heat Removal ◽  
Protective Layer ◽  
Aircraft Engine ◽  
Thermal Design ◽  
Heat Transfer Analysis ◽  
Lean Burn ◽  
Annular Combustor ◽  
Combustion Technology

Increasingly stringent limitations imposed on aircraft engine emissions have led many manufacturers toward lean combustion technology, which involves a relevant increase in mass flow rate dedicated to primary combustion, leading as a consequence to a reduction of air dedicated to cooling of liners. One of the most promising cooling techniques in such conditions is represented by effusion cooling, which consists of an array of closely spaced discrete film cooling holes. This cooling method is based on a protective layer of cooling flow on the hot side of the liner, enhancing at the same time the heat removal within the holes. In the latest years many aero engine manufacturers have increased the research and technology investment on this combustion technology. Working in partnership with the University of Florence, specific component design tools and experimental techniques have been improved by Avio Aero for combustor gas turbine investigation. From a design perspective, CFD analysis has become a key tool up to the early stages of novel combustor design process, producing affordable direct 3D optimization of combustor aerodynamics. Nevertheless, a RANS simulation of even only a single sector of an annular combustor still presents a challenge when the cooling system is taken into account. This issue becomes more critical in case of modern effusion cooled combustors, which may contain up to two thousand holes for the single sector. For this reason, many efforts have been devoted to develop methodologies based on film cooling modeling. Among the approaches published in the literature, models based on local sources represent a good compromise between simplicity and accuracy, with the capability to automatically perform a Conjugate Heat Transfer analysis. This type of methodology has been already defined and validated by the authors, with comparison on effusion cooled plates in terms of experimental overall effectiveness measurements as well as the application on a tubular combustor test case. In the context of this work, the proposed approach has been applied to the analysis of a lean annular combustor with the purpose of investigating pressure losses, flow split and metal temperature field. The results obtained have been compared to experimental data and different numerical tools exploited during the preliminary design of these devices.

Development of an Aeroderivative Gas Turbine Dry Low Emissions Combustion System

1993 ◽  
Author(s):  
Gary Leonard ◽  
James Stegmaier
Keyword(s):  
Gas Turbine ◽  
Aircraft Engine ◽  
System Component ◽  
Test Results ◽  
Combustion System ◽  
Fuel Delivery ◽  
Component Test ◽  
Engine Combustion ◽  
Annular Combustor ◽  
New System

This paper gives the development status of GE’s new aeroderivative premixed combustion system. This system consists of a new fuel staged annular combustor, compressor rear frame, first stage turbine nozzle, electronic staging controller, and fuel delivery system. Component test results along with a description of the combustion system are presented. This new system will reduce NOx emissions by 90% relative to the original aircraft engine combustion system while maintaining low emissions of CO and UHCs. Tests of a LM6000 gas turbine equipped with the new system are planned for early 1994.

High-Temperature Instability of A Cr2Nb-Nb(Cr) Microlaminate Composite

1996 ◽  
Vol 54 ◽  
pp. 374-375
Author(s):  
M. Larsen ◽  
R.G. Rowe ◽  
D.W. Skelly
Keyword(s):  
Heat Treatment ◽  
Solid Solution ◽  
High Temperature ◽  
Elevated Temperatures ◽  
Aircraft Engine ◽  
Lattice Parameter ◽  
Microstructural Stability ◽  
Elevated Temperature Strength ◽  
Cross Sectional ◽  
Bcc Structure

Microlaminate composites consisting of alternating layers of a high temperature intermetallic compound for elevated temperature strength and a ductile refractory metal for toughening may have uses in aircraft engine turbines. Microstructural stability at elevated temperatures is a crucial requirement for these composites. A microlaminate composite consisting of alternating layers of Cr2Nb and Nb(Cr) was produced by vapor phase deposition. The stability of the layers at elevated temperatures was investigated by cross-sectional TEM.The as-deposited composite consists of layers of a Nb(Cr) solid solution with a composition in atomic percent of 91% Nb and 9% Cr. It has a bcc structure with highly elongated grains. Alternating with this Nb(Cr) layer is the Cr2Nb layer. However, this layer has deposited as a fine grain Cr(Nb) solid solution with a metastable bcc structure and a lattice parameter about half way between that of pure Nb and pure Cr. The atomic composition of this layer is 60% Cr and 40% Nb. The interface between the layers in the as-deposited condition appears very flat (figure 1). After a two hour, 1200 °C heat treatment, the metastable Cr(Nb) layer transforms to the Cr2Nb phase with the C15 cubic structure. Grain coarsening occurs in the Nb(Cr) layer and the interface between the layers roughen. The roughening of the interface is a prelude to an instability of the interface at higher heat treatment temperatures with perturbations of the Cr2Nb grains penetrating into the Nb(Cr) layer.

Report and discussion on “A philosophy of aircraft engine manufacture”

1965 ◽  
Vol 44 (7) ◽  
pp. 344
Author(s):  
L.R. Beesly ◽  
Morley ◽  
W.S. Hollis ◽  
Higson Smith ◽  
G.A.J. Witton ◽  
...  
Keyword(s):  
Aircraft Engine
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