11 Furnace exit temperature

2021 ◽  
pp. 32-40
Keyword(s):  
1989 ◽  
Author(s):  
PAUL NELSON ◽  
NORMAN POTI ◽  
JEFFREY STRICKER

1996 ◽  
Author(s):  
Stephen R. Schaps ◽  
George Alers ◽  
Arnold Kahn ◽  
Louis C. Phillips

2014 ◽  
Vol 611-612 ◽  
pp. 981-988 ◽  
Author(s):  
Ramona Hölker ◽  
Matthias Haase ◽  
Nooman Ben Khalifa ◽  
A. Erman Tekkaya

The influence of local inner die cooling on the heat balance in hot aluminum extrusion was investigated. For the manufacturing of the die with cooling channels close to the forming zone, the layer-laminated manufacturing method was applied. The new tooling technology was applied in order to decrease the profiles exit temperature and to avoid thermally induced surface defects with the aim to raise the productivity in hot aluminum extrusion processes. Numerical and experimental investigations revealed that, while maintaining the exit temperature of the extrudate, a distinct increase of the production speed up to 300% can be realized, while the extrusion force increases only slightly. An effect on the profiles microstructure was also detected. By applying die cooling, grain coarsening can be significantly limited or even be avoided.


Extrusion, Second Edition provides a complete and thorough overview of the processes, equipment, and tooling used to extrude metals into desired shapes and forms. It covers all types of processes, including direct, indirect, and hydrostatic extrusion, cable sheathing, continuous extrusion, and the extrusion of powder metals. It describes each process in detail, explaining how the associated forces, stresses, displacements, and heat cause metals to deform and flow and how it affects the microstructure and properties of the resulting products. It discusses the design, setup, and control of extrusion equipment, the use of lubricants and shells, the effect of tooling materials and geometries, and the practical implications of material flow, friction, discard length, and exit temperature. It describes the deformation and extrusion behaviors of many materials, the product forms into which they can be made, and related processing requirements. The book also provides detailed application examples, an introduction to quality management, a review of the basics of metallurgy, and experimentally measured extrusion data. For information on the print version, ISBN 978-0-87170-837-3, follow this link.


1976 ◽  
Vol 98 (4) ◽  
pp. 501-505 ◽  
Author(s):  
P. E. Jenkins

The mean and conditional temperature and velocity profiles and their correlations were measured in a heated jet of air. The conditional measurements were “zone” averaged measurements, taken only in the fully turbulent region of the flow field by using an electronic sampling technique. The zone averaged measurements were taken of the velocity, temperature, shear stress, and the velocity-temperature correlation at three axial stations: x/D = 35, 45, and 50. The jet Reynolds number (based on the jet slot width) was held constant at 1.43 × 104, with a jet exit temperature excess of θ = 35°C. The conditioned profiles show a large variation from the mean measurements in the fully turbulent region of the jet. The zone averaged measurements approach the mean only as the jet center line and jet interface is approached.


Author(s):  
Stefan Kuntzagk ◽  
Jörn Kraft ◽  
Ina Esemann

The combustion chamber of aircraft engines plays an important role in achieving the optimum performance during an engine overhaul. For long decades, it has been common understanding in the MRO business that a well overhauled compressor and turbine are required to get an engine with low SFC and high EGT margin. In recent work at Lufthansa Technik AG, a comprehensive CFD analysis of the combustion chamber showed that, in contrast to this, small geometrical features influence the mixing process in the combustion chamber and can have an effect on the exit temperature profile. This in turn can reduce the accuracy of the EGT measurement significantly and create measurement errors and misinterpretations of the real engine performance. In order to get insight into the flow topology, a very detailed digital model has been created using scans of the hardware available in the shop. Important geometrical features such as the cooling provisions and swirl creating components have been included in a very detailed manner with an efficient hexahedral mesh. The model includes the HPT vanes and the cooling flow extraction from the secondary cold flow. CFD results have been generated using the flow solver Ansys CFX 17.1, which is able to predict all relevant physical effects such as injection of liquid fuel, evaporation, and combustion of Jet A1 fuel using the Burning-Velocity combustion model. The flow in the combustion chamber shows large natural fluctuations. Subsequently, for each case a transient calculation has been carried out in order to allow an evaluation of the time-averaged flow field. Different geometrical features are investigated to predict the effect of geometry deviations on the exit temperature profile, e.g. the shape and size of the dilution holes. Finally along the example of two CFM56 engines it will be shown how the data obtained by the detailed CFD model is used to optimize work-scoping and maintenance procedures. On the two cases put forward the combination of extended test-cell instrumentation and detailed modeling enabled not only the identification but also the rectification of combustion chamber deviations. This in turn minimized the necessary work, whereas in the past combustion chamber issues often went unnoticed and consequently resulted in extensive additional work.


Author(s):  
L. A. Diehl ◽  
J. A. Biaglow

Emissions and performance characteristics were determined for two full-annulus swirl-can modular combustors operated to near-stoichiometric fuel air ratios. The purposes of the tests were to obtain stoichiometric data at inlet-air temperatures up to 894 K and to determine the effect of module number by investigating 120 and 72 module swirl-can combustors. The maximum average exit temperature obtained with the 120-module swirl-can combustor was 2465 K with a combustion efficiency of 95 percent at an inlet-air temperature of 894 K. The 72-module swirl-can combustor reached a maximum average exit temperature of 2306 K with a combustion efficiency of 92 percent at an inlet-air temperature of 894 K. At a constant inlet air temperature, maximum oxides of nitrogen emission index values occurred at a fuel-air ratio of 0.037 for the 72-module design and 0.044 for the 120-module design. The combustor average exit temperature and combustion efficiency were calculated from emissions measurements. The measured emissions included carbon monoxide, unburned hydrocarbons, oxides of nitrogen, and smoke.


1987 ◽  
Vol 109 (2) ◽  
pp. 237-243 ◽  
Author(s):  
W. W. Chin ◽  
M. A. El-Masri

Results of a study for selecting the optimum parameters of a dual-pressure bottoming cycle as a function of the gas turbine exhaust temperature are presented. Realistic constraints reflecting current technological practice are assumed. Exergy analysis is applied to quantify all loss sources in each cycle. Compared to a single pressure at typical exhaust gas temperatures the optimized dual-pressure configuration is found to increase steam cycle work output on the order of 3 percent, principally through the reduction of the heat transfer irreversibility from about 15 to 8 percent of the exhaust gas energy. Measures to further reduce the heat transfer irreversibility such as three-pressure systems or use of multicomponent mixtures can therefore only result in modest additional gains. The results for the efficiency of optimized dual-pressure bottoming cycles are correlated against turbine exit temperature by simple polynomial fits. Sensitivity of the results to variations in the constraint envelope are presented.


1992 ◽  
Vol 72 (1) ◽  
pp. 71-81 ◽  
Author(s):  
B. M. Mosimanyana ◽  
D. N. Mowat

The effects of processing variables on soybean crude protein (CP) ruminal degradation were investigated. Soybean meal (SBM) was heated in a forced-air oven (90 °C, 1 h) with blood (0, 5, 10 and 20% dry matter) and/or xylose (3 mol mol−1 SBM-blood lysine) in a randomized complete block design. In another experiment, whole soybeans were utilized using the following treatments: raw; roasted (in Gem Co. unit exit temperature 150 °C) and steeped for 0 or 2 h; roasted, flaked (exit temperature 111 °C) and steeped for 0, 1, 2, 3 h or 1 h with 4% xylose and/or 10% blood. Solubility of SBM CP was reduced (P < 0.01) by the addition of xylose, without adverse effects on pepsin-digestible CP and acid detergent insoluble nitrogen. In situ degradation of CP (EDCP), assuming a passage rate of 5% h−1, of SBM was reduced by the addition of blood (P < 0.05) and particularly xylose (P < 0.01). Soybean CP solubility was reduced (P < 0.01) by roasting and flaking (65.6 vs. 17.6% total CP). Not flaking the roasted beans further reduced (P < 0.01) CP solubility (to 10.4%) probably due to less rapid cooling. The EDCP of raw soybeans (87.6%) was reduced by roasting (64.2%), steeping whole (57.6%) or flaked (61.1%) beans. These data support xylose to effectively reduce ruminal degradation of SBM and simple steeping (1 h) with or without flaking to further reduce EDCP of roasted soybeans. Key words: Soybean meal, soybeans, xylose, blood, steeping, protein degradation


Author(s):  
Kristen Bishop ◽  
William Allan

The effects of fuel nozzle condition on the temperature distributions experienced by the nozzle guide vanes have been investigated using an optical patternator. Average spray cone angle, symmetry, and fuel streaks were quantified. An ambient pressure and temperature combustion chamber test rig was used to capture exit temperature distributions and to determine the pattern factor. The rig tests matched representative engine operating conditions by matching Mach number, equivalence ratio, and fuel droplet size. It was observed that very small deviations (± 10° in spray cone angle) from a nominal distribution in the fuel nozzle spray pattern correlated to increases in pattern factor, apparently due to a degradation of mixing processes, which created larger regions of very high temperature core flow and smaller regions of cooler temperatures within the combustion chamber exit plane. The spray cone angle had the most measureable influence while the effects of spray roundness and streak intensity had slightly less influence. Comparisons were made with published studies conducted on the combustion chamber geometry, and recommendations were made for fuel nozzle inspections.


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