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Aircraft engine main fuel nozzle design technology of thermal protection

Author: HuangYiYong
Tutor: LiXunBo；XuHuaSheng
School: University of Electronic Science and Technology
Course: Mechanical Engineering
Keywords: Fuel nozzle Thermal Protection Heat transfer calculation Heat Transfer
CLC: V233.22
Type: Master's thesis
Year: 2011
Downloads: 170
Quote: 0
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Abstract


With advanced high-performance gas turbine engine pressure ratio increased and fuel as airframe and engine cooling coolant enhanced the role of the combustor inlet air temperature and fuel temperature rising, resulting in fuel coke , resulting in lower nozzle life. This issue has become much attention abroad and need to be solved in a new topic. To this end a number of studies abroad , explore a variety of nozzle insulation measures on the one hand , on the other hand are looking for high-temperature nozzle structure scheme ; All of these have gradually been applied. In this paper, aircraft engine fuel injection nozzle thermal protection structure design technology has been studied , using convection heat transfer engineering method to establish a nozzle one -dimensional heat transfer model , combined with three-dimensional numerical simulation of a certain type of aircraft engine fuel nozzles in the main flight conditions the heat transfer characteristics were calculated and analyzed , presented the prototype nozzle thermal protection structure improvement program. Final test on the heat transfer through the nozzle nozzle heat transfer calculation established by the model is validated , the results indicate that test results more in line with the results of the calculation method has some engineering applicability .

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Engine attachment system > Fuel supply system > Member
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