Effects of asynchronous ignition phase on knock combustion of two stroke engine

贝太学; 魏民祥; 刘锐; 盛敬

doi:10.13224/j.cnki.jasp.2017.02.009

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Effects of asynchronous ignition phase on knock combustion of two stroke engine

更新时间：2026-07-07

- Effects of asynchronous ignition phase on knock combustion of two stroke engine
- Vol. 32, Issue 2, Pages: 322-329(2017)
- 作者机构：
  
  1. 南京航空航天大学能源与动力学院,南京,210016
  2. 南昌工程学院机械与电气工程学院,南昌,330099
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2017.02.009
  CLC：
- Published：2017
- 稿件说明：
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贝太学, 魏民祥, 刘锐, 盛敬. 异步点火相位对二冲程发动机爆震燃烧的影响[J]. 航空动力学报, 2017, 32(2): 322-329.

doi: 10.13224/j.cnki.jasp.2017.02.009
贝太学, 魏民祥, 刘锐, 盛敬. 异步点火相位对二冲程发动机爆震燃烧的影响[J]. 航空动力学报, 2017, 32(2): 322-329. DOI： 10.13224/j.cnki.jasp.2017.02.009.

doi: 10.13224/j.cnki.jasp.2017.02.009 DOI：

摘要

为了了解异步点火相位对二冲程航空活塞发动机燃用煤油时的爆震影响问题，使用Fire软件建立了发动机燃烧室的计算模型，并通过试验验证了该模型，研究了异步点火相位对发动机缸内燃烧以及火焰面密度分布、爆震强度的影响等.结果表明：在转速为5000r/min、全负荷工况、混合气当量比为11、点火能量为3564mJ条件下，当其中一个火花塞点火时刻固定在上止点前曲轴转角为29° ，另一个火花塞相对其分别提前曲轴转角为1°，3°，5°时点火，随着双火花塞异步点火相位差的增大，缸内平均压力、放热率及累积放热量均呈现减小的趋势，两个火花塞附近的湍动能增大，火焰传播速度加快，火焰发展期缩短，爆震强度表征物的浓度逐步减小，二冲程煤油发动机爆震发生的倾向减小.

Abstract

In order to understand the impact of asynchronous ignition phase on the knock of twostroke kerosene aeropiston engine

a calculation model of the combustion chamber was established by using fire software. And the validity of the model was verified by the test data. The simulation and test results show that: at 5000r/min

full load and equivalence ratio of the mixture under 11 conditions

ignition energy at 3564mJ conditions

when one of the spark plugs ignition time is fixed at before top dead center crank angle is 29°

another ignition time is set ahead of crank angle is 1°

3° and 5° relatively; with the increase of the phase difference of the double spark ignition

the average pressure

heat release rate and the accumulated heat release rate have decreased. The turbulent kinetic energy of the two spark plugs increases

the flame propagation velocity rises

the flame development period is shortened

and the concentration of the knock intensity is reduced gradually.

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Related Institution

Science and Technology on Combustion, Internal Flow and Thermal-Structure Laboratory, School of Astronautics, Northwestern Polytechnical University

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College of Mechanical and Electrical Engineering，Beijing University of Chemical Technology

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室

西北工业大学航天学院燃烧、流动和热结构国家级重点实验室

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