| 苏湛超1，2 ，胡斌2，3，5 ，石强2，3 ，曾文1 ，赵巍2，3，5 ，赵庆军 2，3，4，5.ATR发动机环形富燃燃气发生器燃烧特性数值模拟[J].航空发动机,2025,51(6):59-68 |
| ATR发动机环形富燃燃气发生器燃烧特性数值模拟 |
| Numerical Simulation of Combustion Performance of an ATR Engine Annular Fuel-Rich Gas Generator |
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| DOI： |
| 中文关键词: 环形富燃燃气发生器 空气涡轮火箭发动机 局部流量 局部混合比 温度分布 燃烧效率 燃烧喷嘴 |
| 英文关键词:annular fuel-rich combustion gas generator air turbo rocket(ATR)engine local mass flow rates local mixing ratios temperature distribution combustion efficiency combustion nozzle |
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| 摘要点击次数: 2007 |
| 全文下载次数: 422 |
| 中文摘要: |
| 为实现空气涡轮火箭（ATR）发动机富燃燃气发生器与涡轮部件的最佳气动匹配，环形富燃燃气发生器是必然的发展趋
势。以ATR发动机液氧/煤油环形富燃燃气发生器为研究对象，通过数值模拟方法分别探究环形截面下不同局部流量和局部混合
比对燃烧特性的影响。结果表明：在保证喷嘴总混合比不变、增大中心燃烧喷嘴流量（或减小边区燃烧喷嘴流量）时，喷嘴下游的
高温区主要沿流向增长；在不同状态下， “倒锥形”低温射流区变化不大；在中心燃烧喷嘴混合比为0.8，边区喷嘴混合比为0.5不变
的条件下，当中心燃烧喷嘴混合比略高于边区燃烧喷嘴混合比时，燃烧效率达到极值83.94%；在保证喷嘴总流量不变，提高中心
燃烧喷嘴混合比（或降低边区燃烧喷嘴混合比）时，喷嘴下游的高温区主要沿流向和径向增长； “倒锥形”低温射流区随着燃烧喷嘴
混合比的提高沿流向逐渐增大；在中心单元喷嘴流量为0.108 kg/s，边区单元喷嘴流量为0.144 kg/s不变的条件下，当中心燃烧喷嘴
流量略大于边区燃烧喷嘴流量时，燃烧效率达到极值83.37%。 |
| 英文摘要: |
| To achieve the best aerodynamic match between the rich combustion gas generator and the turbine components of an air
turbo rocket(ATR)engine,an annular fuel-rich gas generator is an inevitable development trend.Taking a liquid oxygen/ RP-3 annular fuel-
rich gas generator for ATR engines as the research object,the effects of different local mass flow rates and local mixing ratios on combustion
performance under the annular cross section were investigated by numerical simulation.The results show that when the total mixing ratio of
the nozzles remains unchanged,increasing the mass flow rate of the central combustion nozzles(or decreasing the mass flow rate of the side
combustion nozzles)causes the high-temperature region downstream of the nozzle to primarily expand along the flow direction. Under differ?
ent conditions,the low-temperature jet zone with the shape of an "inverted cone" changes little;Under the constant condition that the mixing
ratio of the central combustion nozzle is 0.8 and that of the side nozzle is 0.5,the combustion efficiency reaches an extreme value of 83.94%
when the central combustion nozzle mixing ratio is slightly higher than the side nozzle mixing ratio;When the total flow rate of the nozzles
remains unchanged,increasing the mixing ratio of the central combustion nozzles(or decreasing the mixing ratio of the side combustion
nozzles)causes the high-temperature region downstream of the nozzle to expand primarily along the flow direction and radial direction.The
low-temperature jet zone with the shape of an"inverted cone" increases along the flow direction with the increase of combustion nozzle mix?
ing ratio;under the constant condition that the mass flow rate of the central unit nozzles is 0.108 kg/s and that of the side unit nozzles is
0.144 kg/s,the combustion efficiency reaches an extreme value of 83.37% when the mass flow rate of the central combustion nozzles is
slightly higher than that of the side combustion nozzles. |
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