北京航空航天大学 能源与动力工程学院,北京,100191
纸质出版:2012
移动端阅览
解亚东, 单鹏. 小流量多级高负荷轴流压气机设计[J]. 航空动力学报, 2012,27(9).
XIE Ya-dong, SHAN Peng. Design research of small flow rate multi-stage high-loaded axial compressor[J]. 2012, 27(9).
解亚东, 单鹏. 小流量多级高负荷轴流压气机设计[J]. 航空动力学报, 2012,27(9). DOI:
XIE Ya-dong, SHAN Peng. Design research of small flow rate multi-stage high-loaded axial compressor[J]. 2012, 27(9). DOI:
以增压比为6的国外某小流量5级轴流压气机为设计原型
在不超过其前3级的轴向长度的条件下
设计了3级轴流压气机
研究其最大增压能力.在采用了正预旋、静子端弯、第2、3级转子叶尖适度斜流等措施后
3级轴流的设计点流量为5.80kg/s
增压比为5.445
效率为0.8272
喘振裕度为11.8%
3级平均级增压比为1.759.研究结果表明:在一定的轴向长度限制下
小流量3级轴流压气机虽可以达到5.5量级的增压比
但其流量特性曲线已经变得很陡峭.
The pressure ratio of a five stage foreign compressor with small flow rate is 6.On condition that not exceeding its pre three stage axial length
a three stage compressor was designed and its maximum pressurizing ability was researched.By using positive pre-whirl
end-bend stator and the measure that properly boosted the shroud of the second and third stages
the design result of this three stage compressor was that the mass flow rate was 5.80kg/s
pressure ratio was 5.445
efficiency was 0.8272
surge margin was 11.8%
and average stage pressure ratio was 1.759.On condition that not exceeding the limit of a certain axial length
the small flow three stages got the pressure level of 5.5.The flow characteristic curve has been cliffy.
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