旋翼/涡轴发动机动力涡轮联合变转速对性能影响研究

伊卫林; 崔志伟; 郑霆锴

doi:10.13224/j.cnki.jasp.20220077

旋翼/涡轴发动机动力涡轮联合变转速对性能影响研究

doi: 10.13224/j.cnki.jasp.20220077

北京理工大学机械与车辆学院，北京 100081

基金项目: 国家自然科学基金（52176035）

详细信息

作者简介:
伊卫林（1978-），男，副教授、博士生导师，博士，主要从事航空发动机总体及叶轮机械气动热力学方面的研究

中图分类号: V212.5
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出版历程
- 收稿日期: 2022-02-22
- 网络出版日期: 2024-04-10

Effect investigation of combined variable speed of rotor/turboshaft engine power turbine on the performance

School of Mechanical Engineering，Beijing Institute of Technology，Beijing 100081，China

摘要

摘要:
分别建立了考虑飞行工况条件的旋翼最优转速及功率需求计算模型、动力涡轮可变速的涡轴发动机性能分析模型，以此发展了旋翼/涡轴发动机转速联合优化分析方法及程序，并以UH60A直升机及T700涡轴发动机为对象进行了典型飞行包线下的性能分析。结果表明：动力涡轮转速可变后压气机、高压涡轮稳态匹配工作线变化不大，但动力涡轮自身等熵效率随转速降低有明显下降，其性能需进一步提升。与定转速运行模式相比，完成典型飞行任务后，旋翼/涡轴发动机协同变速运行可使得总耗油量明显降低约5%。
- 旋翼 /
- 动力涡轮 /
- 涡轴发动机 /
- 变转速 /
- 耗油量
Abstract:
The calculation model of optimal rotor speed and power demand considering flight conditions and the performance analysis model of turboshaft engine with variable speed power turbine were built respectively. Based on these models, the performance analysis method and program of rotor /turboshaft engine power turbine were developed, and the performance analysis under typical flight envelope was carried out for UH60A helicopter and T700 turboshaft engine. The results showed that when the speed of power turbine becames variable, the steady-state matching working line of compressor and high-pressure turbine changed slightly. However, the isentropic efficiency of the power turbine decreased significantly as the speed decreased, indicating that further improvements in its performance were necessary. Compared with the constant speed operation mode, after a completion of a typical flight mission, the coordinated variable speed operation of rotor /turboshaft engine could reduce fuel consumption by nearly 5%.
- rotor /
- power turbine /
- turboshaft engine /
- variable speed /
- fuel consumption

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图 1 联合仿真计算流程图

Figure 1. Flowchart of co-simulation calculation

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图 2 前进比与叶片载荷系数的关系^[20]

Figure 2. Relation between advance ratio and blade loading^[20]

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图 3 最佳旋翼转速和飞行速度的关系（200 m）

Figure 3. Relationship between optimal rotor speed and flight speed （200 m）

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图 4 T700发动机模型

Figure 4. T700 engine model

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图 5 仿真结果与试验数据对比

Figure 5. Simulation results are compared with the experimental data

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图 6 旋翼-变速箱-发动机联合仿真模型

Figure 6. Rotor-transmission-engine co-simulation model

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图 7 旋翼最优转速与需求功率关系

Figure 7. Relationship between optimal rotor speed and power demand

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图 8 转速变化对总耗油量的影响

Figure 8. Effect of speed change on total fuel consumption

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图 9 各工况转速变化对动力涡轮性能的影响

Figure 9. Effect of speed variation on power turbine performance under different working conditions

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图 10 各工况转速变化对压气机性能的影响

Figure 10. Effect of speed variation on compressor performance under different working conditions

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图 11 各工况转速变化对高压涡轮性能的影响

Figure 11. Effect of speed variation on high pressure turbine performance under different working conditions

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表 1 UH-60A黑鹰直升机参数^[7]

Table 1. UH-60A black hawk helicopter parameters^[7]

参数类型及单位	数值
主旋翼半径R/m	8.178
尾翼半径R_tr /m	1.676
主旋翼翼弦/m	0.5273
尾翼翼弦/m	0.2469
主旋翼叶片数	4
尾翼叶片数	4
等效平板面积比（f/A）	0.016
平均叶片截面阻力系数C_d0	0.012
主旋翼与尾翼距离L/m	9.93
主旋翼常规转速ω/（rad/s）	27
尾翼与主旋翼速比α	4.6
直升机质量W/N	71168
飞行速度范围V/（m/s）	0/90
旋翼实度σ（叶片实际面积/盘面积）	0.082

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表 2 发动机模型设计参数^[7]

Table 2. Engine model design parameters^[7]

模型设计参数	数值
空气流量/（kg/s）	4.612
进气总压恢复系数	0.988
压气机压比	17.5
压气机效率	0.821
压气机/高压涡轮转速/（r/min）	44700
燃烧室总压损失	0.04
燃烧室效率	0.985
燃油流量/（kg/s）	0.101
高压涡轮效率	0.85
高压涡轮落压比	4.283
动力涡轮设计转速/（r/min）	20900
动力涡轮效率	0.85
动力涡轮落压比	3.3897

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表 3 设计点计算参数

Table 3. Design point calculation parameters

设计点	S2	S3	S4	S5	S6	S7
焓值/（kJ/kg）	288.18	735.31	1624.71	1187.10	903.80	903.80
总温/K	288.17	721.11	1454.44	1098.33	857.22	857.22
总压/Pa	100010	1764400	1694000	395300	116000	114400
动力涡轮输出功率/kW	1343
耗油率SFC/（kg/kWh）	0.2708
总热效率	0.3084

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表 4 UH-60A飞行任务参数

Table 4. UH-60A mission parameters

任务区间	飞行距离/时间/（km/s）	海拔高度/m
起飞爬升	0/10	0～100
加速（0～90 m/s）	0.6/13.5	100
前飞和爬升	9.5/107	100～1500
巡航（84 m/s）	100/1190	1500
前飞和爬升	5/62	1500～3000
巡航（70 m/s）	314/4490	3000
前飞和下降	20/578	3000～10
悬停	0/300	10
降落	0/10	10～0
总计	449.1 km/6760.5 s

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