Engineering approach of compressor test efficiency correction
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摘要: 效率是评价航空发动机压气机性能的重要指标，通常由试验直接获得。由于试验环境、结构构型和测点损失的影响，试验效率值需要修正后才能作为工程应用中性能评价和整机匹配的依据。本文提出了压气机试验效率的工程修正方法，对不同试验环境中压气机效率的影响因素进行系统分类，给出了雷诺数、进口过渡段损失、温度测量偏差、空气湿度和测试受感部损失等因素的具体修正方法。应用该方法对某10级压气机部件的试验效率进行修正，修正后效率提升了1.85%；对整机环境下压气机试验效率进行修正，修正后效率提升了0.95%。该方法可用于核心机/整机压气机试验效率修正和性能评定中。Abstract: Efficiency is the key parameter for evaluating compressor performance of the aero engine. It is usually acquired by compressor performance tests. Due to the difference in test condition, mechanical configuration, and instrumentation loss, efficiency obtained from compressor rig tests should be corrected for evaluating performance and engine matching in the engineering field. An engineering approach for correcting the compressor efficiency was proposed. The influence factors of the compressor efficiency were classified systematically under different test conditions, and detailed methods of correcting Reynolds number, inlet strut loss, thermo-couple Mach number recovery, air humidity and probe loss were given. Two examples were conducted using this method. The efficiency of a ten-stage compressor component rig test was corrected by 1.85 percent improvement. Besides, in the engine test, the compressor efficiency was corrected by 0.95 percent improvement. This method can be applied in the engineering field of efficiency measurement correction and performance evaluation for core and whole engines.
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Key words:
- aero engine /
- compressor /
- efficiency test /
- engineering approach
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图 2 不同进口节流比的压气机特性图
Figure 2. Speed lines of the compressor with different inlet throttle ratio
图 4 进口测量截面探针周向和径向位置分布图
Figure 4. Circumferential and radial distribution of the probes at inlet measurement section
图 5 工作点压比和效率修正
Figure 5. Correction of total pressure ratio and efficiency at work point
图 6 考虑过渡段端壁边界层总压恢复系数
Figure 6. Total pressure recovery coefficient due to endwall boundary layer
图 7 各转速工作点压比和效率的修正量
Figure 7. Correction of total pressure ratio and efficiency at different speed
表 1 测量参数最大允许误差
Table 1. Maximum error of measurement parameters
Parameters Maximum error ${T}_{ {{\rm{in}} } }^{*}$ ±1.0 K ${T}_{ {{\rm{ex}}} }^{*}$ ±2.0 K ${P}_{ {{\rm{in}}} }^{*}$ ±0.2% Pa ${P}_{ {{\rm{ex}}} }^{*}$ ±0.2% Pa 
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表 2 过渡段总压损失系数
Table 2. Total pressure recovery coefficient of intermediate casing
Corrected speed Total pressure recovery coefficient Test 1 Test 2 100%
(Work point)0.9938 0.9912 100%
(Near surge point)0.9939 0.9916 80%
(Work point)0.9993 0.9924 80%
（Near surge point）0.9994 0.9930
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表 3 总温修正结果
Table 3. Result of total temperature correction
Parameters Value Inlet Mach number 0.45 Outlet Mach number 0.25 Correction of inlet total temperature 0.70 K Correction of outlet total temperature 0.59 K Correction of efficiency 0.21%
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表 4 某10级压气机性能试验效率修正
Table 4. Correction of ten-stage compressor testing efficiency
Correction term Value Reynolds number 0.50% Strut loss 0.44% Temperature error 0.21% Air humidity −0.20% Probe loss 0.90% Total 1.85%
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表 5 发动机整机试验压气机效率修正
Table 5. Correction of compressor efficiency in whole engine test
Correction term Value Strut loss 0.50% Temperature error 0.25% Air humidity −0.20% Probe loss 0.40% Total 0.95%
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