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A study on flow development in an APU-style inlet and its effect on centrifugal compressor performance.

机译：APU型进气道中的流动发展及其对离心压缩机性能的影响的研究。

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摘要

The objectives of this research were to investigate the flow development inside an APU-style inlet and its effect on centrifugal compressor performance. The motivation arises from the increased applications of gas turbine engines installed with APU-style inlets such as unmanned aerial vehicles, auxiliary power units, and helicopters. The inlet swirl distortion created from these complicated inlet systems has become a major performance and operability concern. To improve the integration between the APU-style inlet and gas turbine engines, better understanding of the flow field in the APU-style inlet and its effect on gas turbine is necessary.;A research facility for the purpose of performing an experimental investigation of the flow field inside an APU-style inlet was developed. A subcritical air ejector is used to continuously flow the inlet at desired corrected mass flow rates. The facility is capable of flowing the APU inlet over a wide range of corrected mass flow rate that matches the same Mach numbers as engine operating conditions. Additionally, improvement in the system operational steadiness was achieved by tuning the pressure controller using a PID control method and utilizing multi-layer screens downstream of the APU inlet. Less than 1% relative unsteadiness was achieved for full range operation.;The flow field inside the rectangular-sectioned 90? bend of the APU-style inlet was measured using a 3-Component LDV system. The structures for both primary flow and the secondary flow inside the bend were resolved. Additionally, the effect of upstream geometry on the flow development in the downstream bend was also investigated.;Furthermore, a Single Stage Centrifugal Compressor research facility was developed at Purdue University in collaboration with Honeywell to operate the APU-style inlet at engine conditions with a compressor. To operate the facility, extensive infrastructure for facility health monitoring and performance control (including lubrication systems, secondary air systems, a throttle system, and different inlet configurations) were built. Additionally, three Labview programs were developed for acquiring the compressor health monitoring, steady and unsteady pressure and strain data.;The baseline, steady aerodynamic performance map was established. Additionally, the unsteady pressure field in the compressor was investigated. Steady performance data have been acquired from choke to near surge at three different corrected speeds from 90% to 100% corrected speed in 5% increments. The performance of the compressor stage was characterized using total pressure ratio (TPR), total temperature ratio (TTR), and isentropic efficiency. The impeller alone and diffuser along performance were also investigated, and the high loss regions in the compressor were identified.;At last, the compressor unsteady shroud pressure was investigated at 100% corrected speed in both the time domain and frequency domain. Results show strong pressure components in relation to the shaft frequency (SF). The impeller has 17 main blades and 17 splitter blades, and introduces pressure fluctuations at 17SF and its harmonics. Additionally, the diffuser has a vane count of 25 and results in pressure spectra of 59SF (17+17+25) due to the interactions between the impeller and diffuser.
机译：这项研究的目的是研究APU型进气口内部的流动发展及其对离心压缩机性能的影响。动力来自安装有APU型进气口的燃气涡轮发动机的增加应用，例如无人驾驶飞机，辅助动力装置和直升机。由这些复杂的进气系统产生的进气涡流畸变已成为主要的性能和可操作性问题。为了提高APU型进气门与燃气轮机发动机之间的集成度，有必要更好地了解APU型进气门的流场及其对燃气轮机的影响。开发了APU型进样口内部的流场。亚临界空气喷射器用于使入口以期望的校正质量流率连续流动。该设备能够使APU进气口在更宽的校正质量流率范围内流动，该质量流率匹配与发动机工况相同的马赫数。此外，通过使用PID控制方法调整压力控制器并利用APU入口下游的多层滤网，可以改善系统的运行稳定性。对于全范围操作，相对不稳定度小于1％。；矩形截面90？内的流场。使用3组分LDV系统测量APU型进样口的弯曲度。解决了弯头内一次流动和二次流动的结构。此外，还研究了上游几何形状对下游弯道中流动发展的影响。此外，普渡大学与霍尼韦尔（中国）合作开发了单级离心压缩机研究设施，以在发动机工况下以APU式进气道运行。压缩机。为了运营该设施，建立了用于设施健康监测和性能控制的广泛基础设施（包括润滑系统，二次空气系统，节气门系统和不同的进气口配置）。此外，还开发了三个Labview程序来获取压缩机运行状况监控，稳态和非稳态压力和应变数据。;建立了基线，稳态空气动力性能图。此外，还研究了压缩机中的非稳态压力场。在从90％到100％校正速度（以5％为增量）的三种不同校正速度下，已获得了从扼流圈到接近喘振的稳定性能数据。使用总压力比（TPR），总温度比（TTR）和等熵效率来表征压缩机级的性能。还研究了单独的叶轮和扩压器的性能，并确定了压缩机中的高损耗区域。最后，在时域和频域中以100％校正速度研究了压缩机的非定常罩压。结果显示出与轴频率（SF）相关的强压力分量。叶轮有17个主叶片和17个分流叶片，并在17SF及其谐波处引入压力波动。此外，由于叶轮和扩散器之间的相互作用，扩散器的叶片数为25，压力谱为59SF（17 + 17 + 25）。

著录项

  • 作者

    Lou, Fangyuan.;

  • 作者单位

    Purdue University.;

  • 授予单位 Purdue University.;
  • 学科 Mechanical engineering.;Aerospace engineering.
  • 学位 Ph.D.
  • 年度 2016
  • 页码 230 p.
  • 总页数 230
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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