喷嘴导叶喉道的主动流体控制

IF 1.9 3区 工程技术 Q3 ENGINEERING, MECHANICAL
Alexander Spens, Jeffrey Bons
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引用次数: 0

摘要

摘要通过实验验证了流体控制变面积涡轮概念的组成部分,该概念利用注入的高压空气有效地减小了涡轮进口的节流面积。初步结果表明,在一定的喷嘴压力比下,节流质量流量与注入质量流量的比值为2.2:1。利用阴影成像技术成功地显示了注射流的穿透和相应的初级流管的减少。在此基础上,构建了具有代表性的单通道喷管导叶跨声速流道,以验证超越准一维聚散喷管的可行性。叶片压力面和叶片吸力面在通道喉部上游的二次槽吹气再次成功地降低了一次流量。此外,在相邻吸力面上采用了流体涡发生器,以减小总压损失,进一步节流一次流。本文还讨论了这种主动流动控制技术在变面积涡轮中的应用。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Active Fluidic Control of a Nozzle Guide Vane Throat
Abstract Experiments were conducted to validate the building blocks of a fluidically controlled variable area turbine concept that uses injected high-pressure air to effectively reduce the choke area of the turbine inlet. Preliminary results from a simple quasi-1D converging-diverging nozzle, with an injection flow slot upstream of the throat, showed a 2.2:1 ratio between throttled mass flowrate and injected mass flowrate at a constant nozzle pressure ratio. The penetration of the injection flow and corresponding reduction in the primary flow streamtube were successfully visualized using a shadowgraph technique. Building on this success, a representative single passage nozzle guide vane transonic flowpath was constructed to demonstrate feasibility beyond the quasi-1D converging-diverging nozzle. Both secondary slot blowing from the vane pressure surface and vane suction surface just upstream of the passage throat again successfully reduced primary flow. In addition, fluidic vortex generators were used on the adjacent suction surface to reduce total pressure loss and further throttle the primary flow. Implications for the application of this active flow control technology to a variable area turbine are considered.
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来源期刊
CiteScore
4.70
自引率
11.80%
发文量
168
审稿时长
9 months
期刊介绍: The Journal of Turbomachinery publishes archival-quality, peer-reviewed technical papers that advance the state-of-the-art of turbomachinery technology related to gas turbine engines. The broad scope of the subject matter includes the fluid dynamics, heat transfer, and aeromechanics technology associated with the design, analysis, modeling, testing, and performance of turbomachinery. Emphasis is placed on gas-path technologies associated with axial compressors, centrifugal compressors, and turbines. Topics: Aerodynamic design, analysis, and test of compressor and turbine blading; Compressor stall, surge, and operability issues; Heat transfer phenomena and film cooling design, analysis, and testing in turbines; Aeromechanical instabilities; Computational fluid dynamics (CFD) applied to turbomachinery, boundary layer development, measurement techniques, and cavity and leaking flows.
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