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PREDICTION AND ANALYSIS OF INLET PRESSURE AND TEMPERATURE DISTORTION ON ENGINE OPERABILITY FROM A RECENT T-38 FLIGHT TEST PROGRAM

机译：最近的T-38飞行测试程序对发动机可操作性的入口压力和温度变形的预测和分析

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Since the initial development of the T-38 Talon trainer, therehave been upgrades to both the aircraft and to the J85-GE-5afterburning turbojet engine to improve takeoff performance,reduce maintenance time and cost, and to decrease fuelconsumption. The latest upgrades, referred to as thePropulsion Modernization Program (PMP), focused on improvedperformance of the T-38's inlets, twin J85-GE-5 afterburningturbojet engines, and improved exhaust nozzle design. The T-38's inlet includes bleed holes upstream of the engine face toprovide cooling air flow from the inlet to the engine bay.However, at various locations in the flight envelope, the bay airis pressurized relative to the inlet resulting in reverse flow of hotengine bay air into the inlet. This reverse flow along with inletheat transfer effects can cause total temperature distortion andreduce engine stability margin. During any flight maneuvers,there will be an associated level of total pressure distortion.When pressure distortion is combined with the temperaturedistortion due to engine bay flow reversal and inlet heat transfer,losses in stability pressure ratio (or stability margin) may furtherbe increased. This analysis effort reported herein uses amodeling and simulation technique known as the parallelcompressor theory (model) to investigate the effects of total c. „ Tu ., .. _ _ _„ ,. ,pressure and temperature Net distortion on system operability Fl9ure 1" The NorthroP Gruj"man T-38, Talon,and makes predictions of the loss in stability pressure ratio Trainer [3]associated with those combined pressure and temperaturedistortions during flight maneuvers.
机译：自从T-38 Talon教练机最初开发以来， 已经对飞机和J85-GE-5进行了升级 加力涡轮喷气发动机以提高起飞性能， 减少维护时间和成本，并减少燃料 消耗。最新升级，称为 推进现代化计划（PMP），着重于改进 T-38进气口的性能，双J85-GE-5加力燃烧 涡轮喷气发动机，并改进了排气喷嘴设计。 T- 38的进气口包括在发动机端面上游的放气孔，用于 提供从进气口到发动机舱的冷却空气流。 但是，在飞行包线的各个位置， 相对于进口被加压导致热的逆流 发动机舱空气进入进气口。这种逆流与入口一起 传热效应可能会导致总温度失真，并且 降低发动机稳定性裕度。在任何飞行演习中， 总压力畸变将有一个相关的水平。 当压力变形与温度结合在一起时 由于发动机舱气流逆流和进气口传热而导致的变形， 稳定压力比（或稳定裕度）的损失可能会进一步增加 增加。本文报告的分析工作使用了 建模和仿真技术被称为并行 压缩机理论（模型）研究总c的影响。 „ Tu。，.. _ _ _„，。 ， 压力和温度净变形对系统的可操作性Fl9ure 1“ The NorthroP Gruj” man T-38，Talon， 并预测稳定压力比Trainer的损失[3] 与那些压力和温度相结合的 飞行演习中的变形。

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