Performance Trends for a Product Scale Pulse Detonation Engine
Performance Trends for a Product Scale Pulse Detonation Engine
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DOI：
10.2514/6.2004-3402
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发表时间：
2004-07
期刊：
影响因子：
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通讯作者：
S. Anderson;J. Tonouchi;G. Lidstone;K. Lupkes;F. Alfonso
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文献类型：
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作者：
S. Anderson;J. Tonouchi;G. Lidstone;K. Lupkes;F. Alfonso
脉冲爆震发动机(PDE)作为一种新的推进技术，在过去的十年里引起了人们的极大兴趣。独特的爆震循环特性为空气呼吸和火箭应用提供了提高效率和简化设计的潜力。然而，在公开文献中提出的PDE性能估计有相当大的差异。此外，严重缺乏可用数据来核实爆炸循环性能潜力，并为分析工具提供验证数据。普惠西雅图航空科学中心(SAC)最近完成了一项由海军研究办公室(ONR)资助的为期三年的技术风险降低计划，该计划的重点是为2.5马赫攻击导弹应用开发PDE。该计划最终测试了一种可飞行跟踪的发动机配置，重点是展示爆炸周期的性能潜力。普拉特和惠特尼还开发了PDE分析工具，以提供测试台硬件和产品配置的性能预测。本文将介绍脉冲爆震发动机的性能分析方法，并将性能预测与五燃烧室综合试验台(ITR-2)的试验数据进行比较。试验数据和分析既包括环境灌装条件(无喷嘴)，也包括背压灌装条件。比较将包括亚音速发射条件和马赫2.5，40,000英尺高度巡航条件。数据包括发动机总体性能参数，如推力和比油耗。
Pulse detonation engines (PDE’s) have gen erated significant interest in the last ten years as a new propulsion technology. Unique detonation cycle characteristics offer the potential for increased efficiency and simplified design in both airbreathing and rocket applications. However, there has been considerable variation in PDE performance estimates presented in the open literature. In addition, there has been a severe lack of available data to verify the detonation cycle performance potential and to provide validation data for analysis tools. Pratt & Whitney Seattle Aerosciences Center (SAC) has recently completed a three -year technology risk reduction program funded by the Office of Naval Research (ONR) that has been focused on the development of a PDE for a Mach 2.5 strike missile applicatio n. The program culminated in the test of a flight -traceable engine configuration focused on demonstrating the performance potential of the detonation cycle. Pratt and Whitney has also developed the PDE analysis tools to provide performance predictions of both the test rig hardware and product configurations. This paper will describe the PDE performance analysis methodology and compare performance predictions with test data from the five combustor Integrated Test Rig (ITR -2). Test data and analysis inclu des both ambient filling conditions (no nozzle) as well as backpressured filling conditions. Comparisons will include both a subsonic launch condition and a Mach 2.5, 40,000 foot altitude cruise condition. Data includes overall engine performance paramet ers such as thrust and specific fuel consumption.