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Infra-red signature reduction study on a small-scale jet engine

Published online by Cambridge University Press:  03 February 2016

J. Dix ,
A.J. Saddington ,
K. Knowles  and
M.A. Richardson
J. Dix
Affiliation:
Department of Aerospace, Power and Sensors, Cranfield University, RMCS, Shrivenham, Swindon, UK
A.J. Saddington
Affiliation:
Department of Aerospace, Power and Sensors, Cranfield University, RMCS, Shrivenham, Swindon, UK
K. Knowles
Affiliation:
Department of Aerospace, Power and Sensors, Cranfield University, RMCS, Shrivenham, Swindon, UK
M.A. Richardson
Affiliation:
Department of Aerospace, Power and Sensors, Cranfield University, RMCS, Shrivenham, Swindon, UK
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Abstract

This paper presents infra-red signature data for a small-scale, low pressure ratio turbojet engine typical of that used in unmanned air vehicle applications. The aim of the study was to test a number of different convergent nozzle designs concentrating on those with trailing edge modifications. The engine used in the tests has a single stage centrifugal compressor and radial inflow turbine and is designed to produce approximately 150N of thrust at 103,500rpm using liquid propane fuel. The test rig consisted of a calibrated thrust stand whilst the engine was controlled through an electronic engine control unit and laptop PC. The jet plume was visualised using an infra-red spectroradiometer which yielded qualitative data across the infra-red spectrum. Simultaneous measurements were also made of the engine thrust. A Pitot probe was used to take pressure readings across different sections of the exhaust flow. Analysis of the infrared signature of the engine exhaust plume and any thrust penalty yielded a performance comparison for each of the nozzles tested. Correlation of engine thrust with engine rpm showed that, within the accuracy of the measurements, there was no significant thrust penalty associated with the notched nozzles. Infra-red imagery of the plain and 60° notched nozzles indicated that the latter reduced the length of the hottest part of the exhaust plume by approximately 33%. The spectroradiometer data shows a significant reduction in spectral radiance for the CO2 wavelength of approximately 4·3µm when the notched nozzles are used. The 60° notched nozzle appeared to perform best in reducing the spectral radiance at this wavelength. Centreline total pressure measurements in the exhaust plume correlated well with the infra-red imagery in that a potential core length reduction of up to 30% could be achieved using the 60° notched nozzle. Total pressure contours recorded 20mm (0·43D) downstream of the nozzle exit plane suggest that the notched nozzles are promoting increased mixing through radial spreading of the jet possibly associated with increased streamwise vorticity (although the latter could not be confirmed). There were also signs that the jet plumes being investigated were swirling.

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1092 , February 2005 , pp. 83 - 88
Copyright
Copyright © Royal Aeronautical Society 2005 

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