Performance estimation for serpentine nozzle coupled with aero-engine

Xiao Lin Sun, Zhan Xue Wang, Li Zhou, Jing Wei Shi

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

4 Scopus citations

Abstract

In order lo increase the survivability of the fighter aircraft, serpentine nozzles are applied in series of stealth bombers and Unmanned Aerial Vehicles (UAVs) for their predominant performance in suppressing infrered radiation signature (IRS) emitted by engine exhausts. The aim of this paper is to qualitatively study the influences of the serpentine nozzle on the performance of aero-engine. It is commonly known that excessive geometric parameters are included in the double serpentine nozzle design and, as a result, the performance estimation model for serpentine nozzle coupled with aero-engine is established by combining design of experiment (DOE), response surface methodology (RSM) and aero-engine simulation program based on component characters. In coupling model, seven aerodynamic and geometric parameters were involved in the model, e.g. the length-daimeter ratio; the axial length ratio; the offset distance, the exit area and the exit width of the first serpentine paragraph: the exit aspect ratio of the second serpentine paragraph: and nozzle pressure ratio (.YPR), are taken into consideration. Results show that the interaction effects between different parameters are evident for both the thrust coefficient and the flux coefficient; the thrust of the aero-engine coupling with the serpentine nozzle reduces 0.85%-1.81%, and the specific fuel consumption (SFC) increases 1.43%-1.92% as compared to the aero-engine coupling with the axisvmmetric nozzle.

Original languageEnglish
Title of host publication52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104060
DOIs
StatePublished - 2016
Event52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016 - Salt Lake City, United States
Duration: 25 Jul 201627 Jul 2016

Publication series

Name52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016

Conference

Conference52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016
Country/TerritoryUnited States
CitySalt Lake City
Period25/07/1627/07/16

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