Parametric Study of an Expander Bleed Engine Performance

Aerotecnica Missili & Spazio

View Publication Info
 
 
Field Value
 
Title Parametric Study of an Expander Bleed Engine Performance
 
Creator Leonardi, Marco
Di Matteo, Francesco
Nasuti, Francesco
 
Subject Aerospace Propulsion
Rocket engine, System analysis, Pump-fed systems, Regenerative cooling
Liquid rocket engine system analysis
 
Description Expander bleed cycles have a rather simple configuration when compared to other engine cycles, making them appealing when a new low-thrust engine must be designed. This type of cycles can only operate with light fuels (H2, CH4, C3H8) that can be pumped in the liquid state and then properly expanded as a gas in the turbines. As a consequence of the limited amount of power provided by the cooling, expander cycles are characterised by a maximum size of engine thrust of about 250 kN. The present study is focussed on the analysis of a liquid oxygen/liquid hydrogen bleed engine cycle, with a thrust comprised between 110-150 kN and dedicated to upper stage applications. We carry out a basic selection of all the key parameters defining the engine and its subsystems to obtain a specific configuration able to work at a prescribed working point. Starting from this configuration, we perform parametric analyses aimed at and select the key design parameters optimise engine performance.
 
Publisher Associazione Italiana di Aeronautica e Astronautica (AIDAA)
 
Contributor European Space Agency (ESA/ESTEC)
 
Date 2017-09-19
 
Type info:eu-repo/semantics/article
info:eu-repo/semantics/publishedVersion
Peer-reviewed Article
Simulation
 
Format application/pdf
 
Identifier http://131.114.27.37/index.php/AMS/article/view/275
10.19249/ams.v96i1.275
 
Source Aerotecnica Missili & Spazio; Vol 96, No 1 (2017); 32-43
0365-7442
 
Language eng
 
Relation http://131.114.27.37/index.php/AMS/article/view/275/pdf
 
Rights Copyright (c) 2017 Aerotecnica Missili & Spazio
 

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