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
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| Creator |
Leonardi, Marco
Di Matteo, Francesco Nasuti, Francesco |
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| Subject |
Aerospace Propulsion
Rocket engine, System analysis, Pump-fed systems, Regenerative cooling Liquid rocket engine system analysis |
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| 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.
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| Publisher |
Associazione Italiana di Aeronautica e Astronautica (AIDAA)
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| Contributor |
European Space Agency (ESA/ESTEC)
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| Date |
2017-09-19
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| Type |
info:eu-repo/semantics/article
info:eu-repo/semantics/publishedVersion Peer-reviewed Article Simulation |
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| Format |
application/pdf
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| Identifier |
http://131.114.27.37/index.php/AMS/article/view/275
10.19249/ams.v96i1.275 |
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| Source |
Aerotecnica Missili & Spazio; Vol 96, No 1 (2017); 32-43
0365-7442 |
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| Language |
eng
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| Relation |
http://131.114.27.37/index.php/AMS/article/view/275/pdf
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| Rights |
Copyright (c) 2017 Aerotecnica Missili & Spazio
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