Investigation of a Radial Turbines Compatibility for Small Rocket Engine
In the radial turbine preliminary design for an expander rocket engine, a comparison was made with axial turbine used in Pratt & Whitney RL10 engine. One of the primary requirements of a liquid propellant rocket engine is the generation of a high thrust, which depends on both the mass flow rate...
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EDP Sciences
2020-01-01
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| Series: | E3S Web of Conferences |
| Online Access: | https://www.e3s-conferences.org/articles/e3sconf/pdf/2020/57/e3sconf_ati2020_11009.pdf |
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doaj-8e1805fa04914bbdb45b0b61c6dc55892021-04-02T17:17:33ZengEDP SciencesE3S Web of Conferences2267-12422020-01-011971100910.1051/e3sconf/202019711009e3sconf_ati2020_11009Investigation of a Radial Turbines Compatibility for Small Rocket EngineLeto AngeloIn the radial turbine preliminary design for an expander rocket engine, a comparison was made with axial turbine used in Pratt & Whitney RL10 engine. One of the primary requirements of a liquid propellant rocket engine is the generation of a high thrust, which depends on both the mass flow rate of the propellant and the pressure in the thrust chamber. In expander-cycle engines, which are the subject of the present study, the liquid propellant is first compressed using centrifugal turbo-pumps, then it is used to cool the combustion chamber and the nozzle and, once vaporized, it flows through the turbines used to drive the turbo-pumps. The aim was to demonstrate the greater efficiency of the radial turbine with a reduction of the pressure ratio with respect to the axial turbine.https://www.e3s-conferences.org/articles/e3sconf/pdf/2020/57/e3sconf_ati2020_11009.pdf |
| collection |
DOAJ |
| language |
English |
| format |
Article |
| sources |
DOAJ |
| author |
Leto Angelo |
| spellingShingle |
Leto Angelo Investigation of a Radial Turbines Compatibility for Small Rocket Engine E3S Web of Conferences |
| author_facet |
Leto Angelo |
| author_sort |
Leto Angelo |
| title |
Investigation of a Radial Turbines Compatibility for Small Rocket Engine |
| title_short |
Investigation of a Radial Turbines Compatibility for Small Rocket Engine |
| title_full |
Investigation of a Radial Turbines Compatibility for Small Rocket Engine |
| title_fullStr |
Investigation of a Radial Turbines Compatibility for Small Rocket Engine |
| title_full_unstemmed |
Investigation of a Radial Turbines Compatibility for Small Rocket Engine |
| title_sort |
investigation of a radial turbines compatibility for small rocket engine |
| publisher |
EDP Sciences |
| series |
E3S Web of Conferences |
| issn |
2267-1242 |
| publishDate |
2020-01-01 |
| description |
In the radial turbine preliminary design for an expander rocket engine, a comparison was made with axial turbine used in Pratt & Whitney RL10 engine.
One of the primary requirements of a liquid propellant rocket engine is the generation of a high thrust, which depends on both the mass flow rate of the propellant and the pressure in the thrust chamber.
In expander-cycle engines, which are the subject of the present study, the liquid propellant is first compressed using centrifugal turbo-pumps, then it is used to cool the combustion chamber and the nozzle and, once vaporized, it flows through the turbines used to drive the turbo-pumps.
The aim was to demonstrate the greater efficiency of the radial turbine with a reduction of the pressure ratio with respect to the axial turbine. |
| url |
https://www.e3s-conferences.org/articles/e3sconf/pdf/2020/57/e3sconf_ati2020_11009.pdf |
| work_keys_str_mv |
AT letoangelo investigationofaradialturbinescompatibilityforsmallrocketengine |
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