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...

Full description

Saved in:
Bibliographic Details
Published inE3S web of conferences Vol. 197; p. 11009
Main Author Leto, Angelo
Format Journal Article Conference Proceeding
LanguageEnglish
Published Les Ulis EDP Sciences 01.01.2020
Subjects
Combustion chambers
Design
Efficiency
Engines
Flow rates
Flow velocity
High thrust
Liquid propellant rocket engines
Liquid propellants
Mass flow rate
Preliminary designs
Pressure ratio
Pumps
Rockets
Thrust chambers
Turbine pumps
Turbines
Online AccessGet full text

Cover

More Information
Summary: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.
Bibliography:ObjectType-Conference Proceeding-1
SourceType-Conference Papers & Proceedings-1
content type line 21
ISSN:2267-1242
2555-0403
2267-1242
DOI:10.1051/e3sconf/202019711009