The high specific heat of hydrogen compared with air leads to turbine stages which have low pressure ratios for comparable levels of specific work. In high speed propulsion systems designed for reusable space launch vehicles, the choice of scantlings is influenced by the need to minimize weight consistent with the achievement of the required efficiency. The effect of unit increase of mass in a component is, typically, to increase the takeoff weight by approximately five units, and efficiencies significantly lower than those of normal aero-gas turbine practice are adopted. A multi-stage turbine design with overall pressure ratio of 7.6 and overall loading delta H/ u squared = 31.4 is described. A parametric study covering a range of mean diameters and number of stages was performed, in which the aim was to establish the trends of efficiency against weight. The final design has ten stages with a common hub diameter.
Design Considerations of a High Expansion Ratio Hydrogen Turbine
1990
8 pages
Report
No indication
English
Aircraft , Manned Spacecraft , Rocket Engines & Motors , Hydrogen , Propulsion system configurations , Reusable spacecraft , Turbines , Propulsion system performance , Spacecraft launching , Takeoff , High speed , Launch vehicles , Low pressure , Pressure ratio , Selection , Specific heat , Trends , Foreign technology
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