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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Empirical equations were derived to establish the appropriate heat transfer coefficients as functions of the temperature drops and heat transfer rates for a wide range of convective and boiling conditions at different locations in a liquid hydrogen turbopump.
Engineering criteria for thermodynamic improvenent of liquid hydrogen turbopumps for rocket engines
Pressure rise response of turbopumps to flucturating flow rates and unsteady flow about two dimensional linear cascade of airfoils
Thermodynamic improvements in liquid hydrogen turbopumps
Low speed characteristics of liquid hydrogen centrifugal turbopumps
Suction pressure feed systems performance testing for predictive computer program on twin-spool turbopump
Modified single-shaft turbopump incorporates inducer and main pump, each separately driven at different speeds through coaxial-shaft arrangement. Inducer operates at low speed for low net positive suction pressure, main pump operates at high speed to generate high pressure. This arrangement requires no external control for the inducer.
Cold flow startup test on nuclear rocket engine using radial turbopump
Steady state and dynamic performance prediction methods developed for turbopump self compensating thrust balance systems
Thermal conditioning problems of liquid hydrogen turbopumps to enhance mixed-phase operation and to minimize engine system constraints on starts and restarts
Test program to verify theory used in calculating axial thrust uses turbopump instrumented with /a/ proximity transducers for measuring shaft position, /b/ a strain gage thrust bearing carrier to measure axial thrust, and /c/ internal pressure taps to define component pressure gradients used in thrust calculations.
Low cost turbopump design and development
Low cost design study for turbopump concepts
Bearing requirements for liquid rocket engine turbopumps
Saturated LH-2 turbopump operation and feasibility of zero-tank NPSH mode for use with J-2 engines
Design criteria for liquid rocket engine turbopump inducers
System for cooling turbopumps used in cryogenic fluid storage facilities is described. Technique uses thermodynamic propellant vent to intercept pump heat at desired conditions. Cooling system uses hydrogen from outside source or residual hydrogen from cryogenic storage tank.
State of the art and design criteria for liquid rocket engine turbopump inducers are summarized for optimal fabrication. Design criteria optimize hydrodynamic parameters to obtain highest suction specific speed without violating structural and mechanical constraints.