NASA Technical Reports Server (NTRS) 19930017748: SNTP propellant management system PDF
Preview NASA Technical Reports Server (NTRS) 19930017748: SNTP propellant management system
SNTP Propellant Management System Current SNTP Engine System Uses High Temperature Bleed Cycle Tank Shut-off Valve Boost Pump Ejector Turbopump Assembly Pump Discharge - Turbine Control Valve Shutoff Valve Hydrogen Flowmeter Presented by: Tom Tippetts Allied S~g~~ili SNTP Cycle Selection Full-Temperature Bleed Cycle is Lowest Engine System Mass with-Minimal Isp Penalty \ No design interaction with reactor IOCAL SPECIFIC IMPULY 4 NOZZLEISTRUG~UFIF I EXPANDER Allows light-weight radiation- CYCLE cooled nozzle Lowest system complexity, potentially highest system reliability High-temperature, low-Z material minimize cooling in radiation I I environments TURBINE INLET TEMPERATUnE dinniintd4 Fan NTP: Technology s34 NTP System Components Have Unique Design Constraints High Ionizing Radiation Environment e High Heat Load From Radiation Energy Absorption Restricts Use Of High-Z Materials Design Must Provide For Heat Removal ,e@; Bleed Cycle Presents Unique Design Requirements for Turbopump . M.o derate operating pressures (13 50 psi) Single-stage pump Light pressure vessels . High operating temperatures (2750 K) . Highly energetic working fluid High-pressure ratio impulse turbine High turbine temperatures Large thermal gradients Environmental factors Environmental heating - low -2 material Limited elastomers selection Hot-hydrogen embrittlement Use of bleed cycle and uncooled thrust nozzle results in substantial system weight savings. NP-TIM-92 I”,,”.. 535 NW:T echnology Ir,,7c. Bleed-Cycle Turbopump Uses Carbon-Carbon Components for Operation on 2750 K Gas Carbon-Carbon Carbon-Carbon Hot Section Nozzle/Plcnum Housing Aluminum Carbon-Carbon Pump and Turbines Inducer Titanium Ceramic Rolling Shafting Element Bearings or Foil Bearings 1112712 SNTP Carbon-Carbon Turbine Wheel Design is Based on Technology Developed on the ELITE Program 0 Helical 2-D polar weave architecture Impulse blades 55,600 rpm 2750 K inlet temperature 45-percent design stress margin 26-percent design speed maruin ~, ,# J’-’IlM-92 Turbine Development Program High- Temperature, Carbon-C arbon Components Are Being Fabricated and Will be Tested at 2 750 K I) Turbopump High-Temperature Hot-Turbine Preliminary I) Ccmponent Design Spin Rig Design and Fabrication Test (HTSR) San Tan Hydrogen Test Facility Facility Constructed for Development of SN TP H ydrogen-Relat ed Components Turbopump, valves, internal reactor components Hot, two-phase, and cryogenic hydrogen capability Dedicated facility for non- nuclear NTP testing Company- funded construction NI'-'I?M 02 l'",,* I 537 N'IY. 'l'echnology" '"*'
The list of books you might like
