MACH 6 NOZZLE (M6N) FOR THE 8-FT HTT AT NASA LANGLEY RESEARCH CENTER. NASA LANGLEY RESEARCH CENTER WILL BE…

Public award description

MACH 6 NOZZLE (M6N) FOR THE 8-FT HTT AT NASA LANGLEY RESEARCH CENTER. NASA LANGLEY RESEARCH CENTER WILL BE PARTICIPATING IN UPCOMING PROJECTS THAT WILL REQUIRE THE 8-FT HIGH TEMPERATURE TUNNEL TO TEST LARGE SCALE PROPULSION GROUND TEST ARTICLES AND FLIGHT VEHICLES IN THE MACH 6 SPEED REGIMES. IN PREPARATION FOR THESE PROJECTS THE FACILITY DETERMINED THAT THE EXISTING MACH 7 TRANSPIRATION COOLED NOZZLE (M7N) WAS PAST ITS DESIGN LIFE CYCLE WHICH POSED POTENTIAL RISKS TO PROGRAMS AND THE FACILITIES SUSTAINABILITY. TO REDUCE THIS RISK AND SAVE LIFE CYCLES ON THE M7N, WHICH WILL BE USED PRIMARILY FOR THERMAL PROTECTION TESTING, THE FACILITY IS PUSHING FORWARD WITH REPLACEMENT EFFORT FOR THE M7N. THE FACILITY HAS STUDIED AND POLED POTENTIAL CUSTOMERS FOR FUTURE DEMANDS AND THE M6 SPEEDS WILL BE THE DOMINATING REQUIREMENT FOR THE FORESEEABLE FUTURE. THE NEW MACH 6 NOZZLE (M6N) WILL BE AN INTEGRAL PART OF THE 8-FT HTT AT NASA LANGLEY RESEARCH CENTER. IT WILL PROVIDE THE EXISTING FACILITY EXPANDED CAPABILITY REQUIRED TO MEET THE TESTING GOALS OF TEST PROGRAMS PRESENT AND FUTURE. MACH 6 NOZZLE (DESIGN & ANALYSIS) THE CONTRACTOR SHALL SUBMIT A FINAL DESIGN PACKAGE FOR THE MACH 6 NOZZLE BASED ON THE FOLLOWING REQUIREMENTS. THE CONTRACTOR SHALL COMPLETE THE DESIGN AND ANALYSIS OF A NEW MACH 6 NOZZLE (M6N) AND ITS ASSOCIATED COMPONENTS AS PER THE FOLLOWING REQUIREMENTS. THE DESIGN FOR A NEW M6N SHALL FULLY INTEGRATE AND ALIGN WITH THE EXISTING M5HIQ EXTENSIONS. THE M6N SHALL CONSIST OF THE FOLLOWING MAIN SEPARABLE COMPONENTS: A NEW CONVERGING-DIVERGING NOZZLE, AND NEW NOZZLE EXTENSIONS. THE M6N SHALL FULLY INTEGRATE AND ALIGN WITH THE EXISTING TEST SECTION NOZZLE SECTION AND MOUNTING SYSTEM CURRENTLY LOCATED IN THE 8-FT HTT. THE M6N HARDWARE SHALL COMPLY WITH THE REQUIREMENTS OUTLINED IN LPR-1710.15 (WIND-TUNNEL MODEL SYSTEMS CRITERIA) DATED JULY 22, 2004 (HTTP://LMS-R.LARC.NASA.GOV/ADMIN/DOCUMENTS/LPR1710-15.PDF ) AND LPR-1710.40 DATED FEBRUARY 5TH, 2005 (HTTP://LMS-R.LARC.NASA.GOV/ADMIN/DOCUMENTS/LPR1710-40.PDF). ASSESS AND ANALYZE ALL INTEGRATION ISSUES OF THE HEAT-SINK/WATER COOLED HARDWARE CONSIDERED IN THEIR DESIGNS TO AVOID THERMAL GROWTH DIFFERENTIALS AND CORRESPONDING DEFORMATION OR SEALING FAILURES. THE M6N DESIGN SHALL NOT ALLOW PERMANENT DEFORMATION OF FLOW PATH COMPONENTS DUE TO THERMAL GROWTH IN EXCESS OF 1% TOTAL THROAT DEFORMATION IN ORDER TO MAINTAIN THE ORIGINAL M6N FLOW PATH GEOMETRY. THE DESIGN SHALL PRODUCE LIFE CYCLE EXPECTANCIES GREATER THAN 3000 WITH THE EXCEPTION OF THE NOZZLE THROAT AREA. THE NOZZLE THROAT LIFE CYCLE SHALL BE A MINIMUM OF 2000. THE M6N NOZZLE AND EXTENSION SECTIONS SHALL NOT HAVE A COMBINED TOTAL LENGTH GREATER THAN 423.90 +- .100 . THE M6N SHALL BE DESIGNED FROM STAINLESS STEEL UNLESS THE ANALYSIS DEMONSTRATES THAT IT CANNOT MEET REQUIREMENTS OUTLINED IN LPR-1710.15/LPR-1710.40.