The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $87,847 - Monday the 3rd of February 2014
  National Aeronautics And Space Administration
  MARSHALL SPACE FLIGHT CENTER
  IGF::OT::IGF STTR PHASE III COMPLETE DEVELOPMENT OF LOCI-STREAM AND THE COMPRESSIBLE FORMULATION CAVITATION MODULE TO THE POINT WHERE TIME-ACCURATE MODELING OF CAVITATING FLOWS ARE POSSIBLE WITHIN A USEFUL TIMEFRAME. THE DEFINITION OF USEFUL IN THIS CASE IS THE ADDITION OF CAVITATION TO THE MODEL SHALL NO MORE THAN DOUBLE THE COMPUTER RESOURCES AND ELAPSED TIME COMPARED TO THE RELATED NON-CAVITATING SIMULATION. DEVELOP A SUITE OF VALIDATION CASES FOR THE SUPPORT OF PRODUCTION USES OF THE CAVITATION MODULE WITH LOCI-STREAM. THE VALIDATION SUITE SHALL CONTAIN THREE-DIMENSIONAL CAVITATION PROBLEMS AND MAY INCLUDE TWO-DIMENSIONAL VALIDATION CASES AS WELL. ALL VALIDATION CASES SHALL BE EXECUTED IN A TIME-ACCURATE MANNER. ALL VALIDATION CASES SHALL BE EXECUTED ON COMPUTATIONAL MESHES CONSISTENT WITH THOSE IN PRODUCTION USE AT NASA/MSFC, PREFERABLY AFLR-GENERATED MESHES. EACH VALIDATION CASE SHALL CONTAIN DOCUMENTATION OF THE EXECUTION OF A RIGOROUS SOLUTION VERIFICATION PROCESS. PURSUE THE OPTIMIZATION OF CAVITATION MODELING ABILITIES WITHIN LOCI-STREAM. THIS TASK MAY INVOLVE, BUT IS NOT LIMITED TO, THE IMPLEMENTATION OF HIGHER FIDELITY CAVITATION MODELS, IMPROVEMENTS TO THE COMPUTATIONAL FLUID DYNAMICS (CFD) ALGORITHMS WITHIN LOCI-STREAM AND/OR THE CAVITATION MODULE, AND IMPROVEMENTS AND EXTENSIONS OF THE NUMERICAL METHODS USED TO CONDUCT THE CFD SIMULATION OF CAVITATING FLOW PROBLEMS. DOCUMENT THE ALGORITHM, RESULTS OF VERIFICATION AND VALIDATION AND RESULTS OF EFFORTS TO IMPROVE THE PERFORMANCE OF THE CAVITATION MODEL IN THE INTERIM AND FINAL REPORTS. EXTEND THE LOCI-STREAM USERS MANUAL TO COMPLETELY DOCUMENT THE CAVITATION METHODOLOGY, ALL USER-CONTROLLED INPUTS RELATED TO THE CAVITATION MODEL AND SUGGESTIONS ON BEST PRACTICES FOR THE APPLICATION OF THE CAVITATION MODEL ON PRODUCTION PROBLEMS. PROVIDE INTERIM AND FINAL REPORTS AND DELIVERY OF THE INTERIM AND OFFICIAL RELEASE VERSIONS OF LOCI-STREAM AND THE CAVITATION MODULE FOR MSFC PERSONNEL TO EVALUATE AND USE FOR PRODUCTION ANALYSIS. DELIVERABLES THE FOLLOWING DOCUMENTATION, REPORTING AND SOFTWARE WILL BE REQUIRED: 1) FINAL AND QUARTERLY REPORTS DETAILING THE METHODOLOGY AND RESULTS OF VERIFICATION AND VALIDATION CASES AND 2) DELIVERY OF INTERIM AND FINAL VERSIONS OF LOCI-STREAM AND THE CAVITATION MODULE, INCLUDING THE UPDATED LOCI-STREAM USER MANUAL COVERING FORMULATION AND USE OF THE CAVITATION MODULE. THE CONTRACTOR SHALL REPORT AND DOCUMENT THIS WORK AND FULFILL THE REQUIREMENTS OF ASSOCIATED DATA REQUIREMENT DESCRIPTIONS (DRDS) AS OUTLINED IN DATA PROCUREMENT DOCUMENT (DPD) 1435 (ATTACHMENT J-2). THE CONTRACTOR SHALL DETERMINE THE DATA RESTRICTION THAT APPLIES TO EACH DATA DELIVERABLE AND MARK OR TRANSMIT THE DATA RESTRICTION IN ACCORDANCE WITH SECTION 2.3.3 OF THE DATA PROCUREMENT DOCUMENT. THE CONTRACTOR SHALL PREPARE AND SUBMIT A QUARTERLY PROGRESS REPORT IN ACCORDANCE WITH DRD 1435MA-001.

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• $45,000 - Wednesday the 19th of March 2014
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THE INNOVATION PROPOSED HERE IS A HIGH PERFORMANCE, HIGH FIDELITY SIMULATION CAPABILITY TO ENABLE ACCURATE, FAST AND ROBUST SIMULATION OF UNSTEADY TURBULENT, REACTING FLOWS INVOLVING PROPELLANTS OF RELEVANCE TO NASA (GOX/GH2, LOX/LH2 AND LOX/LCH4). THE KEY FEATURES OF THIS PROPOSED CAPABILITY ARE: (A) HYBRID RANS-LES (HRLES) METHODOLOGY, AND (B) FLAMELET MODELING FOR TURBULENT COMBUSTION, INCORPORATED IN A PROVEN EXISTING SOLVER CALLED LOCI-STREAM WHICH HAS BEEN DEVELOPED BY THE PROPOSING PERSONNEL UNDER FUNDING FROM NASA OVER THE LAST SEVERAL YEARS. BASIC FLAMELET METHODOLOGY HAS BEEN INCORPORATED IN LOCI-STREAM DURING PHASE 1 WORK AND TESTED ON GAS-GAS INJECTORS OF RELEVANCE TO NASA. THE ENHANCEMENTS IN LOCI-STREAM RESULTING FROM PHASE 1 WORK HAVE DEMONSTRATED AN ORDER OF MAGNITUDE IMPROVEMENT IN SIMULATION TURNAROUND TIMES RELATIVE TO EXISTING CAPABILITY FOR TURBULENT REACTING FLOW APPLICATIONS AT NASA. THE WORK PROPOSED DURING PHASE 2 WILL EXTEND THE FLAMELET METHODOLOGY TO REAL-FLUID FLOWS, WALL HEAT TRANSFER AND VARIABLE PRESSURES. THIS WILL ULTIMATELY RESULT IN A STATE-OF-THE-ART DESIGN AND ANALYSIS TOOL TO ENABLE THE ACCURATE MODELING OF FOR MULTIPHASE COMBUSTION IN SOLID AND LIQUID ROCKET ENGINES, COMBUSTION STABILITY ANALYSIS, ETC. WHICH CONSTITUTE CRITICAL COMPONENTS OF VERSATILE SPACE PROPULSION ENGINES PART OF NASA'S DEEP SPACE MISSIONS.

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• $373,990 - Wednesday the 17th of September 2014
  Department Of Air Force
  FA8651 AFRL RWK
  ADD FINAL INCREMENT OF FUNDS&ENABLING CLAUSE

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• $15,415 - Friday the 27th of April 2012
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  THE INNOVATION PROPOSED HERE IS A FRAMEWORK FOR THE INCORPORATION OF HIGH PERFORMANCE, HIGH FIDELITY COMPUTATIONAL FLUID DYNAMICS (CFD) TECHNIQUES TO ENABLE ACCURATE AND ROBUST SIMULATION OF UNSTEADY TURBULENT, REACTING OR NON-REACTING FLOWS INVOLVING REAL OR IDEAL FLUIDS WITH PRACTICALLY USEFUL TURNAROUND TIMES. THE EMPHASIS WILL BE ON A MAJOR IMPROVEMENT IN EFFICIENCY AND SCALABILITY OF LOCI-STREAM WHICH IS A CFD CODE ALREADY IN USE AT NASA. THE LOCI-STREAM CODE IS BECOMING MORE AND MORE RELIABLE FOR INDIVIDUAL CALCULATIONS; HOWEVER, THE OVERALL COMPUTATIONAL PERFORMANCE OF THE CODE ON THE COMPUTER CLUSTERS EMPLOYED BY NASA IS NOT SUFFICIENT FOR THE TOOL TO BE USED EFFECTIVELY IN THE DESIGN PROCESS GIVEN THE COMPLEXITY OF THE CONFIGURATIONS BEING MODELED BY NASA ENGINEERS ALONG WITH THE LARGE GRID SIZES USED TO MODEL THESE CONFIGURATIONS. THE PROPOSED WORK TARGETS AN ORDER OF MAGNITUDE IMPROVEMENT IN PERFORMANCE OF LOCI-STREAM. THE WORK PROPOSED HERE WILL ENABLE THE EFFICIENT AND ACCURATE MODELING OF: (A) MULTIPHASE COMBUSTION IN SOLID AND LIQUID ROCKET ENGINES, (B) COMBUSTION STABILITY ANALYSIS (C) ACOUSTIC FIELDS OF SPACE PROPULSION SYSTEMS IN NEAR-GROUND OPERATION, (D) LAUNCH PAD-INDUCED ENVIRONMENTS, (D) SMALL VALVES AND TURBOPUMPS, ETC.

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• $149,944 - Thursday the 1st of August 2013
  National Aeronautics And Space Administration
  MARSHALL SPACE FLIGHT CENTER
  IGF::OT::IGF STTR PHASE III - DEVELOPMENT OF SPRAY COMBUSTION CAPABILITY IN LOCI-STREAM FOR LIQUID ROCKET INJECTORS USING HYBRID RANS-LES (HRLES) AND FLAMELET MODELS

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