Federal Contractor Profile
Rolls-royce North American Technologies INC
$96.9M obligated·60 awards·2 agencies·7 NAICS
Federal Contracts
Showing contracts 101–132 of 132 total. Sorted by action date, most recent first. Excludes $0 modifications.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| Aug 29, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC11TA92T | 541712 | ADMINISTRATION AND BASELINE SECURITY | $15K |
| Aug 29, 2017 | Department of DefenseDCMA APO ROLLS ROYCE INDIANAPOLIS | FA865010C5325 | 541712 | AMPI: PRECISION THIN WALL AIRFOIL CASTINGS | $1.1M |
| Jul 27, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | 0010 | 541712 | SUPERSONIC TURBINE ENGINE FOR LONG RANGE (STELR) DEMO | $129K |
| Jul 20, 2017 | Department of DefenseHQUSSOCOM | H9222216C0121 | 336413 | A KITS AND B KITS FOR AC-130W | $400K |
| Jun 14, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | 0006 | 541710 | — | $600 |
| Jun 7, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC17TA42T | 541712 | IGF::OT::IGF TASK ORDER NNC17TA42T ENTITLED `ELECTRICAL&MECHANICAL HYBRID DISTRIBUTED PROPULSION FOR SINGLE-AISLE AIRCRAFT'. RESEARCH OPPORTUNITIES IN AERONAUTICS (ROA-2016)-NNH16ZEA001N-AATT1 PROPOSAL NUMBER 16-AATTI-0003 CONTRACT NNC15BA07B UNDER TASK ORDER NNC17TA42T. THE OBJECTIVE OF THIS 12-MONTH WORK IS TO DEVELOP AN ADVANCED SINGLE-AISLE-CLASS COMMERCIAL TRANSPORT CONCEPT WITH EXPECTED ENTRY INTO SERVICE (EIS) IN THE MIDTERM TIMEFRAME (EIS IN 2035 OR EARLIER) WHERE A SIGNIFICANT AMOUNT OF ELECTRICAL POWER IS USED TO GENERATE THRUST. IN PARTICULAR, THE CONCEPT VEHICLE TO BE DEVELOPED SHALL LEVERAGE A NUMBER OF INNOVATIVE TECHNOLOGIES TARGETING FOUR MECHANISMS IN PARTICULAR THAT SHALL LEAD TO SIGNIFICANT IMPROVEMENTS IN LIFE-CYCLE CARBON EMISSIONS, LTO NOX, NOISE, AND MISSION ENERGY USE. FIRST, IMPROVEMENTS TO LIFTING SURFACE EFFECTIVENESS SHALL BE ACHIEVED THROUGH THE USE OF WING-EMBEDDED PROPULSION. SECOND, FUSELAGE DRAG REDUCTION/AND PROPULSIVE EFFICIENCY SHALL BE AFFECTED BY AFT FUSELAGE BOUNDARY LAYER INGESTIONS. THIRD, STORED ELECTRICAL ENERGY SHALL BE USED TO IMPROVE GAS TURBINE EFFICIENCY BY ALTERING THE CYCLE DESIGN POINT FOR CRUISE, REDUCE LTO NOX THROUGH TAKEOFF POWER SUPPLEMENTATION, AND OFFSET CRUISE ENERGY REQUIREMENTS FOR SHORTER RANGE OPERATIONS. FOURTH, WING-EMBEDDED PROPULSION AND AFT FUSELAGE BLI RELY ON DISTRIBUTED PROPULSION. THIS CONCEPT SHALL APPLY A COMBINATION OF MECHANICAL AND ELECTRICAL DISTRIBUTED TO TRANSFER THRUST POWER FROM THE GAS TURBINE SOURCE TO THE PROPULSOR CONSUMERS. THIS COMBINED POWER DISTRIBUTION SYSTEM SHALL UTILIZE THE APPROPRIATE MEANS FOR POWER TRANSFER BASED ON PROPULSOR PROXIMITY TO THE GAS TURBINE, REQUIREMENTS FOR RE-CONFIGURABILITY AND REDISTRIBUTION TO REDUCE ONE ENGINE INOPERABLE (OEI) ADVERSE YAW, AND THE DESIRED LEVEL OF ELECTRICAL POWER SUPPLEMENTATION. THIS TECHNOLOGY SUITE SHALL TARGET REALIZATION IN THE EIS 2035 TIMEFRAME. THE CONCEPT SHALL BE DESIGNED TO CARRY A PAYLOAD OF 154 PASSENGERS AT 200LB PER PASSENGER AND 0 CARGO PAYLOAD, AND SHALL BE CAPABLE OF OPERATING IN THE CURRENT INFRASTRUCTURE INCLUDING CLASS C AIRPORT OPERATIONS. IT SHALL BE DESIGNED IN ANTICIPATION OF FURTHER ENVIRONMENTAL RESTRICTIONS BY THE 2035 EIS DATE. THIS VEHICLE AND PROPULSION SYSTEM CONCEPT SHALL ALSO INCLUDE AN ASSESSMENT OF THE TALL POLE TECHNOLOGIES, OPERATIONAL ECONOMICS, AND TOP SAFETY AND FLIGHT CERTIFICATION CHALLENGES. PREVIOUS INVESTMENTS IN THE ECO-150R AND ASSOCIATED TOOLS SHALL BE LEVERAGED TO INVESTIGATE A MECHANICAL/ELECTRICAL HYBRID PROPULSION SYSTEM UTILIZING EMBEDDED WING FANS AND FUSELAGE AFT BOUNDARY LAYER INGESTION. THIS PROPULSION SYSTEM AND AIRCRAFT SYSTEM-LEVEL INTEGRATION SHALL EXCEED ALL PREVIOUSLY EXPLORED ECO-150 CONCEPTS AND VEHICLE ITERATIONS WITHIN AND OUTSIDE OF GOVERNMENT. | $314K |
| May 31, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC17TA29T | 541712 | IGF::OT::IGF CONTRACT OPERATIONS AND BASELINE SECURITY. FOR MORE INFORMATION CONTACT THE FPDS ADMINISTRATOR. | $21K |
| May 25, 2017 | Department of DefenseNAVAL AIR SYSTEMS COMMAND | N0001917C0065 | 336413 | THE PURPOSE OF THIS CONTRACT IS TO PROVIDE FSR SUPPORT FOR THE HMX-1 SQUADRON. (PID# N00019-16-RFPREQ-PMA-275-0444) IPT - POWER AND PROPULSION IGF::OT::IGF | $197K |
| May 5, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC17TA42T | 541712 | IGF::OT::IGF TASK ORDER NNC17TA42T ENTITLED `ELECTRICAL&MECHANICAL HYBRID DISTRIBUTED PROPULSION FOR SINGLE-AISLE AIRCRAFT'. RESEARCH OPPORTUNITIES IN AERONAUTICS (ROA-2016)-NNH16ZEA001N-AATT1 PROPOSAL NUMBER 16-AATTI-0003 CONTRACT NNC15BA07B UNDER TASK ORDER NNC17TA42T. THE OBJECTIVE OF THIS 12-MONTH WORK IS TO DEVELOP AN ADVANCED SINGLE-AISLE-CLASS COMMERCIAL TRANSPORT CONCEPT WITH EXPECTED ENTRY INTO SERVICE (EIS) IN THE MIDTERM TIMEFRAME (EIS IN 2035 OR EARLIER) WHERE A SIGNIFICANT AMOUNT OF ELECTRICAL POWER IS USED TO GENERATE THRUST. IN PARTICULAR, THE CONCEPT VEHICLE TO BE DEVELOPED SHALL LEVERAGE A NUMBER OF INNOVATIVE TECHNOLOGIES TARGETING FOUR MECHANISMS IN PARTICULAR THAT SHALL LEAD TO SIGNIFICANT IMPROVEMENTS IN LIFE-CYCLE CARBON EMISSIONS, LTO NOX, NOISE, AND MISSION ENERGY USE. FIRST, IMPROVEMENTS TO LIFTING SURFACE EFFECTIVENESS SHALL BE ACHIEVED THROUGH THE USE OF WING-EMBEDDED PROPULSION. SECOND, FUSELAGE DRAG REDUCTION/AND PROPULSIVE EFFICIENCY SHALL BE AFFECTED BY AFT FUSELAGE BOUNDARY LAYER INGESTIONS. THIRD, STORED ELECTRICAL ENERGY SHALL BE USED TO IMPROVE GAS TURBINE EFFICIENCY BY ALTERING THE CYCLE DESIGN POINT FOR CRUISE, REDUCE LTO NOX THROUGH TAKEOFF POWER SUPPLEMENTATION, AND OFFSET CRUISE ENERGY REQUIREMENTS FOR SHORTER RANGE OPERATIONS. FOURTH, WING-EMBEDDED PROPULSION AND AFT FUSELAGE BLI RELY ON DISTRIBUTED PROPULSION. THIS CONCEPT SHALL APPLY A COMBINATION OF MECHANICAL AND ELECTRICAL DISTRIBUTED TO TRANSFER THRUST POWER FROM THE GAS TURBINE SOURCE TO THE PROPULSOR CONSUMERS. THIS COMBINED POWER DISTRIBUTION SYSTEM SHALL UTILIZE THE APPROPRIATE MEANS FOR POWER TRANSFER BASED ON PROPULSOR PROXIMITY TO THE GAS TURBINE, REQUIREMENTS FOR RE-CONFIGURABILITY AND REDISTRIBUTION TO REDUCE ONE ENGINE INOPERABLE (OEI) ADVERSE YAW, AND THE DESIRED LEVEL OF ELECTRICAL POWER SUPPLEMENTATION. THIS TECHNOLOGY SUITE SHALL TARGET REALIZATION IN THE EIS 2035 TIMEFRAME. THE CONCEPT SHALL BE DESIGNED TO CARRY A PAYLOAD OF 154 PASSENGERS AT 200LB PER PASSENGER AND 0 CARGO PAYLOAD, AND SHALL BE CAPABLE OF OPERATING IN THE CURRENT INFRASTRUCTURE INCLUDING CLASS C AIRPORT OPERATIONS. IT SHALL BE DESIGNED IN ANTICIPATION OF FURTHER ENVIRONMENTAL RESTRICTIONS BY THE 2035 EIS DATE. THIS VEHICLE AND PROPULSION SYSTEM CONCEPT SHALL ALSO INCLUDE AN ASSESSMENT OF THE TALL POLE TECHNOLOGIES, OPERATIONAL ECONOMICS, AND TOP SAFETY AND FLIGHT CERTIFICATION CHALLENGES. PREVIOUS INVESTMENTS IN THE ECO-150R AND ASSOCIATED TOOLS SHALL BE LEVERAGED TO INVESTIGATE A MECHANICAL/ELECTRICAL HYBRID PROPULSION SYSTEM UTILIZING EMBEDDED WING FANS AND FUSELAGE AFT BOUNDARY LAYER INGESTION. THIS PROPULSION SYSTEM AND AIRCRAFT SYSTEM-LEVEL INTEGRATION SHALL EXCEED ALL PREVIOUSLY EXPLORED ECO-150 CONCEPTS AND VEHICLE ITERATIONS WITHIN AND OUTSIDE OF GOVERNMENT. | $250K |
| Apr 18, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | 0010 | 541712 | SUPERSONIC TURBINE ENGINE FOR LONG RANGE (STELR) DEMO | $2.9M |
| Apr 18, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC17TA29T | 541712 | IGF::OT::IGF CONTRACT OPERATIONS AND BASELINE SECURITY. FOR MORE INFORMATION CONTACT THE FPDS ADMINISTRATOR. | $5K |
| Mar 29, 2017 | Department of DefenseDCMA APO ROLLS ROYCE INDIANAPOLIS | 0006 | 541710 | — | $9K |
| Feb 1, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC15TA69T | 541712 | IGF::OT::IGF "HIGH TEMPERATURE SEALS" | $23K |
| Jan 30, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC15TA69T | 541712 | IGF::OT::IGF "HIGH TEMPERATURE SEALS" | $65K |
| Jan 20, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC14CA29C | 541712 | IGF::OT::IGF SYSTEMS AND TECHNOLOGY STUDIES HAVE INDICATED THAT HYBRID GAS-ELECTRIC PROPULSION SYSTEMS FOR SUBSONIC TRANSPORT AIRCRAFT ARE POTENTIALLY FEASIBLE IN THE N+3 TIMEFRAME. FW PROJECT RESEARCH CURRENTLY FOCUSES ON TWO GENERAL ARCHITECTURE CONCEPTS: 1) A GAS-ELECTRIC HYBRID CONCEPT WHERE AT A MINIMUM GAS TURBINE AND STORED ELECTRIC ENERGY SOURCES DRIVE A SINGLE PROPULSOR THROUGH A COMMON SHAFT WITH THE POTENTIAL FOR USING ELECTRICAL ENERGY FROM STORED ENERGY OR TURBINE DRIVEN GENERATOR TO POWER ELECTRICAL MOTOR DRIVEN AUXILIARY OR REMOTE FANS, AND 2) A SINGLE GAS TURBINE ELECTRIC POWER SOURCE WHERE THE GAS TURBINE IS USED TO DRIVE A GENERATOR TO CONVERT ALL THE TURBINE POWER TO ELECTRICITY THAT IS THEN DISTRIBUTED TO MULTIPLE DISTRIBUTED ELECTRIC MOTOR DRIVEN PROPULSORS. THE FW PROJECT IS INVESTING IN ELECTRIC SYSTEM MATERIALS, ELECTRIC COMPONENTS, AND POWER MANAGEMENT AND DISTRIBUTION TECHNOLOGIES IN SUPPORT OF THESE SYSTEM ARCHITECTURE CONCEPTS AND CONFIGURATION STUDIES. TO COMPLEMENT EXISTING RESEARCH, SEVERAL SUBTOPICS WERE SOLICITED. THE LONG-TERM OBJECTIVE OF THIS RESEARCH IS TO EXPLORE THE DESIGN SPACE OF POTENTIAL ENGINE CYCLES, MOTOR, POWER CONVERSION, ENERGY STORAGE AND THERMAL MANAGEMENT TECHNOLOGIES FOR GAS-ELECTRIC HYBRID PROPULSION SYSTEMS TO IDENTIFY THE ARCHITECTURE WITH THE BEST PERFORMANCE AGAINST NASA N+3 OBJECTIVES (NOISE, EMISSIONS, ENERGY CONSUMPTION) FOR A 737/A320 CLASS SINGLE AISLE AIRCRAFT. BELOW IS A SUMMARY OF OBJECTIVES FOR EACH PHASE. TASK 1.1 NPSS MODELING AND CONCEPT DEFINITION TASK 1.2 - SYSTEM CONCEPTUAL DESIGN AND DOWN-SELECTION TASK 2.1 - DETAILED CONCEPTUAL DESIGN TASK 2.2 - TECHNOLOGY ROADMAP DEVELOPMENT TASK 3.1 - SUBSCALE ENERGY MANAGEMENT/ELECTRIC DRIVE DEVELOPMENT TASK 3.2 CONTROL SYSTEM PRELIMINARY DESIGN AND PERFORMANCE VALIDATION TASK 3.3 PROPULSION SYSTEM CONCEPTUAL DESIGN UPDATE 1.3.3 PHASE I DELIVERABLES THE CONTRACTOR SHALL PROVIDE: A PHASE I FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND FINAL CONCEPT SELECTED FOR DETAILED CONCEPTUAL DESIGN. DUE BY SEPTEMBER 30, 2015. PHASE II DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE II FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND CONCEPTUAL DESIGNS. DUE SEP 2016 2) AN NPSS FULL PROPULSION SYSTEM MODEL OF THE FINAL SYSTEM. THIS MODEL WILL INCLUDE TURBOMACHINERY PERFORMANCE MAPS, POWER REQUIREMENTS, WEIGHTS, AND VOLUMES FOR THE TURBOMACHINERY/GAS TURBINE ENGINE, ELECTRIC MOTOR PERFORMANCE MAPS, ENERGY STORAGE DEVICE PERFORMANCE CHARACTERISTICS, ELECTRICAL TRANSMISSION AND POWER CONDITIONING COMPONENTS, AND THERMAL MANAGEMENT SYSTEM. THIS MODEL WILL BE FOR GOVERNMENT USE ONLY. DUE SEP 2016 3) NPSS ELEMENTS, SUBELEMENTS, FUNCTIONS REQUIRED BY THE MODEL IN DELIVERABLE 2 OTHER THAN THOSE INCLUDED WITH THE NPSS PROGRAM WILL BE DELIVERED TO NASA FOR PUBLIC DISSEMINATION. DUE SEP 2016 4) A DETAILED TECHNOLOGY ROADMAP THAT SHOWS A CLEAR RESEARCH PATH TO ELEVATE THE KEY TECHNICAL CHALLENGES EMBODIED IN THE PREFERRED SYSTEM CONCEPT TO TRL 6 BY 2025. DUE SEP 2016 5) FOUR MONTHS BEFORE THE PROPOSED START OF PHASE III, CONTRACTOR WILL SUBMIT A PHASE III PROPOSAL TO INCLUDE PHASE III TASKS, DELIVERABLES, LABOR HOURS, PRICING, AND THE CONTRACTOR S COMMITMENT OF RESOURCES. NASA WILL CONSIDER THESE SUBJECTS AND THE CONTRACTOR S PROJECTED COMMITMENT OF RESOURCES TO PHASE III WHEN DETERMINING WHETHER TO EXERCISE OPTION 2. PHASE III DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE III FINAL REPORT, ADDRESSING THE INITIAL STEPS TO MATURING IDENTIFIED KEY TECHNICAL CHALLENGES IN THE PREFERRED SYSTEM CONCEPT UPON COMPLETION OF PHASE III (IF AWARDED). DUE SEPT 2019 2) FINAL NPSS MODEL INCLUDING ALL NECESSARY COMPONENT PERFORMANCE CHARACTERISTICS FOR GOVERNMENT USE ONLY. DUE SEPT 2019 | $1.3M |
| Nov 16, 2016 | Department of DefenseNAVAL AIR SYSTEMS COMMAND | 0003 | 336412 | IGF::OT::IGF OPTION YEAR 2 FSR SUPPORT | $227K |
| Nov 4, 2016 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865013C5211 | 541712 | IGF::OT::IGF BEHAVIOR&LIFE PREDICTION FOR SIC/SIC CMCS FOR TURBINE APPLICATIONS: ENVIRONMENTAL DAMAGE MODELING | $135K |
| Oct 19, 2016 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC16TA23T | 541712 | IGF::OT::IGF NNC15BA07B/NNC16TA23T FOR EXTENDED TURBINE OPERABILITY EVALUATION FOR A TBCC RESEARCH VEHICLE CONCEPT UTILIZING WATER INJECTION THE OVERALL OBJECTIVE FOR THE F405-RR-402 WATER INJECTION TEST IS TO VERIFY THAT AN OFF-THE-SHELF (OTS) TURBINE CAN OPERATE AT HIGHER THAN DESIGNED MACH NUMBER ENTHALPY CONDITIONS USING WATER TO COOL THE INCOMING AIR. THE RESULTS FROM THIS TEST WILL BE USED TO ASSESS THE PERFORMANCE AND OPERABILITY OF AN OFF-THE-SHELF TURBINE IN AN AFFORDABLE, REUSABLE TURBINE BASED COMBINED CYCLE HYPERSONIC VEHICLE. THE DEFENSE ADVANCED RESEARCH PROJECTS AGENCY (DARPA) WILL USE THE TEST RESULTS TO DETERMINE A PATH FORWARD FOR THE TBCC PROPULSION SYSTEM OF A MAJOR HYPERSONIC VEHICLE DEVELOPMENT PROGRAM. NASA WILL USE THE RESULTS OF THIS STUDY TO DEVELOP A TBCC VISION VEHICLE FOR CIVILIAN APPLICATIONS FOR POINT-TO-POINT TRANSPORT WITH THE END GOAL OF SPACE ACCESS. THE BASE PERIOD CONSISTS OF THE FOLLOWING SUB-TASKS: 1) CHECKOUT OF AN F405-RR-402 ENGINE, 2) F405 ENGINE PERFORMANCE AND OPERABILITY ANALYSIS, 3) TEST HARDWARE DESIGN AND TEST PLANNING SUPPORT, 4) MEETINGS SUPPORT AND REPORTING. THE OPTION PERIOD CONSISTS OF THE FOLLOWING SUB-TASKS: 1) TEST HARDWARE DEVELOPMENT AND TEST PLANNING SUPPORT, 2) HARDWARE INSTALLATION AND TEST SUPPORT, 3) POST-TEST DATA ANALYSIS AND ENGINE INSPECTION, 4) MEETINGS SUPPORT AND REPORTING. | $720K |
| Oct 17, 2016 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC14CA29C | 541712 | IGF::OT::IGF SYSTEMS AND TECHNOLOGY STUDIES HAVE INDICATED THAT HYBRID GAS-ELECTRIC PROPULSION SYSTEMS FOR SUBSONIC TRANSPORT AIRCRAFT ARE POTENTIALLY FEASIBLE IN THE N+3 TIMEFRAME. FW PROJECT RESEARCH CURRENTLY FOCUSES ON TWO GENERAL ARCHITECTURE CONCEPTS: 1) A GAS-ELECTRIC HYBRID CONCEPT WHERE AT A MINIMUM GAS TURBINE AND STORED ELECTRIC ENERGY SOURCES DRIVE A SINGLE PROPULSOR THROUGH A COMMON SHAFT WITH THE POTENTIAL FOR USING ELECTRICAL ENERGY FROM STORED ENERGY OR TURBINE DRIVEN GENERATOR TO POWER ELECTRICAL MOTOR DRIVEN AUXILIARY OR REMOTE FANS, AND 2) A SINGLE GAS TURBINE ELECTRIC POWER SOURCE WHERE THE GAS TURBINE IS USED TO DRIVE A GENERATOR TO CONVERT ALL THE TURBINE POWER TO ELECTRICITY THAT IS THEN DISTRIBUTED TO MULTIPLE DISTRIBUTED ELECTRIC MOTOR DRIVEN PROPULSORS. THE FW PROJECT IS INVESTING IN ELECTRIC SYSTEM MATERIALS, ELECTRIC COMPONENTS, AND POWER MANAGEMENT AND DISTRIBUTION TECHNOLOGIES IN SUPPORT OF THESE SYSTEM ARCHITECTURE CONCEPTS AND CONFIGURATION STUDIES. TO COMPLEMENT EXISTING RESEARCH, SEVERAL SUBTOPICS WERE SOLICITED. THE LONG-TERM OBJECTIVE OF THIS RESEARCH IS TO EXPLORE THE DESIGN SPACE OF POTENTIAL ENGINE CYCLES, MOTOR, POWER CONVERSION, ENERGY STORAGE AND THERMAL MANAGEMENT TECHNOLOGIES FOR GAS-ELECTRIC HYBRID PROPULSION SYSTEMS TO IDENTIFY THE ARCHITECTURE WITH THE BEST PERFORMANCE AGAINST NASA N+3 OBJECTIVES (NOISE, EMISSIONS, ENERGY CONSUMPTION) FOR A 737/A320 CLASS SINGLE AISLE AIRCRAFT. BELOW IS A SUMMARY OF OBJECTIVES FOR EACH PHASE. TASK 1.1 NPSS MODELING AND CONCEPT DEFINITION TASK 1.2 - SYSTEM CONCEPTUAL DESIGN AND DOWN-SELECTION TASK 2.1 - DETAILED CONCEPTUAL DESIGN TASK 2.2 - TECHNOLOGY ROADMAP DEVELOPMENT TASK 3.1 - SUBSCALE ENERGY MANAGEMENT/ELECTRIC DRIVE DEVELOPMENT TASK 3.2 CONTROL SYSTEM PRELIMINARY DESIGN AND PERFORMANCE VALIDATION TASK 3.3 PROPULSION SYSTEM CONCEPTUAL DESIGN UPDATE 1.3.3 PHASE I DELIVERABLES THE CONTRACTOR SHALL PROVIDE: A PHASE I FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND FINAL CONCEPT SELECTED FOR DETAILED CONCEPTUAL DESIGN. DUE BY SEPTEMBER 30, 2015. PHASE II DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE II FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND CONCEPTUAL DESIGNS. DUE SEP 2016 2) AN NPSS FULL PROPULSION SYSTEM MODEL OF THE FINAL SYSTEM. THIS MODEL WILL INCLUDE TURBOMACHINERY PERFORMANCE MAPS, POWER REQUIREMENTS, WEIGHTS, AND VOLUMES FOR THE TURBOMACHINERY/GAS TURBINE ENGINE, ELECTRIC MOTOR PERFORMANCE MAPS, ENERGY STORAGE DEVICE PERFORMANCE CHARACTERISTICS, ELECTRICAL TRANSMISSION AND POWER CONDITIONING COMPONENTS, AND THERMAL MANAGEMENT SYSTEM. THIS MODEL WILL BE FOR GOVERNMENT USE ONLY. DUE SEP 2016 3) NPSS ELEMENTS, SUBELEMENTS, FUNCTIONS REQUIRED BY THE MODEL IN DELIVERABLE 2 OTHER THAN THOSE INCLUDED WITH THE NPSS PROGRAM WILL BE DELIVERED TO NASA FOR PUBLIC DISSEMINATION. DUE SEP 2016 4) A DETAILED TECHNOLOGY ROADMAP THAT SHOWS A CLEAR RESEARCH PATH TO ELEVATE THE KEY TECHNICAL CHALLENGES EMBODIED IN THE PREFERRED SYSTEM CONCEPT TO TRL 6 BY 2025. DUE SEP 2016 5) FOUR MONTHS BEFORE THE PROPOSED START OF PHASE III, CONTRACTOR WILL SUBMIT A PHASE III PROPOSAL TO INCLUDE PHASE III TASKS, DELIVERABLES, LABOR HOURS, PRICING, AND THE CONTRACTOR S COMMITMENT OF RESOURCES. NASA WILL CONSIDER THESE SUBJECTS AND THE CONTRACTOR S PROJECTED COMMITMENT OF RESOURCES TO PHASE III WHEN DETERMINING WHETHER TO EXERCISE OPTION 2. PHASE III DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE III FINAL REPORT, ADDRESSING THE INITIAL STEPS TO MATURING IDENTIFIED KEY TECHNICAL CHALLENGES IN THE PREFERRED SYSTEM CONCEPT UPON COMPLETION OF PHASE III (IF AWARDED). DUE SEPT 2019 2) FINAL NPSS MODEL INCLUDING ALL NECESSARY COMPONENT PERFORMANCE CHARACTERISTICS FOR GOVERNMENT USE ONLY. DUE SEPT 2019 | $493K |
| Sep 27, 2016 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC16TA23T | 541712 | IGF::OT::IGF NNC15BA07B/NNC16TA23T FOR EXTENDED TURBINE OPERABILITY EVALUATION FOR A TBCC RESEARCH VEHICLE CONCEPT UTILIZING WATER INJECTION THE OVERALL OBJECTIVE FOR THE F405-RR-402 WATER INJECTION TEST IS TO VERIFY THAT AN OFF-THE-SHELF (OTS) TURBINE CAN OPERATE AT HIGHER THAN DESIGNED MACH NUMBER ENTHALPY CONDITIONS USING WATER TO COOL THE INCOMING AIR. THE RESULTS FROM THIS TEST WILL BE USED TO ASSESS THE PERFORMANCE AND OPERABILITY OF AN OFF-THE-SHELF TURBINE IN AN AFFORDABLE, REUSABLE TURBINE BASED COMBINED CYCLE HYPERSONIC VEHICLE. THE DEFENSE ADVANCED RESEARCH PROJECTS AGENCY (DARPA) WILL USE THE TEST RESULTS TO DETERMINE A PATH FORWARD FOR THE TBCC PROPULSION SYSTEM OF A MAJOR HYPERSONIC VEHICLE DEVELOPMENT PROGRAM. NASA WILL USE THE RESULTS OF THIS STUDY TO DEVELOP A TBCC VISION VEHICLE FOR CIVILIAN APPLICATIONS FOR POINT-TO-POINT TRANSPORT WITH THE END GOAL OF SPACE ACCESS. THE BASE PERIOD CONSISTS OF THE FOLLOWING SUB-TASKS: 1) CHECKOUT OF AN F405-RR-402 ENGINE, 2) F405 ENGINE PERFORMANCE AND OPERABILITY ANALYSIS, 3) TEST HARDWARE DESIGN AND TEST PLANNING SUPPORT, 4) MEETINGS SUPPORT AND REPORTING. THE OPTION PERIOD CONSISTS OF THE FOLLOWING SUB-TASKS: 1) TEST HARDWARE DEVELOPMENT AND TEST PLANNING SUPPORT, 2) HARDWARE INSTALLATION AND TEST SUPPORT, 3) POST-TEST DATA ANALYSIS AND ENGINE INSPECTION, 4) MEETINGS SUPPORT AND REPORTING. | $690K |
| Sep 20, 2016 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC14CA29C | 541712 | IGF::OT::IGF SYSTEMS AND TECHNOLOGY STUDIES HAVE INDICATED THAT HYBRID GAS-ELECTRIC PROPULSION SYSTEMS FOR SUBSONIC TRANSPORT AIRCRAFT ARE POTENTIALLY FEASIBLE IN THE N+3 TIMEFRAME. FW PROJECT RESEARCH CURRENTLY FOCUSES ON TWO GENERAL ARCHITECTURE CONCEPTS: 1) A GAS-ELECTRIC HYBRID CONCEPT WHERE AT A MINIMUM GAS TURBINE AND STORED ELECTRIC ENERGY SOURCES DRIVE A SINGLE PROPULSOR THROUGH A COMMON SHAFT WITH THE POTENTIAL FOR USING ELECTRICAL ENERGY FROM STORED ENERGY OR TURBINE DRIVEN GENERATOR TO POWER ELECTRICAL MOTOR DRIVEN AUXILIARY OR REMOTE FANS, AND 2) A SINGLE GAS TURBINE ELECTRIC POWER SOURCE WHERE THE GAS TURBINE IS USED TO DRIVE A GENERATOR TO CONVERT ALL THE TURBINE POWER TO ELECTRICITY THAT IS THEN DISTRIBUTED TO MULTIPLE DISTRIBUTED ELECTRIC MOTOR DRIVEN PROPULSORS. THE FW PROJECT IS INVESTING IN ELECTRIC SYSTEM MATERIALS, ELECTRIC COMPONENTS, AND POWER MANAGEMENT AND DISTRIBUTION TECHNOLOGIES IN SUPPORT OF THESE SYSTEM ARCHITECTURE CONCEPTS AND CONFIGURATION STUDIES. TO COMPLEMENT EXISTING RESEARCH, SEVERAL SUBTOPICS WERE SOLICITED. THE LONG-TERM OBJECTIVE OF THIS RESEARCH IS TO EXPLORE THE DESIGN SPACE OF POTENTIAL ENGINE CYCLES, MOTOR, POWER CONVERSION, ENERGY STORAGE AND THERMAL MANAGEMENT TECHNOLOGIES FOR GAS-ELECTRIC HYBRID PROPULSION SYSTEMS TO IDENTIFY THE ARCHITECTURE WITH THE BEST PERFORMANCE AGAINST NASA N+3 OBJECTIVES (NOISE, EMISSIONS, ENERGY CONSUMPTION) FOR A 737/A320 CLASS SINGLE AISLE AIRCRAFT. BELOW IS A SUMMARY OF OBJECTIVES FOR EACH PHASE. TASK 1.1 NPSS MODELING AND CONCEPT DEFINITION TASK 1.2 - SYSTEM CONCEPTUAL DESIGN AND DOWN-SELECTION TASK 2.1 - DETAILED CONCEPTUAL DESIGN TASK 2.2 - TECHNOLOGY ROADMAP DEVELOPMENT TASK 3.1 - SUBSCALE ENERGY MANAGEMENT/ELECTRIC DRIVE DEVELOPMENT TASK 3.2 CONTROL SYSTEM PRELIMINARY DESIGN AND PERFORMANCE VALIDATION TASK 3.3 PROPULSION SYSTEM CONCEPTUAL DESIGN UPDATE 1.3.3 PHASE I DELIVERABLES THE CONTRACTOR SHALL PROVIDE: A PHASE I FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND FINAL CONCEPT SELECTED FOR DETAILED CONCEPTUAL DESIGN. DUE BY SEPTEMBER 30, 2015. PHASE II DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE II FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND CONCEPTUAL DESIGNS. DUE SEP 2016 2) AN NPSS FULL PROPULSION SYSTEM MODEL OF THE FINAL SYSTEM. THIS MODEL WILL INCLUDE TURBOMACHINERY PERFORMANCE MAPS, POWER REQUIREMENTS, WEIGHTS, AND VOLUMES FOR THE TURBOMACHINERY/GAS TURBINE ENGINE, ELECTRIC MOTOR PERFORMANCE MAPS, ENERGY STORAGE DEVICE PERFORMANCE CHARACTERISTICS, ELECTRICAL TRANSMISSION AND POWER CONDITIONING COMPONENTS, AND THERMAL MANAGEMENT SYSTEM. THIS MODEL WILL BE FOR GOVERNMENT USE ONLY. DUE SEP 2016 3) NPSS ELEMENTS, SUBELEMENTS, FUNCTIONS REQUIRED BY THE MODEL IN DELIVERABLE 2 OTHER THAN THOSE INCLUDED WITH THE NPSS PROGRAM WILL BE DELIVERED TO NASA FOR PUBLIC DISSEMINATION. DUE SEP 2016 4) A DETAILED TECHNOLOGY ROADMAP THAT SHOWS A CLEAR RESEARCH PATH TO ELEVATE THE KEY TECHNICAL CHALLENGES EMBODIED IN THE PREFERRED SYSTEM CONCEPT TO TRL 6 BY 2025. DUE SEP 2016 5) FOUR MONTHS BEFORE THE PROPOSED START OF PHASE III, CONTRACTOR WILL SUBMIT A PHASE III PROPOSAL TO INCLUDE PHASE III TASKS, DELIVERABLES, LABOR HOURS, PRICING, AND THE CONTRACTOR S COMMITMENT OF RESOURCES. NASA WILL CONSIDER THESE SUBJECTS AND THE CONTRACTOR S PROJECTED COMMITMENT OF RESOURCES TO PHASE III WHEN DETERMINING WHETHER TO EXERCISE OPTION 2. PHASE III DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE III FINAL REPORT, ADDRESSING THE INITIAL STEPS TO MATURING IDENTIFIED KEY TECHNICAL CHALLENGES IN THE PREFERRED SYSTEM CONCEPT UPON COMPLETION OF PHASE III (IF AWARDED). DUE SEPT 2019 2) FINAL NPSS MODEL INCLUDING ALL NECESSARY COMPONENT PERFORMANCE CHARACTERISTICS FOR GOVERNMENT USE ONLY. DUE SEPT 2019 | $186 |
| Sep 7, 2016 | Department of DefenseHQUSSOCOM | H9222216C0121 | 336413 | A KITS AND B KITS FOR AC-130W | $9.3M |
| Aug 26, 2016 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865013C5211 | 541712 | IGF::OT::IGF BEHAVIOR&LIFE PREDICTION FOR SIC/SIC CMCS FOR TURBINE APPLICATIONS: ENVIRONMENTAL DAMAGE MODELING | $79K |
| Aug 16, 2016 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC14CA29C | 541712 | IGF::OT::IGF SYSTEMS AND TECHNOLOGY STUDIES HAVE INDICATED THAT HYBRID GAS-ELECTRIC PROPULSION SYSTEMS FOR SUBSONIC TRANSPORT AIRCRAFT ARE POTENTIALLY FEASIBLE IN THE N+3 TIMEFRAME. FW PROJECT RESEARCH CURRENTLY FOCUSES ON TWO GENERAL ARCHITECTURE CONCEPTS: 1) A GAS-ELECTRIC HYBRID CONCEPT WHERE AT A MINIMUM GAS TURBINE AND STORED ELECTRIC ENERGY SOURCES DRIVE A SINGLE PROPULSOR THROUGH A COMMON SHAFT WITH THE POTENTIAL FOR USING ELECTRICAL ENERGY FROM STORED ENERGY OR TURBINE DRIVEN GENERATOR TO POWER ELECTRICAL MOTOR DRIVEN AUXILIARY OR REMOTE FANS, AND 2) A SINGLE GAS TURBINE ELECTRIC POWER SOURCE WHERE THE GAS TURBINE IS USED TO DRIVE A GENERATOR TO CONVERT ALL THE TURBINE POWER TO ELECTRICITY THAT IS THEN DISTRIBUTED TO MULTIPLE DISTRIBUTED ELECTRIC MOTOR DRIVEN PROPULSORS. THE FW PROJECT IS INVESTING IN ELECTRIC SYSTEM MATERIALS, ELECTRIC COMPONENTS, AND POWER MANAGEMENT AND DISTRIBUTION TECHNOLOGIES IN SUPPORT OF THESE SYSTEM ARCHITECTURE CONCEPTS AND CONFIGURATION STUDIES. TO COMPLEMENT EXISTING RESEARCH, SEVERAL SUBTOPICS WERE SOLICITED. THE LONG-TERM OBJECTIVE OF THIS RESEARCH IS TO EXPLORE THE DESIGN SPACE OF POTENTIAL ENGINE CYCLES, MOTOR, POWER CONVERSION, ENERGY STORAGE AND THERMAL MANAGEMENT TECHNOLOGIES FOR GAS-ELECTRIC HYBRID PROPULSION SYSTEMS TO IDENTIFY THE ARCHITECTURE WITH THE BEST PERFORMANCE AGAINST NASA N+3 OBJECTIVES (NOISE, EMISSIONS, ENERGY CONSUMPTION) FOR A 737/A320 CLASS SINGLE AISLE AIRCRAFT. BELOW IS A SUMMARY OF OBJECTIVES FOR EACH PHASE. TASK 1.1 NPSS MODELING AND CONCEPT DEFINITION TASK 1.2 - SYSTEM CONCEPTUAL DESIGN AND DOWN-SELECTION TASK 2.1 - DETAILED CONCEPTUAL DESIGN TASK 2.2 - TECHNOLOGY ROADMAP DEVELOPMENT TASK 3.1 - SUBSCALE ENERGY MANAGEMENT/ELECTRIC DRIVE DEVELOPMENT TASK 3.2 CONTROL SYSTEM PRELIMINARY DESIGN AND PERFORMANCE VALIDATION TASK 3.3 PROPULSION SYSTEM CONCEPTUAL DESIGN UPDATE 1.3.3 PHASE I DELIVERABLES THE CONTRACTOR SHALL PROVIDE: A PHASE I FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND FINAL CONCEPT SELECTED FOR DETAILED CONCEPTUAL DESIGN. DUE BY SEPTEMBER 30, 2015. PHASE II DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE II FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND CONCEPTUAL DESIGNS. DUE SEP 2016 2) AN NPSS FULL PROPULSION SYSTEM MODEL OF THE FINAL SYSTEM. THIS MODEL WILL INCLUDE TURBOMACHINERY PERFORMANCE MAPS, POWER REQUIREMENTS, WEIGHTS, AND VOLUMES FOR THE TURBOMACHINERY/GAS TURBINE ENGINE, ELECTRIC MOTOR PERFORMANCE MAPS, ENERGY STORAGE DEVICE PERFORMANCE CHARACTERISTICS, ELECTRICAL TRANSMISSION AND POWER CONDITIONING COMPONENTS, AND THERMAL MANAGEMENT SYSTEM. THIS MODEL WILL BE FOR GOVERNMENT USE ONLY. DUE SEP 2016 3) NPSS ELEMENTS, SUBELEMENTS, FUNCTIONS REQUIRED BY THE MODEL IN DELIVERABLE 2 OTHER THAN THOSE INCLUDED WITH THE NPSS PROGRAM WILL BE DELIVERED TO NASA FOR PUBLIC DISSEMINATION. DUE SEP 2016 4) A DETAILED TECHNOLOGY ROADMAP THAT SHOWS A CLEAR RESEARCH PATH TO ELEVATE THE KEY TECHNICAL CHALLENGES EMBODIED IN THE PREFERRED SYSTEM CONCEPT TO TRL 6 BY 2025. DUE SEP 2016 5) FOUR MONTHS BEFORE THE PROPOSED START OF PHASE III, CONTRACTOR WILL SUBMIT A PHASE III PROPOSAL TO INCLUDE PHASE III TASKS, DELIVERABLES, LABOR HOURS, PRICING, AND THE CONTRACTOR S COMMITMENT OF RESOURCES. NASA WILL CONSIDER THESE SUBJECTS AND THE CONTRACTOR S PROJECTED COMMITMENT OF RESOURCES TO PHASE III WHEN DETERMINING WHETHER TO EXERCISE OPTION 2. PHASE III DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE III FINAL REPORT, ADDRESSING THE INITIAL STEPS TO MATURING IDENTIFIED KEY TECHNICAL CHALLENGES IN THE PREFERRED SYSTEM CONCEPT UPON COMPLETION OF PHASE III (IF AWARDED). DUE SEPT 2019 2) FINAL NPSS MODEL INCLUDING ALL NECESSARY COMPONENT PERFORMANCE CHARACTERISTICS FOR GOVERNMENT USE ONLY. DUE SEPT 2019 | $100K |
| Jul 11, 2016 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865013C5211 | 541712 | IGF::OT::IGF BEHAVIOR&LIFE PREDICTION FOR SIC/SIC CMCS FOR TURBINE APPLICATIONS: ENVIRONMENTAL DAMAGE MODELING | $216K |
| Jun 14, 2016 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | NNC14CA29C | 541712 | IGF::OT::IGF SYSTEMS AND TECHNOLOGY STUDIES HAVE INDICATED THAT HYBRID GAS-ELECTRIC PROPULSION SYSTEMS FOR SUBSONIC TRANSPORT AIRCRAFT ARE POTENTIALLY FEASIBLE IN THE N+3 TIMEFRAME. FW PROJECT RESEARCH CURRENTLY FOCUSES ON TWO GENERAL ARCHITECTURE CONCEPTS: 1) A GAS-ELECTRIC HYBRID CONCEPT WHERE AT A MINIMUM GAS TURBINE AND STORED ELECTRIC ENERGY SOURCES DRIVE A SINGLE PROPULSOR THROUGH A COMMON SHAFT WITH THE POTENTIAL FOR USING ELECTRICAL ENERGY FROM STORED ENERGY OR TURBINE DRIVEN GENERATOR TO POWER ELECTRICAL MOTOR DRIVEN AUXILIARY OR REMOTE FANS, AND 2) A SINGLE GAS TURBINE ELECTRIC POWER SOURCE WHERE THE GAS TURBINE IS USED TO DRIVE A GENERATOR TO CONVERT ALL THE TURBINE POWER TO ELECTRICITY THAT IS THEN DISTRIBUTED TO MULTIPLE DISTRIBUTED ELECTRIC MOTOR DRIVEN PROPULSORS. THE FW PROJECT IS INVESTING IN ELECTRIC SYSTEM MATERIALS, ELECTRIC COMPONENTS, AND POWER MANAGEMENT AND DISTRIBUTION TECHNOLOGIES IN SUPPORT OF THESE SYSTEM ARCHITECTURE CONCEPTS AND CONFIGURATION STUDIES. TO COMPLEMENT EXISTING RESEARCH, SEVERAL SUBTOPICS WERE SOLICITED. THE LONG-TERM OBJECTIVE OF THIS RESEARCH IS TO EXPLORE THE DESIGN SPACE OF POTENTIAL ENGINE CYCLES, MOTOR, POWER CONVERSION, ENERGY STORAGE AND THERMAL MANAGEMENT TECHNOLOGIES FOR GAS-ELECTRIC HYBRID PROPULSION SYSTEMS TO IDENTIFY THE ARCHITECTURE WITH THE BEST PERFORMANCE AGAINST NASA N+3 OBJECTIVES (NOISE, EMISSIONS, ENERGY CONSUMPTION) FOR A 737/A320 CLASS SINGLE AISLE AIRCRAFT. BELOW IS A SUMMARY OF OBJECTIVES FOR EACH PHASE. TASK 1.1 NPSS MODELING AND CONCEPT DEFINITION TASK 1.2 - SYSTEM CONCEPTUAL DESIGN AND DOWN-SELECTION TASK 2.1 - DETAILED CONCEPTUAL DESIGN TASK 2.2 - TECHNOLOGY ROADMAP DEVELOPMENT TASK 3.1 - SUBSCALE ENERGY MANAGEMENT/ELECTRIC DRIVE DEVELOPMENT TASK 3.2 CONTROL SYSTEM PRELIMINARY DESIGN AND PERFORMANCE VALIDATION TASK 3.3 PROPULSION SYSTEM CONCEPTUAL DESIGN UPDATE 1.3.3 PHASE I DELIVERABLES THE CONTRACTOR SHALL PROVIDE: A PHASE I FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND FINAL CONCEPT SELECTED FOR DETAILED CONCEPTUAL DESIGN. DUE BY SEPTEMBER 30, 2015. PHASE II DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE II FINAL REPORT FOR PUBLIC DISSEMINATION DESCRIBING ANALYSIS OF ALTERNATIVES, DESIGN SPACE EXPLORATION, AND CONCEPTUAL DESIGNS. DUE SEP 2016 2) AN NPSS FULL PROPULSION SYSTEM MODEL OF THE FINAL SYSTEM. THIS MODEL WILL INCLUDE TURBOMACHINERY PERFORMANCE MAPS, POWER REQUIREMENTS, WEIGHTS, AND VOLUMES FOR THE TURBOMACHINERY/GAS TURBINE ENGINE, ELECTRIC MOTOR PERFORMANCE MAPS, ENERGY STORAGE DEVICE PERFORMANCE CHARACTERISTICS, ELECTRICAL TRANSMISSION AND POWER CONDITIONING COMPONENTS, AND THERMAL MANAGEMENT SYSTEM. THIS MODEL WILL BE FOR GOVERNMENT USE ONLY. DUE SEP 2016 3) NPSS ELEMENTS, SUBELEMENTS, FUNCTIONS REQUIRED BY THE MODEL IN DELIVERABLE 2 OTHER THAN THOSE INCLUDED WITH THE NPSS PROGRAM WILL BE DELIVERED TO NASA FOR PUBLIC DISSEMINATION. DUE SEP 2016 4) A DETAILED TECHNOLOGY ROADMAP THAT SHOWS A CLEAR RESEARCH PATH TO ELEVATE THE KEY TECHNICAL CHALLENGES EMBODIED IN THE PREFERRED SYSTEM CONCEPT TO TRL 6 BY 2025. DUE SEP 2016 5) FOUR MONTHS BEFORE THE PROPOSED START OF PHASE III, CONTRACTOR WILL SUBMIT A PHASE III PROPOSAL TO INCLUDE PHASE III TASKS, DELIVERABLES, LABOR HOURS, PRICING, AND THE CONTRACTOR S COMMITMENT OF RESOURCES. NASA WILL CONSIDER THESE SUBJECTS AND THE CONTRACTOR S PROJECTED COMMITMENT OF RESOURCES TO PHASE III WHEN DETERMINING WHETHER TO EXERCISE OPTION 2. PHASE III DELIVERABLES THE CONTRACTOR SHALL PROVIDE: 1) PHASE III FINAL REPORT, ADDRESSING THE INITIAL STEPS TO MATURING IDENTIFIED KEY TECHNICAL CHALLENGES IN THE PREFERRED SYSTEM CONCEPT UPON COMPLETION OF PHASE III (IF AWARDED). DUE SEPT 2019 2) FINAL NPSS MODEL INCLUDING ALL NECESSARY COMPONENT PERFORMANCE CHARACTERISTICS FOR GOVERNMENT USE ONLY. DUE SEPT 2019 | $100K |
| Mar 8, 2016 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865013C5211 | 541712 | IGF::OT::IGF BEHAVIOR&LIFE PREDICTION FOR SIC/SIC CMCS FOR TURBINE APPLICATIONS: ENVIRONMENTAL DAMAGE MODELING | $256K |
| Jan 29, 2016 | National Aeronautics and Space AdministrationGLENN RESEARCH CENTER | NNC11TA92T | 541712 | ADMINISTRATION AND BASELINE SECURITY | $25K |
| Jan 19, 2016 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | 0002 | 541712 | IGF::OT::IGF AIR SUPERIORITY TURBINE TECHNOLOGY EVALUATION (ASTTE) | $689K |
| Nov 25, 2015 | Department of DefenseNAVAL AIR SYSTEMS COMMAND | 0003 | 336412 | IGF::OT::IGF OPTION YEAR 2 FSR SUPPORT | $454K |
| Oct 28, 2015 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865013C5211 | 541712 | IGF::OT::IGF BEHAVIOR&LIFE PREDICTION FOR SIC/SIC CMCS FOR TURBINE APPLICATIONS: ENVIRONMENTAL DAMAGE MODELING | $193K |
| Oct 21, 2015 | National Aeronautics and Space AdministrationGLENN RESEARCH CENTER | NNC15TA69T | 541712 | IGF::OT::IGF "HIGH TEMPERATURE SEALS" | $174K |
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