Federal Contractor Profile
Rolls-royce North American Technologies INC
$96.9M obligated·60 awards·2 agencies·7 NAICS
Federal Contracts
Showing contracts 51–100 of 132 total. Sorted by action date, most recent first. Excludes $0 modifications.
| Date | Agency | PIID | NAICS | Description | Amount |
|---|---|---|---|---|---|
| Apr 22, 2021 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865021F2007 | 541715 | REUSABLE HIGH MACH TURBINE ENGINE TECHNOLOGIES | $884K |
| Mar 24, 2021 | Department of DefenseOFFICE OF NAVAL RESEARCH | N0001420C1063 | 541715 | LIFTFAN CAPABILITY IMPROVEMENT AND COST REDUCTION | $1.2M |
| Mar 11, 2021 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865021F2007 | 541715 | REUSABLE HIGH MACH TURBINE ENGINE TECHNOLOGIES | $1.8M |
| Mar 9, 2021 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $2.9M |
| Jan 21, 2021 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2108 | 541715 | ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES | $200K |
| Dec 23, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865021F2008 | 541715 | MODELING POWER MANAGEMENT SYSTEMS | $436K |
| Dec 11, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2093 | 541715 | SUBSONIC EXPENDABLE TURBINE ENGINE TECHNOLOGIES | $519K |
| Nov 5, 2020 | 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 | $361K |
| Oct 26, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865021F2209 | 541715 | FULL PROPULSION FLOWPATH DEMONSTRATION CONCEPTUAL DESIGN | $249K |
| Sep 29, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2093 | 541715 | SUBSONIC EXPENDABLE TURBINE ENGINE TECHNOLOGIES | $254K |
| Aug 27, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2108 | 541715 | ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES | $100K |
| Jul 2, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $1.4M |
| Apr 27, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $782K |
| Apr 22, 2020 | National Aeronautics and Space AdministrationNASA ARMSTRONG FLIGHT RESEARCH CNTR | 80AFRC20C0012 | 541330 | THE OBJECTIVE OF THIS REQUIREMENT IS TO ASSIST NASA IN REDUCING THE RISK AND COST OF POTENTIAL FUTURE FLIGHT DEMONSTRATION PROCUREMENT(S) THAT SUPPORT THE ACCOMPLISHMENT OF MID- AND FAR- TERM COMMUNITY OUTCOME. | $1.2M |
| Apr 17, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2108 | 541715 | ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES | $173K |
| Apr 6, 2020 | Department of DefenseOFFICE OF NAVAL RESEARCH | N0001420C1063 | 541715 | LIFTFAN CAPABILITY IMPROVEMENT AND COST REDUCTION | $2.0M |
| Jan 7, 2020 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $331K |
| Dec 17, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2108 | 541715 | ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES | $115K |
| Nov 27, 2019 | 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 | $353K |
| Nov 25, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $300K |
| Oct 31, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2108 | 541715 | ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES | $50K |
| Oct 24, 2019 | 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. | $19K |
| Jul 23, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $82K |
| Jul 17, 2019 | 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. | $7K |
| Jun 25, 2019 | 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. | $3K |
| May 2, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | 0010 | 541712 | SUPERSONIC TURBINE ENGINE FOR LONG RANGE (STELR) DEMO | $259K |
| May 1, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017F2217 | 541712 | IGF::OT::IGF DISTROTION TESTING OF MODERATE BYPASS RATIO FAN | $78K |
| Mar 7, 2019 | 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 | $360 |
| Feb 22, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017F2217 | 541712 | IGF::OT::IGF DISTROTION TESTING OF MODERATE BYPASS RATIO FAN | $42K |
| Feb 4, 2019 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2093 | 541715 | SUBSONIC EXPENDABLE TURBINE ENGINE TECHNOLOGIES | $81K |
| Nov 27, 2018 | 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 | $388K |
| Nov 26, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2108 | 541715 | ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES | $150K |
| Nov 26, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2108 | 541715 | ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES | $110K |
| Nov 1, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $372K |
| Oct 11, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865019F2078 | 541715 | EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES | $17K |
| Sep 21, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | 0010 | 541712 | SUPERSONIC TURBINE ENGINE FOR LONG RANGE (STELR) DEMO | $1.4M |
| Sep 21, 2018 | Department of DefenseHQ USSOCOM | H9222216C0121 | 336413 | A KITS AND B KITS FOR AC-130W | $47K |
| Aug 31, 2018 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017F2217 | 541712 | IGF::OT::IGF DISTROTION TESTING OF MODERATE BYPASS RATIO FAN | $500K |
| Jun 14, 2018 | Department of DefenseHQUSSOCOM | H9222216C0121 | 336413 | A KITS AND B KITS FOR AC-130W | $1.5M |
| Apr 30, 2018 | 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. | $38K |
| Apr 23, 2018 | 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 | $420K |
| Mar 9, 2018 | 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. | $350K |
| Feb 23, 2018 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | 80GRC018F0010 | 541712 | TASK ORDER 80GRC018F0010 FOR UNDERSTANDING ICE CRYSTAL ICING EFFECTS IN TURBOFAN ENGINES AND COMPRESSOR RIGS . ASPART OF THE ADVANCED AIR VEHICLE PROGRAM (AAVP), ADVANCED AIR TRANSPORT TECHNOLOGY PROJECT (AATT), NASA GLENN RESEARCH CENTER (GRC) WISHES TO PARTNER WITH COMMERCIAL ENGINE MANUFACTURERS TO INVESTIGATE THE MECHANISMS OF ICE CRYSTAL ICING INSIDE OF A TURBOFAN ENGINES. THE NASA PROPULSIONS SYSTEMS LABORATORY (PSL-3) HAS THE CAPABILITY TO PERFORM ICING INVESTIGATIONS ON FULL SCALE ENGINES, COMPRESSOR RIGS, AND COMPONENTS. FACILITY CALIBRATION, VALIDATION, AND TEST METHODOLOGIES FOR ICE CRYSTAL ICING TESTING ARE STILL BEING ESTABLISHED TO ENSURE PSL HAS WORLD-CLASS ICING CAPABILITY. PERFORMING AN EXPERIMENTAL ANALYSIS ON A WIDE RANGE OF TURBOFAN ENGINE AND CORES IN PSL IS CRUCIAL TO IMPROVING THE CAPABILITY OF THE FACILITY AND GENERATE DATASETS THAT CAN BE USED TO DEVELOP CODES FOR EVALUATING THE N+2/N+3 AIRCRAFT DESIGNS. THE GOAL OF THE NASA AATT PROJECT IS TO EXPAND THE ENGINE AEROTHERMODYNAMIC MODELING CAPABILITY TO PREDICTIVELY ASSESS THE ONSET OF ICING IN CURRENT AND N+2/ N+3 AIRCRAFT DURING FLIGHT OPERATIONS. THIS WILL BE ACHIEVED BY PERFORMING A SERIES OF FUNDAMENTAL ICE CRYSTAL PHYSICS EXPERIMENTS TO IDENTIFY CONDITIONS FAVORABLE FOR ICE ACCRETION AND THE RATE OF ICE GROWTH. ENGINE TESTS WILL EXPLORE THESE CONDITIONS AND PROVIDE DATA TO BE USED FOR MODEL VERIFICATION AND VALIDATION. 0D/1D AND 3D MODELING AND ANALYSIS TOOLS WILL BE DEVELOPED TO ASSESS THE RISK OF ICE ACCRETION AND EVALUATE THE ACCRETION ON THE COMPRESSOR. AATT IS FOCUSED ON DEVELOPING AND DEMONSTRATING MODELING CAPABILITIES BY THE 2021 TIMEFRAME. | $100K |
| Feb 21, 2018 | Department of DefenseHQUSSOCOM | H9222216C0121 | 336413 | A KITS AND B KITS FOR AC-130W | $5.9M |
| Dec 22, 2017 | National Aeronautics and Space AdministrationNASA GLENN RESEARCH CENTER | 80GRC018F0010 | 541712 | TASK ORDER 80GRC018F0010 FOR UNDERSTANDING ICE CRYSTAL ICING EFFECTS IN TURBOFAN ENGINES AND COMPRESSOR RIGS . ASPART OF THE ADVANCED AIR VEHICLE PROGRAM (AAVP), ADVANCED AIR TRANSPORT TECHNOLOGY PROJECT (AATT), NASA GLENN RESEARCH CENTER (GRC) WISHES TO PARTNER WITH COMMERCIAL ENGINE MANUFACTURERS TO INVESTIGATE THE MECHANISMS OF ICE CRYSTAL ICING INSIDE OF A TURBOFAN ENGINES. THE NASA PROPULSIONS SYSTEMS LABORATORY (PSL-3) HAS THE CAPABILITY TO PERFORM ICING INVESTIGATIONS ON FULL SCALE ENGINES, COMPRESSOR RIGS, AND COMPONENTS. FACILITY CALIBRATION, VALIDATION, AND TEST METHODOLOGIES FOR ICE CRYSTAL ICING TESTING ARE STILL BEING ESTABLISHED TO ENSURE PSL HAS WORLD-CLASS ICING CAPABILITY. PERFORMING AN EXPERIMENTAL ANALYSIS ON A WIDE RANGE OF TURBOFAN ENGINE AND CORES IN PSL IS CRUCIAL TO IMPROVING THE CAPABILITY OF THE FACILITY AND GENERATE DATASETS THAT CAN BE USED TO DEVELOP CODES FOR EVALUATING THE N+2/N+3 AIRCRAFT DESIGNS. THE GOAL OF THE NASA AATT PROJECT IS TO EXPAND THE ENGINE AEROTHERMODYNAMIC MODELING CAPABILITY TO PREDICTIVELY ASSESS THE ONSET OF ICING IN CURRENT AND N+2/ N+3 AIRCRAFT DURING FLIGHT OPERATIONS. THIS WILL BE ACHIEVED BY PERFORMING A SERIES OF FUNDAMENTAL ICE CRYSTAL PHYSICS EXPERIMENTS TO IDENTIFY CONDITIONS FAVORABLE FOR ICE ACCRETION AND THE RATE OF ICE GROWTH. ENGINE TESTS WILL EXPLORE THESE CONDITIONS AND PROVIDE DATA TO BE USED FOR MODEL VERIFICATION AND VALIDATION. 0D/1D AND 3D MODELING AND ANALYSIS TOOLS WILL BE DEVELOPED TO ASSESS THE RISK OF ICE ACCRETION AND EVALUATE THE ACCRETION ON THE COMPRESSOR. AATT IS FOCUSED ON DEVELOPING AND DEMONSTRATING MODELING CAPABILITIES BY THE 2021 TIMEFRAME. | $60K |
| Nov 21, 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 | $390K |
| Oct 24, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865007C2803 | 541710 | ADVENT | $1.9M |
| Oct 5, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017F2217 | 541712 | IGF::OT::IGF DISTROTION TESTING OF MODERATE BYPASS RATIO FAN | $250K |
| Sep 30, 2017 | Department of DefenseHQUSSOCOM | H9222216C0121 | 336413 | A KITS AND B KITS FOR AC-130W | $949K |
| Sep 8, 2017 | Department of DefenseFA8650 USAF AFMC AFRL PZL AFRL/PZL | FA865017F2217 | 541712 | IGF::OT::IGF DISTROTION TESTING OF MODERATE BYPASS RATIO FAN | $200K |
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