ROLLSROYCE NORTH AMERICAN TECHNOLOGIES

ADVENT

SUPERSONIC TURBINE ENGINE FOR LONG RANGE (STELR) DEMO

EFFICIENT MEDIUM SCALE PROPULSION TECHNOLOGIES

HIGHLY EFFICIENT EMBEDDED TURBINE ENGINE

A KITS AND B KITS FOR AC-130W

REUSABLE HIGH MACH TURBINE ENGINE TECHNOLOGIES

SUBSONIC EXPENDABLE TURBINE ENGINE TECHNOLOGIES

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INTEGRATED POWER AND THERMAL MANAGEMENT DEVELOPMENT SYSTEM

LIFTFAN CAPABILITY IMPROVEMENT AND COST REDUCTION

VULCAN PROGRAM- PHASE I

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

AMPI: PRECISION THIN WALL AIRFOIL CASTINGS

ADVANCED ENGINE SUSTAINMENT TECHNOLOGIES

HIGHLY EFFICIENT EMBEDDED TURBINE ENGINE (HEETE) VISION SYSTEM STUDY

2700 F SIC/SIC CMC FOR HOT TURBINE SECTION COMPONENTS

BASE YEAR FSR SUPPORT AND TRAVEL

IGF::OT::IGF BEHAVIOR&LIFE PREDICTION FOR SIC/SIC CMCS FOR TURBINE APPLICATIONS: ENVIRONMENTAL DAMAGE MODELING

IDIQ

RESEARCH AND DEVELOPMENT IN THE PHYSICAL, ENGINEERING, AND LIFE SCIENCES (EXCEPT BIOTECHNOLOGY)

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

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.

TAS::57 3605::TAS VAATE PROGRAM - MATERIALS FOR GREEN PROPULSION

IDIQ

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.

AGGRESSIVE EMBEDDED PROPULSION OPERABILITY (AEPO)

IGF::OT::IGF DISTROTION TESTING OF MODERATE BYPASS RATIO FAN

FISSION SURFACE POWER ADVANCED CLOSED BRAYTON CONVERTOR (FSP-ACBC) SYSTEM NRA AWARD

TAS::57 3605::TAS ADAPTIVE COMBUSTOR TECHOLOGY FOR HIGHLY EFFICIENT EMBEDDED TURBINE ENGINE (HEETE) PROGRAM

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.

ADAPTIVE ENGINE TECHNOLOGY MATURATION INTEGRATION (AETMI) ST

DEVELOPMENT OF THE DECENTRALIZED ENGINE CONTROL SYSTEM SIMULATOR FOR SYSTEM AND COMPONENT TESTING AND EVALUATION: LIBERTYWORKS SHALL DEVELOP AN INTEGRATED ENVIRONMENT FOR THE DESIGN, DEVELOPMENT, TESTING, AND INTEGRATION OF CURRENT AND FUTURE GAS TURBINE ENGINE CONTROL SYSTEMS WITH CAPABILITIES TO SUPPORT FLEXIBLE, DECENTRALIZED CONTROL SYSTEM ARCHITECTURES UTILIZING BOTH SIMULATED AND PHYSICAL HARDWARE CONTROL COMPONENTS. THIS HARDWARE-IN-THE-LOOP SYSTEM, ALSO REFERENCED AS THE DECENTRALIZED ENGINE CONTROL SYSTEM SIMULATOR (DECSS), WILL BE DEVELOPED, TESTED, DOCUMENTED, AND DELIVERED TO NASA GLENN RESEARCH CENTER (GRC) FOR ACCESS BY GOVERNMENT AND COMMERCIAL ENTITIES AS DIRECTED BY THE NASA GRC HOST. AS ALL PROGRAMS WORKED BY ROLLS-ROYCE, THIS PROGRAM WILL BE DEVELOPED USING ROLLS-ROYCE DESIGN PRACTICE AND QUALITY PROCESS FOR DEVELOPMENT AND SUPPORT HARDWARE AS DEFINED IN THE ROLLS-ROYCE QUALITY MANAGEMENT SYSTEM. IN THE INTEREST TO CONTROL COSTS AND SINCE THE DECSS IS NOT A FLIGHT SYSTEM, CERTIFICATION TO AS9100 IS BEYOND THE SCOPE OF THIS PROGRAM. THIS SCOPE LIMITATION DOES NOT PRECLUDE CERTIFICATION AT A LATER DATE IF AND WHEN APPROPRIATE.

PHASE II COMBUSTION RULES AND TOOLS...ALTERNATE FUELS

IGF::OT::IGF "HIGH TEMPERATURE SEALS"

INVENT-SDD - REPS

IGF::OT::IGF AIR SUPERIORITY TURBINE TECHNOLOGY EVALUATION (ASTTE)

FULL PROPULSION FLOWPATH DEMONSTRATION CONCEPTUAL DESIGN

IGF::OT::IGF OPTION YEAR 2 FSR SUPPORT

HIGH FIDELITY SUPERSONIC EXHAUST SYSTEM DESIGN AND VALIDATION MODEL SCOPE OF WORK THIS SOW COVERS THE MECHANICAL DESIGN (BASE PERIOD), BASED ON COMPUTATIONAL FLUID DYNAMIC (CFD) ANALYSIS, AND THE MANUFACTURE (OPTION PERIOD) OF A HIGHLY VARIABLE CYCLE (HVC) EXHAUST SYSTEM VALIDATION MODEL THAT WILL ADAPT TO THE HIGH FLOW JET EXIT RIG (HFJER) IN THE AERO-ACOUSTIC PROPULSION LABORATORY (AAPL) AT NASA GLENN RESEARCH CENTER. FABRICATION (OPTION PERIOD) IS CONDITIONAL UPON A SATISFACTORY CRITICAL DESIGN REVIEW (CDR) AND AN ACCEPTABLE HARDWARE COST ESTIMATE. THE NEW HVC EXHAUST SYSTEM MODEL INCORPORATES COMPONENTS THAT WERE REDESIGNED AFTER ANALYSIS OF RESULTS OBTAINED FROM EXPERIMENTS CONDUCTED WITH SUPERSONIC BUSINESS JET (SSBJ) EXHAUST SYSTEM IN 2003. TASKS/TECHNICAL REQUIREMENTS: WBS 1.0 - DELIVER COMPUTATIONAL FLUID DYNAMIC ANALYSIS RESULTS FOR HVC EXHAUST MODEL. THE CONTRACTOR SHALL DELIVER COMPUTATIONAL FLUID DYNAMIC ANALYSIS RESULTS FOR THE PROPOSED HVC. THE ANALYSIS SHALL INCLUDE STEADY STATE FLOW QUANTITIES AND PREDICTED PERFORMANCE AT THE DESIGN POINT, A SEA LEVEL TAKE-OFF POINT, AND A CRUISE POINT AT 50,000 FT ALTITUDE AND A MACH NUMBER OF 1.8. WBS 2.0 - DELIVER REPRESENTATIVE MODEL CYCLE LINES INCLUDING OPERATING PRESSURES AND TEMPERATURES. THE CONTRACTOR SHALL DELIVER REPRESENTATIVE MODEL CYCLE LINES INCLUDING OPERATING PRESSURES AND TEMPERATURES. WBS 3.0 - DEFINE, DIRECT, AND COMPLETE THE DETAILED MECHANICAL DESIGN FOR HVC EXHAUST SYSTEM MODEL. THE CONTRACTOR SHALL DEVELOP A DETAILED DESIGN FOR THE HVC EXHAUST MODEL SHOWN IN FIGURE 1 USING ELECTRONIC SURFACE MODELS FROM THE AERO-DESIGNS AS IGES FILES. THE MODEL SHALL ADAPT TO THE HFJER WITHIN THE AAPL AT NASA GLENN RESEARCH CENTER. THE RIG INTERFACE POINTS FOR THE MODEL SHALL BE THE CHARGING STATION FAN DUCT (NASA DRAWING CE-645707), THE CHARGING STATION CORE DUCT (NASA DRAWING CE-645708), AND THE CORE TAILCONE WELDMENT (NASA DRAWING CF-645686). THE MODEL SHALL INCLUDE AN EXHAUST TAILCONE, A TRANSLATING FORCED LOBE MIXER WITH MANUAL AXIAL SETTINGS, A VARIABLE PRIMARY NOZZLE THROAT SECTION FOR SEA LEVEL TAKE-OFF SETTINGS, AND A VARIABLE SECONDARY NOZZLE WITH REMOTELY ACTUATE CLAM SHELL DOORS. MODEL COMPONENTS SHALL ADHERE TO REQUIREMENTS SPECIFIED (IN OTHER DOCUMENTS PROVIDED). THE CONTRACTOR SHALL PERFORM THE FOLLOWING SPECIFIC TASK ELEMENTS: 3.1 IDENTIFY MODEL WORKING RANGE INCLUDING ALLOWABLE OPERATING PRESSURES AND TEMPERATURES 3.2 PREPARE A GEOMETRY DATA PACKAGE 3.3 DEFINE INSTRUMENTATION TO PROVIDE FOR ADEQUATE COMPUTATIONAL FLUID DYNAMICS AERODYNAMICS COMPARISONS (PRELIMINARY ESTIMATES ASSUME 10 TEMPERATURES AND 100 PRESSURE PROBES). 3.4 PREPARE A REQUIREMENTS DOCUMENT DEFINING TEST OPERATING CONDITIONS AND VARIABLES DEPLOYMENT 3.5 CONDUCT A PRELIMINARY DESIGN REVIEW (PDR) AT NASA GLENN RESEARCH CENTER 3.6 DEVELOP A DETAILED MECHANICAL DESIGN FOR THE MODEL NOZZLE AND LOCATE TEST INSTRUMENTATION ON THE TEST MODEL. 3.7 CDR AT NASA GLENN RESEARCH CENTER 3.8 DELIVER STRESS REPORT OF CALCULATIONS DEMONSTRATING SAFETY FACTORS AT THE OPERATING CONDITIONS DEFINED FOR PERFORMANCE OF WBS 2.0 AND AT MAXIMUM ALLOWABLE MODEL TEMPERATURES AND PRESSURES. 3.9 DELIVER COST ESTIMATE FOR HVC EXHAUST MODEL. WBS 4.0 - DELIVER REPORTS AND PRESENTATIONS. 4.1 THE CONTRACTOR SHALL DELIVER MONTHLY TECHNICAL REPORTS 4.2 THE CONTRACTOR SHALL DELIVER A FINAL PRESENTATION 4.3 THE CONTRACTOR SHALL DELIVER A FINAL REPORT OPTION 1 (FABRICATION): IF OPTION 1 IS EXERCISED, THE FOLLOWING TASKS SHALL BE COMPLETED: WBS 5.0 - FABRICATE THE HVC SUPERSONIC EXHAUST NOZZLE MODEL. THE CONTRACTOR SHALL FABRICATE THE HVC EXHAUST NOZZLE MODEL AS SPECIFIED BY THE REQUIREMENTS DOCUMENT DEVELOPED DURING PERFORMANCE OF WBS 3.0. THE CONTRACTOR SHALL PERFORM THE FOLLOWING SPECIFIC TASK ELEMENTS: 5.1 FABRICATE PARTS FOR THE HVC EXHAUST NOZZLE MODEL 5.2 TRIAL FIT MODEL PARTS, TRIM, ASSEMBLE, AND INSTALL TEST INSTRUMENTATION 5.3

OPTIMIZED PROPULSION TECHNOLOGIES FOR INTENDED MISSION LIFE (OPTIML)

NEW TASK ORDER

IGF::OT::IGF TASK ORDER NNC13TA77T FOR ARCHITECTURE,VOLTAGE AND COMPONENTS FOR A TURBOELECTRIC DISTRIBUTED PROPULSION ELECTRIC GRID RESEARCH STUDY

MODELING POWER MANAGEMENT SYSTEMS

IGF::OT::IGF OPTION YEAR 1 FSR SUPPORT

VAATE - DEVELOPMENT OF COMBUSTION RULES AND TOOLS FOR THE CHARACTERIZATION OF ALERNATIVE FUELS PROGRAM

ENHANCED TBC STRUCTURE

TASK ORDER NNC11TA51T, ROLLS ROYCE NORTH AMERCIAN TECHNOLOGIES INC. ENTITLED " STABILITY, TRANSIENT RESPONSE, CONTROL AND SAFETY OF A HIGH-POWER ELECTRIC GRID FOR TURBOELECTRIC DISTRIBUTED PROPULSION OF AIRCRAFT UNDER TASK ORDER NNC11TA51T

NEW TO