The Collier Report of U.S. Government Contracting

Sampling of Federal Government Funding Actions/Set Asides

In order by amount of set aside monies.

• $9,811 - Thursday the 27th of October 2011
  Department Of Air Force
  FA8650 USAF AFMC AFRL/RQK
  HIT RT - INCREMENTAL FUNDING

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• $90,000 - Wednesday the 20th of June 2012
  Department Of Air Force
  FA8650 USAF AFMC AFRL/RQK
  LOW PRESSURE TURBINE RESEARCH

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• $46,907 - Friday the 10th of July 2015
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  FTT PROPOSES DEVELOPMENT OF A MAGNETICALLY ACTUATED DYNAMIC SEAL. DYNAMIC SEALS ARE USED THROUGHOUT THE TURBOPUMP IN HIGH-PERFORMANCE, PUMP-FED, LIQUID ROCKET ENGINES FOR A VARIETY OF PURPOSES. THE MOST COMMON APPLICATIONS ARE IN THE LIFT-OFF SEAL (LOS), INTER-PROPELLANT SEAL (IPS), AND BALANCE PISTON SEALS HIGH-PRESSURE ORIFICE (HPO), LOW-PRESSURE ORIFICE (LPO), AND INNER DIAMETER IMPELLER SHROUD SEAL (EYE SEAL). THE SYSTEM SOLUTION FOR CONVENTIONAL SEALS REPRESENTS A COMPROMISE BETWEEN THE TURBOPUMP MECHANICAL DESIGN, PRIMARILY FLOWPATH, AND SECONDARY FLOWPATH DESIGN THAT RESULTS IN INCREASED LEAKAGE, INCREASED SEAL WEAR, AND REDUCED BALANCE PISTON LOAD CAPACITY THAT REDUCES PERFORMANCE, THROTTLE-ABILITY, THRUST-TO-WEIGHT, RELIABILITY, AND OPERABILITY. THE MAGNETICALLY ACTUATED SEAL ELIMINATES THIS COMPROMISE AND PROVIDES SIGNIFICANT IMPROVEMENT IN PERFORMANCE, THROTTLE-ABILITY, THRUST-TO-WEIGHT, RELIABILITY, AND OPERABILITY. PHASE 1 RESULTED IN A SIGNIFICANT ADVANCEMENT OF THE TECHNOLOGY BY DEMONSTRATING A MAGNETICALLY ACTUATED FACE SEAL IN BOTH AMBIENT AND CRYOGENIC CONDITIONS, CHARACTERIZING THE SEAL AND ACTUATOR PERFORMANCE, AND QUANTIFYING THE PERFORMANCE IMPROVEMENTS FOR THE TURBOPUMP AND ENGINE. PHASE 2 WILL ADVANCE THE TECHNOLOGY FROM TRL 3 TO 5. THE TECHNOLOGY IS APPLICABLE TO BOOSTER ENGINES, IN-SPACE ENGINES, AND ASCENT/DESCENT ENGINES.

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• $33,974 - Thursday the 2nd of February 2012
  Department Of Air Force
  FA8650 USAF AFMC AFRL/RQK
  SBIR II-CORE DEMO FOR HIGHLY EFFICIENT MINI TURBOFAN-OVERRUN AND MODIFY GFP

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• $200,000 - Friday the 9th of March 2012
  Department Of Air Force
  FA8650 USAF AFMC AFRL/RQK
  HIGH IMPACT TECHNOLOGY RESEARCH TURBINE RIG

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• $124,941 - Thursday the 4th of October 2012
  National Aeronautics And Space Administration
  NASA SHARED SERVICES CENTER
  FTT PROPOSES DEVELOPMENT OF A ROTATING CAVITATION (RC) SUPPRESSOR FOR LIQUID ROCKET ENGINE TURBOPUMP INDUCERS. CAVITATION INSTABILITIES, SUCH AS ROTATING CAVITATION, HAVE CAUSED SEVERE DAMAGE TO BEARINGS AND SEALS, FATIGUE FAILURES, AND EVEN CATASTROPHIC FAILURES OF ROCKET ENGINES. IN ADDITION, CAVITATION INSTABILITIES HAMPER SUCTION PERFORMANCE, WHICH PREVENTS DEVELOPMENTS RELATED TO INCREASING PAYLOAD BY REDUCING OVERALL VEHICLE WEIGHT WITH THINNER PROPELLANT TANK WALLS. AN RC SUPPRESSOR WILL ALLOW FOR INCREASED SUCTION PERFORMANCE AND FOR IMPROVED TURBOPUMP RELIABILITY BY REDUCING LOADS ON THE ROTOR SUPPORT SYSTEM. THIS TECHNOLOGY HAS APPLICATIONS FOR ANY ROCKET ENGINE TURBOPUMP OR COMMERCIAL PUMP. FTT'S APPROACH WILL MATURE THE CONCEPTUAL DESIGN FOR THE SLOTTED ANNULAR CAVITATION SUPPRESSOR (SACS), COMPARE RESULTS OF COMPUTATIONAL FLUID DYNAMICS (CFD) OF A BASELINE INDUCER WITH AND WITHOUT THE SACS, CREATE A TEST PLAN, AND GENERATE A CONCEPTUAL DESIGN OF A TEST ARTICLE TO TEST THE SACS. PHASE I WILL ADVANCE THIS TECHNOLOGY FROM TRL 2 TO TRL 3. PHASE II WILL CULMINATE WITH WATER TESTING OF THE RC SUPPRESSOR AND DATA REDUCTION, AND WILL ADVANCE IT TO TRL 5.

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