SBIR/STTR Research Award
Fan Duct Heat Exchanger for Turbine Cooling Air
Award amount
$123,954Program and phase
SBIR · Phase IAward year
2016Award details
- Awarding agency
- National Aeronautics and Space Administration
- Branch
- Not reported
- Recipient company
- N&R ENGNERING MGT SUPPORT SVCS
- Proposal award date
- 2016-06-10
- Contract end date
- 2016-12-09
- UEI
- L3UNFWGGDL84
- Solicitation number
- Not reported
- Topic code
- A1.07
Research abstract
The proposal is for the design of a fan duct heat exchanger in order to improve aircraft fuel burn. The fan duct heat exchanger decreases the temperature of the 15% to 20% of compressor discharge air used to cool the High Pressure Turbine(HPT). Reducing the HPT cooling air temperature reduces the amount of cooling air needed for HPT cooling, and reducing vane and rotor blade cooling improves engine Specific Fuel Consumption(SFC). Fuel burn is adversely affected by any added engine weight due to the heat exchanger. Fan duct air is much colder than compressor discharge air, and can be used as a cold sink for cooling the HPT cooling air. Parametric analyses will be done to determine the SFC reduction as a function of cooling air temperature decrease. Pressure losses for both sides of the heat exchanger will be part of the analyses. The fan duct heat exchanger has large pressure differentials between the high pressure compressor discharge air and the relatively low pressure fan duct air. Structural analyses will be done for the heat exchanger to determine heat exchanger weight.
Technology keywords
Not reported
Other awards by this recipient
Verified by the same UEI. These are other public SBIR/STTR award pages, not a merged company record.
- Approaches to Facilitate Using HPT SiC/SiC CMC Vanes and Rotor Blades
- Probabilistic/Reliability Software Tool for Ceramic Matrix Composite/Environmental Barrier Coating Interface Modeling
- Probabilistic/Reliability Software Tool for Ceramic Matrix Composite/Environmental Barrier Coating Interface Modeling
- Hybrid Disk Fabrication by Linear Friction Welding
- Design Concepts for Low Aspect Ratio High Pressure Turbines for High Bypass Ratio Turbofans
Awards with the same topic code
Verified by an exact topic code match. This is not a text-similarity match.
- Injector-Integrated Fuel-Air Heat Exchanger Module
- A Mathematical Model to Assess CMAS Damage in EBCs
- Integrated Fluid and Materials Modeling of Environmental Barrier Coatings
- Low Cost Corrosion and Oxidation Resistant Coatings for Improved System Reliability
Research funding history
21 SBIR/STTR records share this UEI (2002–2020). Reported award amounts total $5,768,620. Reported amounts are not federal obligations.
Phases: Phase I, Phase II
Agencies: National Aeronautics and Space Administration, Department of Defense