The proposed work advances the NASA Aeronautics program goal of reduced fuel burn by using a fan duct heat exchanger. Reducing fuel burn, and the consequent reduction of CO2 emissions, is a goal of the Environmentally Responsible Aviation(ERA) component of the NASA Aeronautics program. A fan duct heat exchanger reduces both HPT first stage vane and rotor blade cooling requirements when T40 and T41 are unchanged. Precooling vane coolant air also permits a smaller temperature difference between the combustor outlet temperature, T40, and the rotor inlet temperature, T41. If T40 decreases, NOx production is decreased, since NOx is very sensitive to T40 . If T41 is increased, SFC improves due to a higher rotor inlet temperature. To quantify fuel burn reduction the heat exchanger weight must be known. Applications where the fuel-to-payload fraction is high, or where there is a premium for reduced fuel consumption benefit from a light weight fan duct heat exchanger. The primary benefit of increased turbine inlet temperature is in the reduction of SFC.
The proposed work advances the NASA Aeronautics program goal of reduced fuel burn by using a fan duct heat exchanger. Reducing fuel burn, and the consequent reduction of CO2 emissions, is a goal of the Environmentally Responsible Aviation(ERA) component of the NASA Aeronautics program. A fan duct heat exchanger reduces both HPT first stage vane and rotor blade cooling requirements when T40 and T41 are unchanged. Precooling vane coolant air also permits a smaller temperature difference between the combustor outlet temperature, T40, and the rotor inlet temperature, T41. If T40 decreases, NOx production is decreased, since NOx is very sensitive to T40 . If T41 is increased, SFC improves due to a higher rotor inlet temperature. To quantify fuel burn reduction the heat exchanger weight must be known. Applications where the fuel-to-payload fraction is high, or where there is a premium for reduced fuel consumption benefit from a light weight fan duct heat exchanger. The primary benefit of increased turbine inlet temperature is in the reduction of SFC.
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