Structurally Embedded Heat Exchanger

ABSTRACT: Materials used in high pressure turbine blades limit the life and temperature capability of the component, and thus the attainable thrust or power of the turbine engine.Lowering the temperature of the HP turbine blade cooling air will improve the heat transfer, resulting in lower metal temperatures which allow higher Rotor Inlet Temperature , or conversely longer blade life if the RIT remains the same. Since the air used to cool the turbine blades is compressor discharge air, a lower temperature air stream such as the fan bypass flow stream has a significantly lower temperature (depending on the engine, in the order of 800 R) which can be used in a conformal, structurally embedded heat exchanger to lower the temperature of the cooling air, while adding the extracted heat energy to the bypass flow stream.By utilizing existing components located within the fan bypass stream, an integral, embedded heat exchanger can be designed, which would run the hot compressor bleed/cooling air through the embedded heat exchanger, providing improved heat transfer and blade cooling effectiveness, which can enhance temperature capability and or life or both, with the resulting benefits of higher thrust without compromising blade life, or simply longer life.; BENEFIT: The ability to significantly lower the temperature of the turbine blades cooling air translates into higher engine thrust capability, longer turbine blade life, and or both. The implication of the enhanced thrust, resulting from the higher Rotor Inlet Temperature, is that a throttle push can be accomplished without decreasing blade life, thus enabling higher aircraft performance, i.e. take off, climb, and cruise power, without compromising engine time on wing.If the Rotor Inlet Temperature is maintained at the previous rating and cooled cooling air is provided, then the life of the turbine blade will be significantly improved:as a rule of thumb, every 25 degrees Fahrenheit will reduce blade life by 50%, hence cooled cooling air in this case will in turn result in longer blade life and engine hot section replacement intervals, and therefore also longer engine time on wing, which of course is a direct operating cost reduction, as well as a an enhancement on readiness and mission capability.