GEARED GAS TURBINE ENGINE ARCHITECTURE FOR ENHANCED EFFICIENCY

摘要

An example gas turbine engine includes, among other things, a geared architecture rotatably coupled to the fan drive shaft, and a high pressure compressor. The gas turbine engine is configured so that a core temperature at an exit of the high-pressure compressor is approximately in a range of about 1150 to about 1350 degrees Fahrenheit at take-off. The gas turbine engine is configured so that an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to a primary stream exhaust velocity, is approximately in a range of about 0.75 to about 0.90. A Bypass Ratio of the engine is greater than about 8.0.

主权项

1. A gas turbine engine comprising:
a fan having a drive shaft, the fan being configured to direct air into a bypass duct and into an engine core; a geared architecture rotatably coupled to the fan drive shaft; and a first compressor section, wherein the gas turbine engine is configured to have a core temperature at an exit of the first compressor section is in a range of about 1150 to about 1350 degrees Fahrenheit at take-off, wherein the gas turbine engine is configured so that a ratio of a fan stream exhaust velocity divided by a primary stream exhaust velocity is in a range of about 0.75 to about 0.90, wherein a ratio of a volume of air passing into the bypass duct divided by a volume of air passing into the engine core is greater than about 8.0.