Efficient, Low Pressure Ratio Propulsor for Gas Turbine Engines

Gallagher, Edward J [Inventor]Monzon, Byron R [Inventor]Bugaj, Shari L [Inventor]

关键词: GAS TURBINE ENGINES;    PRESSURE RATIO;    SHAFTS (MACHINE ELEMENTS);    FAN BLADES;    PATENTS;   

RP-ID  :  US-Patent-10,012,150, US-Patent-Appl-SN-15/233,142

学科分类：航空航天科学

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

A gas turbine engine includes a gear assembly and a bypass flow passage that includes an inlet and an outlet that define a design pressure ratio between 1.3 and 1.55. A fan is arranged at the inlet. A first turbine is coupled with a first shaft such that rotation of the first turbine will drive the fan, through the first shaft and the gear assembly, at a lower speed than the first shaft. The fan includes a row of fan blades. The row includes 12-16 (N) fan blades, a solidity value (R) that is from 1.0 to 1.3, and a ratio of N/R that is from 10.0 to 16.