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;    INLET FLOW;    CORE FLOW;    BYPASSES;    LOW PRESSURE;    PATENTS;    INVENTIONS;   

RP-ID  :  US-Patent-9,909,505, US-Patent-Appl-SN-14/695,373

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 core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades. The row includes no more than 20 of the propulsor blades. The propulsor has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades.