Efficient, Low Pressure Ratio Propulsor for Gas Turbine Engines

Gallagher, Edward J [Inventor]Monzon, Byron R [Inventor]

关键词: BYPASSES;    BYPASS RATIO;    COMPRESSORS;    FAN BLADES;    GAS TURBINE ENGINES;    SHAFTS (MACHINE ELEMENTS);    GAS TURBINES;    TURBOFANS;    PROPULSIVE EFFICIENCY;    LOW PRESSURE;    PRESSURE RATIO;    PATENTS;   

RP-ID  :  US-Patent-9,926,885, US-Patent-Appl-SN-15/709,540

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 bypass flow passage that has an inlet and defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is arranged within the bypass flow passage. A first turbine is a 5-stage turbine and is coupled with a first shaft, which is coupled with the fan. A first compressor is coupled with the first shaft and is a 3-stage compressor. A second turbine is coupled with a second shaft and is a 2-stage turbine. The fan includes a row of fan blades that extend from a hub. The row includes a number (N) of the fan blades, a solidity value (R) at tips of the fab blades, and a ratio of N/R that is from 14 to 16.