EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES

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.

主权项

1. A gas turbine engine comprising:
a gear assembly; a bypass flow passage, the bypass flow passage including an inlet and an outlet which define a design pressure ratio with regard to an inlet pressure at the inlet and an outlet pressure at the outlet at a design rotational speed of the engine, the design pressure ratio being between 1.3 and 1.55; a fan arranged at the inlet of the bypass flow passage; a first shaft and a second shaft mounted for rotation about an engine central longitudinal axis; a first turbine coupled with the first shaft such that rotation of the first turbine is configured to drive the fan, through the first shaft and the gear assembly, at a lower speed than the first shaft; and a second turbine coupled with the second shaft; wherein the fan includes a hub and a row of fan blades that extend radially outwardly from the hub and the row includes a number (N) of the fan blades that is from 12 to 16, 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.