Patent ID: 9121412
Filing Date: 2015-09-01
Classification: F02C,F02K,F04D,F05D

Abstract:
1. A gas turbine engine comprising: a spool; a turbine coupled to drive the spool; a propulsor coupled to be driven by said turbine through said spool; and a gear assembly coupled between said propulsor and said spool such that rotation of said spool drives said propulsor at a different speed than said spool, wherein said propulsor includes a hub and a row of propulsor blades that extend from said hub, and said row includes a number (N) of said propulsor blades that is no more than 16, and the propulsor is located at an inlet of a bypass flow passage having a pressure ratio that is between 1.1 and 1.35 with regard to an inlet pressure and an outlet pressure of said bypass flow passage; wherein each of said propulsor blades extends radially between a root and a tip and in a chord direction between a leading edge and a trailing edge at the tip to define a chord dimension (CD), said row of propulsor blades defining a circumferential pitch (CP) with regard to said tips, wherein said row of propulsor blades has a solidity value (R) defined as CD/CP that is between 0.6 and 0.9, and a ratio of N/R is between 8 and 16 or between 18 and 28.