Patent ID: 9121368
Filing Date: 2015-09-01
Classification: F01D,F02K,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, each of said propulsor blades extending 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 such that said row of propulsor blades has a solidity value (R) of CD/CP that is between 1.0 and 1.3, and said row includes a number (N) of said propulsor blades that is no more than 20 such that a ratio of N/R is from 9 to 16.