US 9,121,368 B2
Efficient, low pressure ratio propulsor for gas turbine enginesGeneral
US 9,121,368 B2
Efficient, low pressure ratio propulsor for gas turbine engines
Tech Center:
3700 Mechanical Engineering, Manufacturing and Medical Devices/Processes
Examiner:
Phutthiwat Wongwian
Art Unit:
3741 Thermal and Combustion Technology, Motive and Fluid Power Systems
Inventors:
Edward J. Gallagher; Byron R. Monzon
Assignee:
Priority:
07/05/11
Filed:
05/31/12
Granted:
09/01/15
Expiration:
05/23/32
Abstract
A gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 20 of the propulsor blades.
Cooperative Patent Classification (CPC)
F02F02K1/06F02KF01D17/14F01DF05D2260/4031F05D