US 11,971,040 B2
Aircraft fuel system with clutched augmentor pump
Edward W. Goy, Crystal Lake, IL (US); and Michael R. Blewett, Stillman Valley, IL (US)
Assigned to HAMILTON SUNDSTRAND CORPORATION, Charlotte, NC (US)
Filed by Hamilton Sundstrand Corporation, Charlotte, NC (US)
Filed on Oct. 25, 2021, as Appl. No. 17/509,996.
Prior Publication US 2023/0132118 A1, Apr. 27, 2023
Int. Cl. F02C 7/22 (2006.01); F04D 13/02 (2006.01); F04D 13/14 (2006.01)
CPC F04D 13/14 (2013.01) [F04D 13/021 (2013.01); F05D 2220/32 (2013.01); F05D 2240/515 (2013.01); F05D 2240/55 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A fuel system for a gas turbine engine comprising:
a) an augmentor pump having an inlet communicating with a fuel supply source and a discharge communicating with an augmentation stage of the engine, wherein the augmentor pump is connected to an accessory drive gearbox mounted to the engine along a common drive shaft, wherein the augmentor pump, the drive gearbox and the engine are all mounted on the common drive shaft; and
b) a high speed clutch for selectively engaging and disengaging the augmentor pump and the accessory drive gearbox, wherein the high speed clutch is positioned between the augmentor pump and the drive gearbox along the common drive shaft.