FUEL SUPPLY SYSTEM OF AIRCRAFT GAS TURBINE ENGINE AND FUEL SUPPLY METHOD

Japanese Patent JP2022122754

A

To provide a fuel supply system which can accurately identify an internal leak model of a gear pump.SOLUTION: A fuel supply system comprises a gear pump 120, a measuring section 160 including an orifice 140 and a check valve 150 which are connected to each other in parallel at a downstream of the gear pump, a minimum pressurization check valve 170 disposed downstream of the measuring section, and a control device 180. The check valve 150 is closed when a gear pump rotation number is smaller than an upper threshold, and opened when the gear pump rotation number is equal to or larger than the upper threshold, and the minimum pressurization check valve 170 comprises a cylinder, and a piston for defining the inside of the cylinder to a first chamber communicating with a measuring-section outlet and a second chamber communicating with a system inlet. The piston is energized by a spring in a direction progressing toward the first chamber, and a flow-out port whose opening is adjusted by a reciprocation motion of the piston is arranged at a piston sidewall. The minimum pressurization check valve 170 is constituted so as to constantly maintain a pressure difference between the system inlet and the measuring-section outlet when the gear pump rotation number is equal to or larger than a lower threshold, and equal to or smaller than an intermediate threshold.SELECTED DRAWING: Figure 1

JP2016175515	HEAT INSULATION STRUCTURE OF LIQUID FUEL TANK
JP3839693	POWER GENERATION PLANT AND OPERATING METHOD THEREFOR
JP2022175083	GAS TURBINE

SUGAWARA HIROTAKA
SEKI NAOKI

JP2021020202A

August 23, 2022

February 10, 2021

Click for automatic bibliography generation  

IHI CORP

F02C9/32; F02C9/30

Koji Nagato

Previous Patent: Accessory display pedestal and storage material

Next Patent: Resin composition and resin molding