Patent ID: 9249683
Filing Date: 2016-02-02
CPC Classification: F01D,F02C,F04C,F05D

Claim Text:
1. A method for determining the capacity of an aircraft pump to deliver a predetermined fuel flow rate, in which the pump is able to supply fuel to a combustion chamber of a turbine engine of the aircraft and a fuel distribution circuit to a plurality of cylinders for actuating moving components of the turbine engine, and in which said predetermined flow rate is a fuel flow rate supplying the combustion chamber making it possible to perform a restart up of the turbine engine after stoppage while the aircraft is in flight, comprising: a step of rotating the pump at a predetermined rotation speed; a supply step including maintaining the rotation speed of the pump at the predetermined rotation speed and supplying at least one of said cylinders with the totality of the fuel coming out of the pump; a step of determining the fuel flow rate supplying said at least one cylinder, and a diagnostic step which consists of determining whether the pump is able to supply a sufficient flow rate when the determined value of the flow rate supplying said at least one cylinder is at least equal to the predetermined flow rate value.