US 11,230,979 B2 · Aircraft engine fuel system and method

Abstract

A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.

Claims17

Dependent claims

A liquid fuel system for an aircraft engine, the fuel system comprising:

a first fuel supply conduit hydraulically connected to a fuel source,
a second fuel supply conduit hydraulically connected to the engine,
a fuel return conduit hydraulically connected to the second fuel supply conduit, and
a fuel pump having a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit, the intermediate inlet located between the main inlet and the outlet and in use having a pressure between a pressure at the main inlet and a pressure at the outlet, the intermediate inlet movable relative to the main inlet about a rotation axis of the fuel pump between a lower return pressure position and a higher return pressure position.

1 more element

Dependencies are inferred from the claim text.

Aircraft engine fuel system and method

Life of this patent

Aircraft engine fuel system and method

Life of this patent

Abstract

Claims17