GAS TURBINE FUEL MANIFOLD Russian patent published in 2024 - IPC F02C7/22 F04D29/44 F02C7/06 

FIELD: aircraft engine building.

SUBSTANCE: invention relates to fuel manifolds of a gas turbine engine (GTE), and can be used in the manufacture of fuel manifolds of small-size gas turbine engines of various types and purposes, including centrifugal compressor, direct-flow annular combustion chamber and turbine. Essence of the invention consists in the fact that the collector is made in the form of a stepped disc with a through axial hole and includes a fuel supply system made in the form of at least two circuits of channels, located in steps of larger diameter in parallel planes perpendicular to axis of through axial hole and forming regular polygons. Ends of fuel channels in each circuit are interconnected, the injectors are located on the end surface of the larger-diameter stage on the side of the smaller-diameter stage and are interconnected in each circuit with the ends of the fuel channels communicated with each other. Collector is equipped with blades located on the end surface of the disk stage of larger diameter and forming a diffuser, and the blades located on the side surface of the disc stage of a larger diameter and forming the straightener of the compressor, an air-oil mixture supply channel communicated with the through axial hole, and air channels designed to reduce air losses.

EFFECT: creation of a fuel manifold, which provides expansion of technical capabilities when creating small-size gas turbine engines due to reduction of radial and axial overall dimensions of the fuel manifold.

1 cl, 8 dwg