COMBUSTION ASSEMBLY FOR GAS TURBINE ENGINE Russian patent published in 2013 - IPC F23R3/34 

FIELD: engines and pumps.

SUBSTANCE: combustion assembly for gas turbine engine includes a burner head, a combustion chamber located downstream of the burner head, a swirling device for creation of a swirling air flow in the combustion chamber and multiple fuel injectors located in the burner head for fuel supply to the combustion chamber. Each of the multiple fuel injectors is located in the burner head so that it forms the first fuel outlet angle from downstream surface of the burner head comprising >±0° relative to longitudinal axis of the combustion assembly. The first angle lies in the first plane passing through longitudinal axis and forms the second fuel outlet angle from downstream surface comprising >±0° relative to the first plane. The second angle lies in the second plane orthogonal to the first plane. At that, the first angle and/or the second angle of individual fuel injectors of multiple fuel injectors or groups of fuel injectors of that variety are different.

EFFECT: improving fuel combustion efficiency and enlarging service life of combustion assembly.

13 cl, 41 dwg