Patent ID: 11873993
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 9:
10. A gas turbine engine comprising:
a compressor section and a turbine section with a combustor intermediate the compressor section and the turbine section;
the combustor having a liner defining a combustion chamber, an air and fuel mixing body received within said liner and upstream of the combustion chamber;
the mixing body has a center axis, and includes a bluff-body;
a plurality of fuel injection ports on the bluff-body and communicating with a central fuel supply such that fuel passes from the fuel supply passage and into a mixing chamber with a component in an axially downstream direction and a radially outward direction relative to said central axis;
a plurality of inner air swirlers providing air into the mixing chamber with a component in an axially downstream direction, a radially outward direction, and with a circumferential component due to swirler structure, the inner air swirlers being outwardly angularly offset from the center axis and are configured to achieve the radially outward component and the axially downstream component for a majority of the air exiting the inner air swirlers; and
the fuel injection ports being downstream of an outlet of the inner air swirlers wherein a plurality of outer swirlers delivers air into the combustion chamber downstream of the mixing chamber,
wherein said plurality of outer swirlers are inwardly angularly offset from the center axis,
wherein air is delivered downstream of said plurality of outer air swirlers with a component in an axially downstream direction, a radially inward direction and with a circumferential component due to swirler structure, the outer air swirlers are configured to achieve the axially downstream component and the radially inward component for a majority of the air exiting the outer air swirlers.