Patent ID: 11946379
Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A fan case assembly adapted for use with a gas turbine engine, the fan case assembly comprising:
a fan track liner that extends circumferentially at least partway about a central axis of the gas turbine engine, the fan track liner including a forward end, an aft end spaced apart axially from the forward end, and an inner radial surface that extends between the forward end and the aft end to define a gas path of the gas turbine engine,
an annular case coupled with the fan track liner to support the fan track liner radially in the gas turbine engine, and
an air recirculation duct configured to direct a portion of gases flowing through the gas path of the gas turbine engine from the aft end of the fan track liner into the gas path axially forward of the forward end of the fan track liner, the air recirculation duct including
extraction ports spaced apart circumferentially about the central axis and in fluid communication with the gas path of the gas turbine engine, each of the extraction ports extending radially through the annular case at a location axially aft of and adjacent to the aft end of the fan track liner, and each of the extraction ports opens directly into the gas path exposed to the fan track liner,
a first injection port in fluid communication with the gas path of the gas turbine engine, the first injection port extending radially through the annular case at a location axially forward of the forward end of the fan track liner, and the first injection port opens directly into the gas path exposed to the fan track liner, and
a manifold located radially outward of the annular case and in fluid communication with the extraction ports and the first injection port so that the portion of gases from the aft end of the fan track liner from the extraction ports is directed to the first injection port and into the gas path axially forward of the fan track liner,

wherein the annular case includes an outer wall that extends circumferentially around the central axis of the gas turbine engine, the outer wall formed to define aft holes spaced apart circumferentially about the central axis that each extend radially through the entire outer wall and a forward hole that extends radially through the entire outer wall at a location axially forward of the aft holes, and
wherein each of the extraction ports extends through one of the aft holes and the first injection port extends through the forward hole.