US 12,442,308 B2
Gas turbine engine with relative clocking of bifurcations
Davendu Y Kulkarni, Derby (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE PLC, London (GB)
Filed on Mar. 5, 2025, as Appl. No. 19/070,934.
Claims priority of application No. 2403770 (GB), filed on Mar. 15, 2024.
Prior Publication US 2025/0290426 A1, Sep. 18, 2025
Int. Cl. F02C 7/04 (2006.01); F01D 9/02 (2006.01); F01D 17/10 (2006.01)
CPC F01D 9/02 (2013.01) [F01D 17/105 (2013.01); F02C 7/04 (2013.01); F05D 2220/323 (2013.01); F05D 2240/12 (2013.01); F05D 2260/60 (2013.01); F05D 2260/606 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine for an aircraft comprising:
an air intake comprising a lip, a most upstream portion of which defining a highlight plane,
an engine core comprising a compressor, a combustor, and a turbine coupled to the compressor through a shaft;
a fan located upstream of the engine core and adapted to rotate about an engine main axis, the fan comprising a plurality of fan blades having a respective leading edge, trailing edge, and tip, a forward-most portion of the tip leading edge of each fan blade defining a fan inlet plane;
the air intake arranged upstream of, and configured to direct air to, the fan;
a plurality of fan outlet guide vanes (FOGVs) arranged downstream of the fan in a bypass duct of the gas turbine engine; and
upper and lower bifurcations arranged in the bypass duct and extending along respective radial directions;
wherein the lower bifurcation is arranged at a circumferential position corresponding to a position of highest fan blade loading caused by flow distortions introduced by the air intake in in-flight conditions.