US 12,104,530 B2
Gas turbine engine
Benjamin J Sellers, Bath (GB); Jonathan A Cherry, Bristol (GB); and Craig Town, Bristol (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE plc, London (GB)
Filed on Sep. 8, 2022, as Appl. No. 17/940,035.
Claims priority of application No. 2112778 (GB), filed on Sep. 8, 2021.
Prior Publication US 2023/0167767 A1, Jun. 1, 2023
Int. Cl. F02C 7/32 (2006.01); F02C 3/06 (2006.01); F02C 7/12 (2006.01)
CPC F02C 7/12 (2013.01) [F02C 3/06 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01); F05D 2260/40 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A gas turbine engine for an aircraft, the gas turbine engine comprising, in axial flow sequence, a fan assembly, a compressor module, and a turbine module, with a first electric machine being positioned downstream of the fan assembly and being rotationally connected to the turbine module, the fan assembly being in fluid communication with the compressor module by an intermediate duct;
the fan assembly comprises a highest pressure fan stage having a plurality of fan blades extending radially from a hub, the plurality of fan blades defining a fan diameter (DFAN), each fan blade having a leading edge and a trailing edge, and the compressor module comprises a lowest pressure compressor stage having a row of rotor blades, with each of the rotor blades extending radially and having a leading edge and a trailing edge;
an intermediate flow axis is defined joining a radially outer tip of a trailing edge of one of the plurality of fan blades of the highest pressure fan stage, and a radially outer tip of a leading edge of one of the plurality of rotor blades of a leading edge of a lowest-pressure compressor blade, the intermediate flow axis lies in a longitudinal plane containing a centreline of the gas turbine engine, an intermediate flow axis angle is defined as the angle between the intermediate flow axis and the centreline,
the intermediate flow axis angle is in a range from −20 degrees to −30 degrees,
the first electric machine is between the fan assembly and the compressor module with a downstream end of the first electric machine being upstream of an inlet plane of the compressor module,
the fan assembly is fluidly connected to the compressor module by the intermediate duct that comprises a radially outer wall, an outer intermediate duct wall angle is defined as an angle between a radially inwardly facing surface of the radially outer wall and the centerline and the outer intermediate duct wall angle is −30 degrees, and
the radially outer wall is between the fan assembly and the lowest pressure compressor stage of the compressor module such that the intermediate duct fluidly connects the fan assembly to the leading edge of the lowest pressure compressor stage.