Gas turbine engine
A gas turbine engine for an aircraft comprises: an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a bypass duct delimited by a bypass duct inner wall and a bypass duct outer wall and located radially outwardly from the engine core and downstream of the fan; and an outlet guide vane assembly, located within the bypass duct and, comprising a plurality of outlet guide vanes distributed circumferentially within the bypass duct, each outlet guide vane extending radially along a span between the bypass duct inner wall and the bypass duct outer wall, wherein a space-chord ratio of at least one outlet guide vane, at 50% of the span length from the bypass duct inner wall, is less than 0.72.
1 . A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades;
a bypass duct delimited by a bypass duct inner wall and a bypass duct outer wall and located radially outwardly from the engine core and downstream of the fan; and
an outlet guide vane assembly, located within the bypass duct and, comprising a plurality of outlet guide vanes distributed circumferentially within the bypass duct, each outlet guide vane extending radially along a span between the bypass duct inner wall and the bypass duct outer wall,
wherein a space-chord ratio of at least one outlet guide vane of the plurality of outlet guide vanes, at 50% of a span length from the bypass duct inner wall, is less than 0.72,
wherein a space-chord ratio of at least one outlet guide vane of the plurality of outlet guide vanes at 70% of a span length from the bypass duct inner wall is at least 1.21 times, and less than 1.45 times, greater than the space-chord ratio of the at least one outlet guide vane at 50% of the span length from the bypass duct inner wall,
wherein the space-chord ratio is defined by an average spacing of the outlet guide vanes at a respective span height divided by a true chord length of the at least one outlet guide vane at the respective span height, wherein the average spacing of the outlet guide vanes at the respective span height is defined as a circumference of the bypass duct at the respective span height (2πr, where r is a radius at the respective span height from a principal rotational axis of the gas turbine engine) divided by the number of the outlet guide vanes (N V ), (2πr/N V ).
2 . The gas turbine engine according to claim 1 , wherein the space-chord ratio (s/c) of the at least one outlet guide vane at 50% of the span length from the bypass duct inner wall is less than 0.70.
3 . The gas turbine engine according to claim 1 , wherein at 50% of the span length from the bypass duct inner wall, the space-chord ratio of the at least one outlet guide vane is more than 0.4.
4 . The gas turbine engine according to claim 1 , wherein the space-chord ratio (s/c) of the at least one outlet guide vane at 70% of the span length from the bypass duct inner wall is less than 0.79.
5 . The gas turbine engine according to claim 4 , wherein at 70% of the span length from the bypass duct inner wall, the space-chord ratio of the at least one outlet guide vane is more than 0.48.
6 . The gas turbine engine according to claim 1 , wherein the space-chord ratio (s/c) of the at least one outlet guide vane, at a point from 60% to 70% of the span length from the bypass duct inner wall, is less than
0.65+0.60*(span height−0.5)
wherein the span height is defined as a proportion of the span length from the bypass duct inner wall at said point to a total span length that is a length from the bypass duct inner wall to the bypass duct outer wall.
7 . The gas turbine engine according to claim 1 , the gas turbine engine further comprising:
a gearbox configured to receive an input from the core shaft and output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and wherein the gearbox has a gear ratio in a range of from 3 to 4.2.
8 . The gas turbine engine according to claim 1 , wherein:
the turbine is a first turbine, the compressor is a first compressor, and the core shaft is a first core shaft;
the engine core further comprises a second turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor; and
the second turbine, second compressor, and second core shaft are arranged to rotate at a higher rotational speed than the first core shaft.
9 . A gas turbine engine for an aircraft comprising:
an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades;
a bypass duct delimited by a bypass duct inner wall and a bypass duct outer wall and located radially outwardly from the engine core and downstream of the fan; and
an outlet guide vane assembly, located within the bypass duct and, comprising a plurality of outlet guide vanes distributed circumferentially within the bypass duct, each outlet guide vane extending radially along a span between the bypass duct inner wall and a bypass duct outer wall,
wherein a space-chord ratio of at least one outlet guide vane of the plurality of outlet guide vanes at 70% of a span length from the bypass duct inner wall is at least 1.21 times, and less than 1.45 times, greater than the space-chord ratio of the at least one outlet guide vane at 50% of the span length from the bypass duct inner wall,
wherein the space-chord ratio of the at least one outlet guide vane at 50% of the span length from the bypass duct inner wall is less than 0.65,
wherein the space-chord ratio is defined by an average spacing of the outlet guide vanes at a respective span height divided by a true chord length of the at least one outlet guide vane at the respective span height, wherein the average spacing of the outlet guide vanes at the respective span height is defined as a circumference of the bypass duct at the respective span height (2πr, where r is a radius at the respective span height from a principal rotational axis of the gas turbine engine) divided by the number of the outlet guide vanes (N V ), (2πr/N V ).
10 . The gas turbine engine according to claim 9 , wherein the space-chord ratio (s/c) of the at least one outlet guide vane at 70% of the span length from the bypass duct inner wall is less than 0.79.
11 . The gas turbine engine according to claim 9 , the gas turbine engine further comprising:
a gearbox configured to receive an input from the core shaft and output drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and wherein the gearbox has a gear ratio in a range of from 3.1 to 4.2.