Gas turbine engine and fuel-air mixer thereof
A gas turbine engine including a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section. The combustion section includes a combustion chamber and a fuel-air mixer fluidly coupled with the combustion chamber. The fuel-air mixer includes an outer wall, a center body disposed radially inward of the outer wall, a first splitter including a first lobed trailing edge, a second splitter including a second lobed trailing edge axially offset from the first lobed trailing edge, a first swirler disposed at least partially between the first splitter and the second splitter; and a set of fuel orifices located at the first lobed trailing edge, the second lobed trailing edge, or the first lobed trailing edge and the second lobed trailing edge.
1 . A gas turbine engine, comprising:
a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section comprising:
a combustor liner that at least partially defines a combustion chamber; and
a fuel-air mixer receiving fuel comprising at least 75% by mass diatomic hydrogen, the fuel-air mixer being fluidly coupled with the combustion chamber, the fuel-air mixer comprising:
an outer wall;
a center body disposed radially inward of the outer wall;
a first splitter disposed at least partially between the outer wall and the center body, and including a first lobed trailing edge;
a second splitter disposed at least partially between the first splitter and the outer wall, and including a second lobed trailing edge axially offset from the first lobed trailing edge, wherein the first lobed trailing edge is axially downstream of the second lobed trailing edge;
a first swirler disposed at least partially between the first splitter and the second splitter; and
a set of fuel orifices located at the first lobed trailing edge, the second lobed trailing edge, or the first lobed trailing edge and the second lobed trailing edge.
2 . The gas turbine engine of claim 1 , wherein the first lobed trailing edge and the second lobed trailing edge are angled with respect to a first splitter centerline and a second splitter centerline.
3 . The gas turbine engine of claim 2 , wherein an angle of at least a portion of the first splitter and the second splitter is in a range of at least 5 degrees to less than or equal to 60 degrees with respect to a mixer centerline.
4 . The gas turbine engine of claim 1 , wherein the first lobed trailing edge has a first lobe angle, wherein the first lobe angle is in a range of −45 degrees to 45 degrees with respect to a first splitter centerline.
5 . The gas turbine engine of claim 4 , wherein the second lobed trailing edge has a second lobe angle, wherein the second lobe angle is in a range of −45 degrees to 45 degrees with respect to a second splitter centerline.
6 . The gas turbine engine of claim 5 , wherein the first lobe angle is different from the second lobe angle.
7 . The gas turbine engine of claim 1 , wherein a crest of the first lobed trailing edge is circumferentially offset from a crest of the second lobed trailing edge.
8 . A gas turbine engine, comprising:
a compressor section, a combustion section, and a turbine section in serial flow arrangement, with the combustion section comprising:
a combustor liner that at least partially defines a combustion chamber; and
a fuel-air mixer fluidly coupled with the combustion chamber, the fuel-air mixer comprising:
an outer wall;
a center body disposed radially inward of the outer wall;
a first splitter disposed at least partially between the outer wall and the center body, and including a first lobed trailing edge;
a second splitter disposed at least partially between the first splitter and the outer wall, and including a second lobed trailing edge axially offset from the first lobed trailing edge, wherein the first lobed trailing edge is axially downstream of the second lobed trailing edge;
a first swirler disposed at least partially between the first splitter and the second splitter; and
a set of fuel orifices located at the first lobed trailing edge, the second lobed trailing edge, or the first lobed trailing edge and the second lobed trailing edge.
9 . The gas turbine engine of claim 8 , wherein the first lobed trailing edge includes a trough and a crest, a first amplitude is measured from the trough to the crest of the first lobed trailing edge, and the second lobed trailing edge includes a trough and a crest, a second amplitude is measured from the trough to the crest of the second lobed trailing edge, wherein an axial length of an axial offset of the first lobed trailing edge and second lobed trailing edge is measured from the first lobed trailing edge to the second lobed trailing edge and the axial length is greater than zero and less than or equal to three times a maximum of a first amplitude and a second amplitude.
10 . The gas turbine engine of claim 9 , wherein the axial offset of the first lobed trailing edge and second lobed trailing edge is configured to create a cascading effect to increase mixing of fuel and air.
11 . The gas turbine engine of claim 8 , wherein the set of fuel orifices are configured for fuel comprising hydrogen.
12 . The gas turbine engine of claim 8 , wherein the fuel-air mixer further comprises a second swirler disposed at least partially between the first splitter and the center body, and a third swirler disposed at least partially between the second splitter and the outer wall.
13 . The gas turbine engine of claim 12 , wherein the first swirler has a first swirl number, the second swirler has a second swirl number, and wherein the first swirl number is greater than the second swirl number.
14 . The gas turbine engine of claim 13 , wherein the third swirler has a third swirl number, and wherein the second swirl number and third swirl number are lower than the first swirl number.
15 . The gas turbine engine of claim 8 , wherein the center body includes an air passage.
16 . The gas turbine engine of claim 8 , wherein the first lobed trailing edge has a trough and a crest, a first amplitude measured from the trough to the crest of the first lobed trailing edge, and the second lobed trailing edge has a second amplitude measured from a trough of the second lobed trailing edge to a crest of the second lobed trailing edge.
17 . The gas turbine engine of claim 16 , wherein the first amplitude and the second amplitude are in a range of 50% to 150% of a minimum height, wherein the minimum height includes the minimum height between the center body and the first splitter, the minimum height between the first splitter and the second splitter, or the minimum height between the second splitter and the outer wall.
18 . The gas turbine engine of claim 8 , wherein the center body includes an air passage, wherein the air passage extends annularly about a mixer centerline.
19 . The gas turbine engine of claim 8 , wherein the fuel-air mixer includes a third splitter disposed at least partially between the second splitter and the outer wall; and wherein the third splitter at least partially defines a third air passage.