Turbine engine combustor with a dilution passage
A combustor comprising a dome wall, a combustor liner extending from the dome wall, and a combustion chamber at least partially defined by the dome wall and the combustor liner. A set of fuel cups are arranged along the dome wall. A set of dilution passages extend through the dome wall or the combustor liner to direct air into the combustion chamber, wherein a dilution passage of the set of dilution passages includes an inlet, an outlet, and a passageway.
1 . A combustor for a turbine engine comprising:
a dome wall;
a combustor liner extending from the dome wall;
a combustion chamber at least partially defined by the dome wall and the combustor liner;
a set of fuel cups circumferentially spaced along the dome wall relative to a combustor centerline, with each fuel cup having a fuel cup centerline; and
a set of dilution passages extending through the dome wall or the combustor liner to direct air into the combustion chamber, wherein at least one dilution passage of the set of dilution passages comprises:
a radiused inlet fluidly coupled to a compressed air source;
an outlet downstream of the radiused inlet and fluidly coupled to the combustion chamber;
a passageway fluidly coupling the radiused inlet to the outlet; and
a channel having a radiused sidewall forming the radiused inlet, wherein a passageway inlet is defined at an intersection of the radiused inlet and the passageway, and wherein the channel spans at least two passageway inlets;
wherein at least a portion of a compressed air flow from the compressed air source is provided to the set of dilution passages which defines a dilution airflow to the combustion chamber to direct and shape a flame.
2 . The combustor of claim 1 , wherein the channel is an annular channel that circumferentially fluidly connects the at least two passageway inlets.
3 . The combustor of claim 1 , wherein the channel defines a channel centerline and the radiused inlet defines an inlet centerline, wherein the channel centerline is perpendicular to the inlet centerline.
4 . The combustor of claim 1 , wherein the compressed air source is a low pressure compressor or a high pressure compressor.
5 . The combustor of claim 1 , wherein a radiused inlet diameter of the radiused inlet is greater than a passageway diameter of the passageway.
6 . The combustor of claim 5 , wherein the radiused inlet diameter is twice a radius of curvature of the radiused sidewall.
7 . The combustor of claim 1 , further comprising a flow adjustor located adjacent at least one passageway inlet of the at least two passageway inlets, wherein the flow adjustor recesses into or protrudes from a sidewall of the passageway.
8 . A combustor for a turbine engine comprising:
a dome wall;
a combustor liner extending from the dome wall;
a combustion chamber at least partially defined by the dome wall and the combustor liner;
a set of fuel cups circumferentially spaced along the dome wall relative to a combustor centerline, with each fuel cup having a fuel cup centerline, and wherein each fuel cup of the set of fuel cups includes a swirler; and
a set of dilution passages extending through the dome wall or the combustor liner to direct air into the combustion chamber, wherein at least one dilution passage of the set of dilution passages comprises:
a radiused inlet fluidly coupled to a compressed air source, wherein the radiused inlet is defined by a spherical inlet;
an outlet downstream of the radiused inlet and fluidly coupled to the combustion chamber; and
a passageway fluidly coupling the radiused inlet to the outlet;
wherein a first part of a compressed air is fed to the fuel cup as a swirled airflow via the swirler, and a second part of the compressed air is fed to the set of dilution passages which provides a dilution airflow to the combustion chamber to direct and shape a flame.
9 . The combustor of claim 8 , wherein each fuel cup of the set of fuel cups includes a flare cone, wherein the swirled airflow from the swirler and a flow of fuel are mixed within the flare cone.
10 . The combustor of claim 8 , wherein the radiused inlet includes a radiused portion and a linear portion.
11 . The combustor of claim 8 , further comprising a flow adjustor located adjacent a passageway inlet defined at an intersection of the radiused inlet and the passageway, wherein the flow adjustor recesses into or protrudes from a sidewall of the passageway.
12 . A combustor for a turbine engine comprising:
a dome wall;
a combustor liner extending from the dome wall;
a combustion chamber at least partially defined by the dome wall and the combustor liner;
a set of fuel cups circumferentially spaced along the dome wall relative to a combustor centerline, with each fuel cup having a fuel cup centerline; and
a set of dilution passages extending through the dome wall or the combustor liner to direct air into the combustion chamber, wherein at least one dilution passage of the set of dilution passages comprises:
a radiused inlet fluidly coupled to a compressed air source;
an outlet downstream of the radiused inlet and fluidly coupled to the combustion chamber;
a passageway fluidly coupling the radiused inlet to the outlet; and
a channel having a radiused sidewall forming the radiused inlet, wherein the channel is a curved groove recessed into the dome wall, wherein the radiused sidewall is defined by a portion of the dome wall;
wherein at least a portion of a compressed air flow from the compressed air source is provided to the set of dilution passages which defines a dilution airflow to the combustion chamber to direct and shape a flame.
13 . The combustor of claim 12 , further comprising a flow adjustor located adjacent a passageway inlet defined at an intersection of the radiused inlet and the passageway, wherein the flow adjustor recesses into or protrudes from a sidewall of the passageway.
14 . The combustor of claim 12 , wherein the set of dilution passages includes at least two dilution passages having radiused inlets, and wherein the channel is an annular channel that circumferentially fluidly connects the radiused inlets.
15 . A combustor for a turbine engine comprising:
a dome wall;
a combustor liner extending from the dome wall;
a combustion chamber at least partially defined by the dome wall and the combustor liner;
a set of fuel cups circumferentially spaced along the dome wall relative to a combustor centerline, with each fuel cup having a fuel cup centerline; and
a set of dilution passages extending through the dome wall or the combustor liner to direct air into the combustion chamber, wherein at least one dilution passage of the set of dilution passages comprises:
a radiused inlet fluidly coupled to a compressed air source, wherein the radiused inlet has a radiused inlet diameter at least twice a radius of curvature of the radiused inlet or a radiused sidewall;
an outlet downstream of the radiused inlet and fluidly coupled to the combustion chamber; and
a passageway fluidly coupling the radiused inlet to the outlet;
wherein at least a portion of a compressed air flow from the compressed air source is provided to the set of dilution passages which defines a dilution airflow to the combustion chamber to direct and shape a flame.
16 . The combustor of claim 15 , further comprising a raised inlet portion at least partially defining the radiused inlet.
17 . The combustor of claim 15 , wherein the radiused inlet defines an inlet centerline and the passageway defines a passageway centerline, wherein a passageway angle is defined between the passageway centerline and the inlet centerline.
18 . The combustor of claim 17 , wherein the passageway angle is between +90° and −90°.
19 . The combustor of claim 15 , further comprising an aperture fluidly coupling the compressed air source and the passageway.
20 . The combustor of claim 15 , further comprising an aperture fluidly coupling the compressed air source and the passageway.