Apparatus and method for mitigating particulate accumulation on a component of a gas turbine
A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection device secured to first component, the lateral flow injection device fluidly connecting a flow path located proximate to the second surface of the first component to the cooling channel, the lateral flow injection device being configured to direct airflow from the airflow path into the cooling channel in about a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.
1. A gas turbine engine component assembly, comprising:
a first component having an inner surface and an outer surface opposite the inner surface, wherein the first component includes a dedicated primary orifice extending from the outer surface to the inner surface through the first component;
a second component having a first surface and a second surface, the inner surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the dedicated primary orifice for cooling the second surface of the second component; and
a lateral flow injection device secured to the first component, the lateral flow injection device fluidly connecting an air flow path located proximate to the outer surface of the first component to the cooling channel, the lateral flow injection device being configured to direct airflow from the airflow path into the cooling channel in about a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel,
wherein the lateral flow injection device further comprises a passageway body having a bend radius configured to direct the airflow in about the lateral direction such that the cross flow is generated in the cooling channel,
wherein a portion of the passageway body is embedded within the dedicated primary orifice of the first component, and
wherein the lateral flow injection device further comprises:
a metering cap having a metering hole fluidly connecting an inlet of a passageway to the airflow path, the metering cap being attached to the passageway body, wherein the metering hole has a cross-sectional area less than a cross-sectional area of the passageway.
2. The gas turbine engine component assembly of claim 1 , wherein the lateral flow injection device further comprises:
a portion of the passageway body is located within the dedicated primary orifice.
3. The gas turbine engine component assembly of claim 2 , wherein:
the passageway is formed in the passageway body and enclosed in the passageway body.
4. The gas turbine engine component assembly of claim 1 , wherein:
the passageway body is at least one of scoop shaped and tubular shaped.
5. The gas turbine engine component assembly of claim 4 , wherein:
the passageway body and the dedicated primary orifice form the passageway.
6. The gas turbine engine component assembly of claim 1 , wherein:
the lateral flow injection device is fluidly connected to the airflow path through the inlet oriented in a direction about equal to a direction of the airflow path.
7. The gas turbine engine component assembly of claim 1 , wherein:
the lateral flow injection device is fluidly connected to the airflow path through the inlet oriented in a direction about perpendicular to a direction of the airflow path.
8. The gas turbine engine component assembly of claim 1 , wherein the lateral flow injection device further comprises:
a particulate collection location located opposite the inlet and proximate a particulate separation turn configured to turn the airflow such that a particulate separates from the airflow and is directed into the particulate collection location.
9. A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area, wherein the combustor comprises:
a combustion liner having an inner surface and an outer surface opposite the inner surface, wherein the combustion liner includes a dedicated primary orifice extending from the outer surface to the inner surface through the combustion liner;
a heat shield panel interposed between the inner surface of the combustion liner and the combustion area, the heat shield panel having a first surface and a second surface opposite the first surface, wherein the second surface is oriented towards the inner surface, and wherein the heat shield panel is separated from the combustion liner by an impingement cavity; and
a lateral flow injection device secured to the combustion liner, the lateral flow injection device fluidly connecting an aft flow path located proximate to the outer surface of the combustion liner to the impingement cavity, the lateral flow injection device being configured to direct airflow from the airflow path into the impingement cavity in about a lateral direction parallel to the second surface of the heat shield panel such that a cross flow is generated in the impingement cavity,
wherein the lateral flow injection device further comprises a passageway body having a bend radius configured to direct the airflow in about the lateral direction such that the cross flow is generated in the impingement cavity,
wherein a portion of the passageway body is embedded within the dedicated primary orifice of the combustion liner, and
wherein the lateral flow injection device further comprises:
a metering cap having a metering hole fluidly connecting an inlet of the passageway to the airflow path, the metering cap being attached to the passageway body, wherein the metering hole has a cross-sectional area less than a cross-sectional area of the passageway.
10. The combustor of claim 9 , wherein the lateral flow injection device further comprises:
a portion of the passageway body is located within the dedicated primary orifice.
11. The combustor of claim 10 , wherein:
the passageway is formed in the passageway body and enclosed in the passageway body.
12. The combustor of claim 9 , wherein:
the passageway body is at least one of scoop shaped and tubular shaped.
13. The combustor of claim 12 , wherein:
the passageway body and the dedicated primary orifice from the passageway.
14. The combustor of claim 9 , wherein:
the lateral flow injection device is fluidly connected to the airflow path through the inlet oriented in a direction about equal to a direction of the airflow path.
15. The combustor of claim 9 , wherein:
the lateral flow injection device is fluidly connected to the airflow path through the inlet oriented in a direction about perpendicular to a direction of the airflow path.
16. The combustor of claim 9 , wherein the lateral flow injection device further comprises:
a particulate collection location located opposite the inlet and proximate a particulate separation turn configured to turn the airflow such that a particulate separates from the airflow and is directed into the particulate collection location.