Combustor cooled quench zone array
In accordance with one aspect of the disclosure, a combustor is disclosed. The combustor may include a shell and a liner disposed within the shell. The combustor may further include a grommet at least partially defining a hole communicating through the shell and liner and a cooling channel communicating through the grommet.
1. A combustor for a gas turbine engine, comprising:
a shell having a plurality of impingement holes;
a panel mounted to the shell, the panel having a hot surface defining a portion of a combustion chamber, the panel having a plurality of effusion holes, wherein a flow cavity is defined between the shell and the panel and a flow of air passes through the plurality of impingement holes, into the flow cavity, and into the combustion chamber through the plurality of effusion holes; and
a grommet integrally formed with the panel and at least partially defining a hole communicating through at least the shell, the grommet including at least one cooling channel communicating through the grommet and arranged about the hole, wherein the grommet comprises:
an outward surface arranged proximate the shell;
an engagement surface configured to engage with the shell to prevent air from the hole defined by the grommet from passing between the grommet and the shell to enter the flow cavity;
an inward surface defined flush with the hot surface of the panel and defining a portion of the hot surface of the panel; and
the at least one cooling channel passes from the outward surface through the material of the grommet from the outward surface to the inward surface.
2. The combustor of claim 1 , wherein the at least one cooling channel is oriented perpendicular to the inward surface of the grommet with respect to an axis extending longitudinally through the combustion chamber.
3. The combustor of claim 1 , wherein the at least one cooling channel is provided at a non-perpendicular angle to the inward surface of the grommet.
4. The combustor of claim 1 , wherein the at least one cooling channel comprises between six and sixteen cooling channels that communicate through the grommet.
5. The combustor of claim 1 , wherein the at least one cooling channel is a plurality of cooling channels that are arranged circumferentially around the hole defined by the grommet.
6. The combustor of claim 1 , wherein the at least one cooling channel is a plurality of cooling channels and each cooling channel is separated about a circumference of the grommet by a distance three to ten times a diameter of one cooling channel of the plurality of cooling channels.
7. The combustor of claim 1 , wherein the hole defined by the grommet is a dilution hole.
8. The combustor of claim 1 , wherein the at least one cooling channel is oriented such that a flow passing through the at least one cooling channel will prevent a flame within the combustion chamber from contacting the inward surface of the grommet.
9. A method of cooling a portion of a combustor of a gas turbine engine, the method comprising:
providing a grommet that is integrally formed with a panel that is mounted to a shell of the combustor, wherein the shell includes a plurality of impingement holes, wherein the panel has a hot surface that defines a portion of a combustion chamber, the panel having a plurality of effusion holes, wherein a flow cavity is defined between the shell and the panel and a flow of air passes through the plurality of impingement holes, into the flow cavity, and into the combustion chamber through the plurality of effusion holes, the grommet at least partially defining a hole through the panel and the shell, the grommet including at least one cooling channel that passes from an outward surface of the grommet through the material of the grommet to an inward surface thereof, wherein the inward surface of the grommet is flush with the hot surface of the panel and defines a portion of the hot surface of the panel and wherein the at least one cooling channel is arranged proximate the hole, the grommet including an engagement surface configured to engage with the shell to prevent air from the hole defined by the grommet from passing between the grommet and the shell to enter the flow cavity;
directing cooling air through the at least one cooling channel communicating through the grommet; and
cooling the grommet with the cooling air flowing through the at least one cooling channel by transferring heat from the grommet to the cooling air.
10. The method of claim 9 , further comprising blowing a flame in the combustion chamber off the inward surface of the grommet with the cooling air flowing through the at least one cooling channel.
11. The method of claim 9 , wherein the at least one cooling channel is oriented perpendicular to the inward surface of the grommet with respect to an axis extending longitudinally through the combustion chamber.
12. The method of claim 9 , wherein the at least one cooling channel is provided at a non-perpendicular angle to the inward surface of the grommet.
13. The method of claim 9 , wherein the at least one cooling channel comprises between six and sixteen cooling channels that communicate through the grommet.
14. The method of claim 9 , wherein the at least one cooling channel is a plurality of cooling channels that are arranged circumferentially around the hole defined by the grommet.
15. The method of claim 9 , wherein the at least one cooling channel is a plurality of cooling channels and each cooling channel is separated about a circumference of the grommet by a distance three to ten times a diameter of one cooling channel of the plurality of cooling channels.
16. The method of claim 9 , wherein the at least one cooling channel is oriented such that a flow passing through the at least one cooling channel will prevent a flame within the combustion chamber from contacting the inward surface of the grommet.