Plug resistant effusion holes for gas turbine engine
A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
1. A combustor for a gas turbine engine, comprising:
a liner having a first surface, a second surface opposite the first surface and defining a plurality of effusion cooling holes configured to form a film of cooling fluid on the second surface of the liner, at least one of the plurality of effusion cooling holes including:
an inlet section including an elliptical opening, with a major axis of the opening oblique to a longitudinal axis of the at least one of the plurality of effusion cooling holes and oblique to the first surface, the opening defined along an axis, and a plane extending through the inlet section is at an angle to the first surface and normal to the axis, and the angle is less than 90 degrees;
a converging section fluidly coupled downstream of the inlet section;
a metering section fluidly coupled downstream of the converging section; and
an outlet section fluidly coupled downstream of the metering section configured to form the film of cooling air on the second surface, and the inlet section, the converging section, the metering section and the outlet section extend along the longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
2. The combustor of claim 1 , wherein the at least one of the plurality of effusion cooling holes includes a bump proximate the inlet section to separate cooling fluid from the first surface.
3. The combustor of claim 1 , wherein the inlet section further comprises a bellmouth that surrounds the opening.
4. The combustor of claim 1 , wherein the converging section has a first cross-sectional area proximate the inlet section and smoothly transitions to a second cross-sectional area at the metering section.
5. The combustor of claim 1 , wherein the at least one of the plurality of effusion cooling holes includes a fillet that extends about a perimeter of the at least one of the plurality of effusion cooling holes at the first surface.
6. The combustor of claim 1 , wherein a cross-sectional area of the inlet section is greater than a cross-sectional area of the outlet section.
7. The combustor of claim 1 , wherein the liner has a thickness defined between the first surface and the second surface, and a portion of the outlet section is defined within the thickness.
8. The combustor of claim 7 , wherein the inlet section and the converging section are defined outside of the thickness.
9. The combustor of claim 1 , wherein the inlet section is spaced apart from the first surface.
10. A combustor for a gas turbine engine, comprising:
a liner having a first surface, a second surface opposite the first surface and defining a plurality of effusion cooling holes configured to form a film of cooling fluid on the second surface of the liner, at least one of the plurality of effusion cooling holes including:
an inlet section spaced apart from the first surface, the inlet section including an elliptical opening, with a major axis of the opening oblique to a longitudinal axis of the at least one of the plurality of effusion cooling holes and oblique to the first surface, and a plane extending through the inlet section is at an angle to the first surface and normal to the axis, and the angle is less than 90 degrees;
a converging section fluidly coupled downstream of the opening;
a metering section fluidly coupled downstream of the converging section; and
an outlet section fluidly coupled downstream of the metering section, the outlet section positioned proximate to the second surface and configured to form the film of cooling air on the second surface, and the inlet section, the converging section, the metering section and the outlet section extend along the longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
11. The combustor of claim 10 , wherein the at least one of the plurality of effusion cooling holes includes a bump proximate the inlet section to separate cooling fluid from the first surface.
12. The combustor of claim 10 , wherein the inlet section further comprises a bellmouth that surrounds the opening.
13. The combustor of claim 10 , wherein the converging section has a first cross-sectional area proximate the opening of the inlet section and smoothly transitions to a second cross-sectional area at the metering section.
14. The combustor of claim 10 , wherein the at least one of the plurality of effusion cooling holes includes a fillet that extends about a perimeter of the at least one of the plurality of effusion cooling holes at the first surface.
15. The combustor of claim 10 , wherein a cross-sectional area of the inlet section is greater than a cross-sectional area of the outlet section.
16. The combustor of claim 10 , wherein the liner has a thickness defined between the first surface and the second surface, and a portion of the outlet section is defined within the thickness.
17. The combustor of claim 16 , wherein the inlet section and the converging section are defined outside of the thickness.
18. A combustor for a gas turbine engine, comprising:
a liner having a first surface, a second surface opposite the first surface and defining a plurality of effusion cooling holes configured to form a film of cooling fluid on the second surface of the liner, at least one of the plurality of effusion cooling holes including:
an inlet section spaced apart from the first surface, the inlet section including an elliptical opening, with a major axis of the opening oblique to a longitudinal axis of the at least one of the plurality of effusion cooling holes, the major axis having a first vertex and a second vertex opposite the first vertex, the opening defined along an axis, a plane extending through the inlet section is at an angle to the first surface, is normal to the axis and is normal to the major axis of the opening, and the angle is less than 90 degrees;
a bump proximate the second vertex;
a converging section fluidly coupled downstream of the opening;
a metering section fluidly coupled downstream of the converging section; and
an outlet section fluidly coupled downstream of the metering section, the outlet section positioned proximate to the second surface and configured to form the film of cooling air on the second surface and the inlet section, the converging section, the metering section and the outlet section extend along the longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
19. The combustor of claim 18 , wherein the at least one of the plurality of effusion cooling holes includes a fillet that extends about a perimeter of the at least one of the plurality of effusion cooling holes at the first surface.
20. The combustor of claim 18 , wherein the liner has a thickness defined between the first surface and the second surface, a portion of the outlet section is defined within the thickness, and the inlet section and the converging section are defined outside of the thickness.