Impingement panel for a turbomachine
An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.
1. An impingement panel configured to provide impingement cooling to an exterior surface, the impingement panel comprising:
an impingement plate disposed along the exterior surface, the impingement plate defining a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface, wherein the impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween;
a collection duct defining a collection passage;
an inlet portion extending from the impingement plate to the collection duct such that the collection duct is spaced apart from the impingement plate, and wherein the inlet portion provides for fluid communication between the cooling flow gap and the collection passage; and
at least one support extending between the impingement plate, the inlet portion, and the collection duct.
2. The impingement panel as in claim 1 , wherein the collection passage is configured to collect coolant that has impinged upon the exterior surface.
3. The impingement panel as in claim 1 , wherein the inlet portion defines a first width and the collection duct defines a second width, and wherein the second width is larger than the first width.
4. The impingement panel as in claim 1 , wherein the collection duct is a first collection duct, and wherein the impingement panel further includes a second collection duct that extends from the impingement plate.
5. The impingement panel as in claim 1 , wherein the impingement panel is a plurality of impingement panel segments coupled to one another.
6. The impingement panel as in claim 1 , further comprising stand-offs extending from the impingement plate and spacing apart the impingement plate from the exterior surface.
7. An integrated combustor nozzle, comprising:
a combustion liner extending radially between an inner liner segment and an outer liner segment, the combustion liner including a forward end portion, an aft end portion, a first side wall, and a second side wall, the aft end portion of the combustion liner defining an airfoil-shaped turbine nozzle; and
an impingement panel comprising:
an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment, wherein the impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the one of the inner liner segment or the outer liner segment, wherein the impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween;
a collection duct converging in cross sectional area from a forward end fluidly coupled to a cooling insert to a closed aft end, the collection duct defining a collection passage;
an inlet portion extending from the impingement plate to the collection duct such that the collection duct is spaced apart from the impingement plate, and wherein the inlet portion provides for fluid communication between the cooling flow gap and the collection passage; and
at least one support extending between the impingement plate, the inlet portion, and the collection duct.
8. The integrated combustor nozzle as in claim 7 , wherein the collection passage is configured to collect coolant that has impinged upon the one of the inner liner segment or the outer liner segment and transport the coolant to a fuel injector.
9. The integrated combustor nozzle as in claim 7 , wherein the inlet portion defines a first width and the collection duct defines a second width, and wherein the second width is larger than the first width.
10. The integrated nozzle as in claim 7 , wherein the collection duct is a first collection duct, and wherein the impingement panel further includes a second collection duct that extends from the impingement plate.
11. The integrated nozzle as in claim 7 , wherein the impingement panel includes a plurality of impingement panel segments coupled to one another.
12. The integrated nozzle as in claim 7 , further comprising stand-offs extending from the impingement plate and spacing apart the impingement plate from the exterior surface.
13. The integrated combustor nozzle as in claim 7 , wherein the impingement panel is disposed along the exterior surface of the outer liner segment.
14. The integrated combustor nozzle as in claim 7 , wherein the impingement panel is disposed along the exterior surface of the inner liner segment.
15. The integrated nozzle as in claim 7 , wherein the impingement panel is a first impingement panel having a first collection duct and a second collection duct fluidly coupled to a first low pressure inlet of the cooling insert, and wherein the integrated nozzle further comprises a second impingement panel having a third collection duct fluidly coupled to a second low pressure inlet of the cooling insert.
16. The integrated nozzle as in claim 15 , wherein the first collection duct and the second collection duct are axially longer than the third collection duct.
17. A turbomachine comprising:
a compressor;
a compressor discharge casing disposed downstream from the compressor;
a turbine disposed downstream from the compressor discharge casing; and
an annular combustion system disposed within the compressor discharge casing, the annular combustion system including a plurality of integrated combustor nozzles disposed in an annular array about an axial centerline of the turbomachine, wherein each of the plurality of integrated combustor nozzles comprises:
a combustion liner extending radially between an inner liner segment and an outer liner segment, the combustion liner including a forward end portion, an aft end portion, a first side wall, and a second side wall, the aft end portion of the combustion liner defining an airfoil-shaped turbine nozzle; and
an impingement panel comprising:
an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment, wherein the impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the one of the inner liner segment or the outer liner segment, and wherein the impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween;
a collection duct converging in cross sectional area from a forward end fluidly coupled to a cooling insert to a closed aft end, the collection duct defining a collection passage;
an inlet portion extending from the impingement plate to the collection duct such that the collection duct is spaced apart from the impingement plate, and wherein the inlet portion provides for fluid communication between the cooling flow gap and the collection passage; and
at least one support extending between the impingement plate, the inlet portion, and the collection duct.
18. The turbomachine as in claim 17 , wherein the impingement panel is disposed along the exterior surface of the outer liner segment.
19. The turbomachine as in claim 17 , wherein the impingement panel is disposed along the exterior surface of the inner liner segment.