Turbomachine cooling trench
A component for a turbine engine includes a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine, a cooling passage defined within the body, and a trench on the exterior surface. The trench includes a plurality of outlets, and a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets.
1. A component for a turbine engine, comprising:
a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine;
a cooling passage defined within the body and supplying cooling air to the component; and
a trench on the exterior surface, comprising:
an undulating surface defining a minimum depth and a maximum depth of the trench with respect to the exterior surface;
a plurality of outlets in the undulating surface; and
a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets;
wherein the undulating surface comprises a curved surface defining a cooling wall between two adjacent outlets in the plurality of outlets,
wherein at least one outlet in the plurality of outlets is located at the maximum depth of the trench; and
wherein at least one cooling hole in the plurality of cooling holes comprises a cross-sectional area that increases in a direction toward the plurality of outlets.
2. The component of claim 1 , wherein the cooling wall comprises a peak defining the minimum depth of the trench.
3. The component of claim 2 , wherein the plurality of outlets comprises a first outlet and a second outlet, and the peak is located between the first outlet and the second outlet.
4. The component of claim 1 , wherein the undulating surface defines a plurality of peaks along the trench, wherein at least one peak in the plurality of peaks defines the minimum depth of the trench.
5. The component of claim 4 , wherein the plurality of peaks are interspersed with the plurality of outlets in an alternating arrangement.
6. The component of claim 1 , wherein the plurality of cooling holes comprises a first cooling hole and a second cooling hole, wherein the first cooling hole diverges from the second cooling hole between the cooling passage and the plurality of outlets.
7. The component of claim 1 , wherein the plurality of outlets comprises a first outlet and a second outlet, wherein the first outlet defines a first geometric profile and the second outlet defines a second geometric profile different from the first geometric profile.
8. The component of claim 1 , wherein the component is a turbine rotor blade, wherein the body comprises a first band and an airfoil extending radially from the first band, wherein the exterior surface comprises a first band surface and an airfoil surface, and wherein the trench is positioned on at least one of the first band surface or the airfoil surface.
9. The component of claim 1 , wherein the component is a turbine nozzle, wherein the body comprises a first band, a second band positioned radially outward from the first band, and an airfoil extending therebetween, wherein the exterior surface comprises a first band surface, an airfoil surface, and a second band surface, and wherein the trench is positioned on at least one of the first band surface, the airfoil surface, or the second band surface.
10. The gas turbine engine, comprising:
a compressor section, a combustion section, and a turbine section in axial flow arrangement, the combustion flowpath extending through the combustion section and the turbine section for the flow of combustion gas therethrough; and
the component of claim 1 .
11. The component of claim 1 , wherein the component is a turbine nozzle, wherein the body comprises a first band, a second band positioned radially outward from the first band, and an airfoil extending therebetween, wherein the exterior surface comprises a first band surface, an airfoil surface, and a second band surface, and wherein the trench is positioned on at least one of the first band surface, the airfoil surface, or the second band surface.
12. The component of claim 1 , wherein the plurality of cooling holes includes at least a first cooling hole and a second cooling hole diverging from the first cooling hole between the cooling passage and the plurality of outlets.
13. The component of claim 1 , wherein a portion of the trench includes equally spaced outlets of the plurality of outlets and a portion of the trench includes unequally spaced outlets of the plurality of outlets.
14. A component for a turbine engine, comprising:
a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine;
a cooling passage defined within the body and supplying cooling air to the component; and
a trench on the exterior surface, comprising:
an undulating surface defining a minimum depth and a maximum depth of the trench with respect to the exterior surface;
a plurality of outlets in the undulating surface;
a first curvilinear cooling hole extending from the cooling passage to the corresponding plurality of outlets; and
a second curvilinear cooling hole extending from the cooling passage to the corresponding plurality of outlets, the first curvilinear cooling hole diverging from the second curvilinear cooling hole between the cooling passage and the corresponding plurality of outlets;
wherein the undulating surface comprises a curved surface defining a cooling wall between two adjacent outlets in the plurality of outlets.
15. The component of claim 14 , wherein the cooling wall comprises a peak defining the minimum depth of the trench.
16. The component of claim 14 , wherein the undulating surface defines a plurality of peaks along the trench, wherein at least one peak in the plurality of peaks defines the minimum depth of the trench.
17. The component of claim 16 , wherein the plurality of peaks are interspersed with the plurality of outlets in an alternating arrangement.
18. The component of claim 14 , wherein the plurality of outlets comprises a first outlet and a second outlet, wherein the first outlet defines a first geometric profile and the second outlet defines a second geometric profile different from the first geometric profile.
19. The component of claim 14 , wherein the component is a turbine rotor blade, wherein the body comprises a first band and an airfoil extending radially from the first band, wherein the exterior surface comprises a first band surface and an airfoil surface, and wherein the trench is positioned on at least one of the first band surface or the airfoil surface.
20. The gas turbine engine, comprising:
a compressor section, a combustion section, and a turbine section in axial flow arrangement, the combustion flowpath extending through the combustion section and the turbine section for the flow of combustion gas therethrough; and
the component of claim 14 .