Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine
Method for constructing impingement/effusion cooling features in a component of a combustion turbine engine is provided. A pocket 102 may be arranged between an outer wall 104 and an inner wall 106 of the component. A lasing device 108 allows drilling through the component to form an effusion hole 110 . The lasing device further allows welding closed an opening 117 formed at outer wall 104 of the component during the drilling with the lasing device through the component. Lasing device 108 further allows drilling through outer wall 104 of the component to form an impingement hole 118 for the impingement/effusion cooling feature. The proposed methodology in a multi-panel arrangement, for example, eliminates a need of having to pre-drill such holes in individual panels prior to the bonding and forming of the component, which overcomes various drawbacks commonly associated with such pre-drilling.
1. A method for constructing impingement/effusion cooling features in a component of a combustion turbine engine, the method comprising:
arranging a pocket between an outer panel and an inner panel of the component, wherein either
the outer panel and the inner panel are diffusion bonded together to form the component, or
the outer panel and the inner panel are diffusion bonded to an intermediate panel in-between the outer panel and the inner panel to form the component;
drilling with a lasing device through the component to form an effusion hole for the impingement/effusion cooling features, the effusion hole being slanted relative to a surface of the inner panel of the component and in flow communication with the pocket in the component via a pocket exit opening;
closing with the lasing device an opening formed at the outer panel of the component during the drilling with the lasing device through the component; and
drilling with the lasing device through the outer panel of the component to form an impingement hole in the impingement/effusion cooling features, the impingement hole being perpendicular relative to a surface of the outer panel of the component and in flow communication with the pocket in the component via a pocket entry opening.
2. The method of claim 1 , wherein the component is formed by an arrangement of diffusion bonded panels.
3. The method of claim 2 , wherein the drilling with the lasing device through the component to form the effusion hole in the impingement/effusion cooling features comprises drilling through the arrangement of diffusion bonded panels.
4. The method of claim 3 , Wherein the arrangement of diffusion bonded panels comprises the intermediate panel disposed between the inner panel of the component and the outer panel of the component, wherein the pocket is arranged in the intermediate panel, wherein the effusion hole is formed in the inner panel and the impingement hole is formed in the outer panel.
5. The method of claim 4 , further comprising disposing a thermal barrier coating on the surface of the inner panel prior to the drilling with the device through the component.
6. The method of claim 5 , wherein the drilling with the lasing device through the component to form the effusion hole in the impingement/effusion cooling features comprises drilling through the arrangement of diffusion bonded panels and the thermal barrier coating disposed on the surface of the inner panel.
7. The method of claim 1 , further comprising disposing a thermal barrier coating on the surface of the inner panel prior to the drilling with the lasing device through the component.
8. The method of claim 7 , wherein the drilling with the lasing device through the component to form the effusion hole in the impingement/effusion cooling features comprises drilling through the thermal barrier coating disposed on the surface of the inner panel of the component.
9. The method of claim 1 , wherein the closing with the lasing device comprises welding the opening formed at the outer panel of the component during the drilling with the lasing device through the component.
10. A transition duct comprising the component, and wherein the method comprises constructing the impingement/effusion cooling features in said transition duct in accordance with the method of claim 1 .
11. A method for constructing impingement/effusion cooling features in a component of a combustion turbine engine, the method comprising:
arranging a pocket between an outer panel and an inner panel of the component, wherein either
the outer panel and the inner panel are diffusion bonded together to form the component, or
the outer panel and the inner panel are diffusion bonded to an intermediate panel in-between the outer panel and the inner panel to form the component;
disposing a thermal barrier coating on a surface of the inner panel of the component;
drilling with a lasing device through the component to form an effusion hole in the impingement/effusion cooling features, the effusion hole extending through the inner panel and the thermal barrier coating, the effusion hole being slanted relative to a surface of the thermal barrier coating and in flow communication with the pocket in the component via a pocket exit opening;
closing with the lasing device an opening formed at the outer panel of the component during the drilling with the lasing device through the component; and
drilling with the lasing device through the outer panel of the component to form an impingement hole in the impingement/effusion cooling features, the impingement hole being perpendicular relative to a surface of the outer panel of the component and in flow communication with the pocket in the component via a pocket entry opening.
12. The method of claim 11 , wherein the component is formed by an arrangement of panels affixed to one another, wherein an affixing of the panels to one another is performed prior to the drilling with the lasing device through the component.
13. The method of claim 11 , wherein the disposing of the thermal barrier coating on the surface of the inner panel is performed prior to the drilling with the lasing device through the component, thereby avoiding a masking of holes that otherwise would be present on the surface of the inner panel of the component when disposing the thermal barrier coating.