초록 ▼

An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cyli

An effusion cooled transition duct for transferring hot gases from a combustor to a turbine is disclosed. The transition duct includes a panel assembly with a generally cylindrical inlet end and a generally rectangular exit end with an increased first and second radius of curvature, a generally cylindrical inlet flange, and a generally rectangular end frame. Cooling of the transition duct is accomplished by a plurality of holes angled towards the end frame of the transition duct and drilled at an acute angle relative to the outer wall of the transition duct. The combination of the increase in radii of curvature of the panel assembly with the effusion cooling holes reduces component stresses and increases component life. An alternate embodiment of the present invention is shown which discloses shaped angled holes for improving the film cooling effectiveness of effusion holes on a transition duct while reducing film blow off.

대표청구항 ▼

1. An effusion cooled transition duct for transferring hot gases from a combustor to a turbine comprising: a panel assembly comprising: a first panel formed from a single sheet of metal; a second panel formed from a single sheet of metal; said first panel fixed to said second panel by a means

1. An effusion cooled transition duct for transferring hot gases from a combustor to a turbine comprising: a panel assembly comprising: a first panel formed from a single sheet of metal; a second panel formed from a single sheet of metal; said first panel fixed to said second panel by a means such as welding thereby forming a duct having an inner wall, an outer wall, a thickness there between said walls, a generally cylindrical inlet end, and a generally rectangular exit end, said inlet end defining a first plane, said exit end defining a second plane, said first plane oriented at an angle to said second plane; a generally cylindrical inlet sleeve having an inner diameter and outer diameter, said inlet sleeve fixed to said inlet end of said panel assembly; a generally rectangular aft end frame, said frame fixed to said exit end of said panel assembly; and, a plurality of cooling holes in said panel assembly, each of said cooling holes having a centerline CL and separated from an adjacent cooling hole in the axial and transverse direction by a distance P, said cooling holes extending from said outer wall to said inner wall, each of said cooling holes drilled at an acute surface angle β relative to said outer wall and a transverse angle γ, each of said cooling holes having a first diameter D1 and a second diameter D2, wherein said diameters are measured perpendicular to said said inner wall, and said second diameter D2 is greater than said first diameter D1 such that said cooling hole is generally conical in shape. 2. The transition duct of claim 1 wherein said acute surface angle β is between 15 and 30 degrees from said outer wall. 3. The transition duct of claim 1 wherein said transverse angle γ is between 30 and 45 degrees. 4. The transition duct of claim 1 wherein said first diameter D1 is at least 0.025 inches. 5. The transition duct of claim 1 wherein said second diameter D2 is at least 0.045 inches. 6. The transition duct of claim 1 wherein said cooling holes are drilled in a direction from said outer wall towards said inner wall and angled in a direction towards said aft end frame. 7. The transition duct of claim 1 wherein the distance P in the axial and transverse directions between nearest adjacent cooling holes is at least 0.2 inches. 8. The transition duct of claim 1 wherein said panel assembly, inlet sleeve, and aft end frame are manufactured from a nickel-base superalloy such as Inconnel 625. 9. The transition duct of claim 1 wherein said thickness is at least 0.125 inches.