Cooled transition duct for a gas turbine engine

Details Cooled transition duct for a gas turbine engine Cooled transition duct for a gas turbine engine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01)

Patent

CA 2598506

A transition duct (30) for a gas turbine engine (2) having improved cooling and reduced stress levels. The transition duct may be formed of two panels ((36, 38) joined together with welds (40) disposed remote from the bent corner regions (34) of the panels. Cooling channels (32) extending longitudinally in the direction of flow of the hot combustion gas carried by the duct are formed within each panel, including the corner regions. Because the entire annular width (W) of the transition duct is cooled, the gap (G) separating adjacent ducts around the inlet to the turbine (4) may be reduced when compared to prior art designs. Two-panel construction with welds remote from the corner regions is facilitated by maintaining the minimum bend radius in the corners (R2) and in the direction of flow (R4) to be greater than in prior art designs.

Une conduite de transition (30) destinée à une turbine à gaz (2) permet un refroidissement amélioré et un moindre degré de contraintes. La conduite de transition peut être formée à partir de deux panneaux (36, 38) réunis par soudage (40) et éloignés des régions d'angle incurvées (34) des panneaux. Des canaux de refroidissement (32) qui s'étendent longitudinalement dans la direction du flux de gaz de combustion chaud circulant dans la conduite sont formés dans chaque panneau, y compris les régions d'angle. Comme l'intégralité de la largeur annulaire (W) de la conduite de transition est refroidie, l'intervalle (G) séparant les conduites adjacentes autour de l'entrée de la turbine (4) peut être moins important que dans les modèles existants. On a facilité la conception d'un panneau avec des soudures éloignées des régions d'angle grâce à un rayon de courbure minimal dans les coins (R2) et dans la direction du flux (R4) plus important que dans les modèles existants.

Affiliated with

Also associated with

Rating

Cooled transition duct for a gas turbine engine does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Cooled transition duct for a gas turbine engine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Cooled transition duct for a gas turbine engine will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFCA-PAI-O-2022429