Impingement panel for a turbomachine

Patent · Tue Jun 28 04:00:00 EDT 2022

OSTI ID:1893082

Berry, Jonathan Dwight; Hughes, Michael John

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.

• Research Organization: General Electric Co., Schenectady, NY (United States)
• Sponsoring Organization: USDOE
• DOE Contract Number: FE0023965
• Assignee: General Electric Company (Schenectady, NY)
• Patent Number(s): 11,371,702
• Application Number: 17/007,068
• OSTI ID: 1893082
• Country of Publication: United States
• Language: English