Integrated combustor nozzles with continuously curved liner segments

US11231175B2 · kind B2 · utility

Assignee

• General Electric Company · US

Inventors

• Jonathan Dwight Berry · Simpsonville, US
• Michael John Hughes · State College, US
• Russell DeForest · Simpsonville, US
• Kevin Weston McMahan · Greer, US
• Victor John Morgan · Simpsonville, US
• Ibrahim Sezer · Greenville, US
• Neelesh Nandkumar Sarawate · Pleasanton, US
• Deepak Trivedi · Niskayuna, US

Key dates

• Filing date: Jun 19, 2018
• Grant date: Jan 25, 2022
• Expiry date: Dec 25, 2038

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F23R2900/00012
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.