Combustor for a gas turbine engine

US12146660B2 · kind B2 · utility

Assignee

• General Electric Company · US

Inventors

• Ravindra Shankar Ganiger · Kanchinakote, IN
• Hiranya Nath · Bengaluru, IN
• Daniel J. Kirtley · Blue Ash, US
• Shai Birmaher · Cincinnati, US
• Veeraraju Vanapalli · Bengaluru, IN
• Karthikeyan Sampath · Bengaluru, IN
• Deepak Ghiya · Kanchinakote, IN
• Perumallu Vukanti · Bengaluru, IN
• Rajendra Mahadeorao Wankhade · Bengaluru, IN
• Pradeep Naik · Kanchinakote, IN

Key dates

• Filing date: Jun 7, 2021
• Grant date: Nov 19, 2024
• Expiry date: Jun 7, 2041

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F05D2240/55
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber, the liner further defining a gap; and an intermediate member disposed at least partially within the gap of the liner and in fluid communication with the combustion chamber, wherein the intermediate member is retained at a relatively fixed position with respect to the liner by a support extending between the intermediate member and a case of the gas turbine engine.