Gas turbine combustor

US7954325B2 · kind B2 · utility

Assignee

• UNITED TECHNOLOGIES CORPORATION · US

Inventors

• Steven W. Burd · Cheshire, US
• Albert K. Cheung · East Hampton, US
• Dae K. Dempsey · Greenwood, US
• James B. Hoke · Tolland, US
• Stephen K. Kramer · Cromwell, US
• John T. Ols · Northborough, US
• Reid Dyer Curtis Smith · Amston, US
• William A. Sowa · Simsbury, US

Key dates

• Filing date: Dec 6, 2005
• Grant date: Jun 7, 2011
• Expiry date: Aug 19, 2029

Classification

• Technology area (CPC Y): Emerging Cross-Sectional Technologies
• CPC primary: Y02T50/60
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.