United States Patent	6,378,286
Vermes ,   et al.	April 30, 2002

Low NOX gas turbine combustor liner

Abstract

A combustor liner and a method for combusting fuel in air with lowered production of NOX in a stationary, industrial gas turbine. The liner comprises a fuel injection location within the liner at an upstream end of the liner; combustion air openings in a liner wall sized to admit from about 10% to about 25% of total mass airflow entering the liner; suppression air openings in the liner wall from about 0.3 to about 0.5 equivalent diameters downstream of the combustion air openings, the suppression air openings being sized to admit from about 0.8 to about 4 times the mass airflow entering the liner through the combustion air openings; and wall cooling openings distributed in the liner wall for cooling thereof, the wall cooling openings being sized to admit from about 10% to about 40% of the total mass airflow entering the liner.

Inventors:	Vermes; Geza (Stratford, CT); Opdyke, Jr.; George (Stratford, CT)
Assignee:	Power Tech Associates, Inc. (Media, PA)
Appl. No.:	835220
Filed:	April 13, 2001

 

Current U.S. Class:	60/776; 29/890.02; 60/752; 60/754; 60/755
Intern'l Class:	F02C 007/26; B21D 053/00
Field of Search:	60/39.06,752,754,755,757,748 29/890.02