Title:
COMBUSTOR FOR GAS TURBINE
Document Type and Number:
Japanese Patent JP2017053523
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To provide a combustor for a gas turbine which can prevent the remaining of a high-temperature range of a flame temperature at an outlet of a combustion chamber.SOLUTION: A combustor for a gas turbine comprises: a hollow annular liner 20 having a combustion chamber 21; a burner 13 which sends a swirl flow T of an air-fuel mixture of fuel and compressed air CA into the combustion chamber 21; an outer dilution hole 24a formed at an outer peripheral wall 23 of the liner 20; and an inner dilution hole 26a formed at an inner peripheral wall 25 of the liner 20. Rows of both the dilution holes 24a, 26a are aligned in two rows, and when dividing a liner split part 30 into outer combustion regions 31, 32, and inner combustion regions 33, 34, a total opening area of the outer dilution hole of one outer combustion region 31 which the swirl flow T enters from an inner side, and the inner dilution hole of the other inner combustion region 34 which the swirl flow enters from an outer side is set larger than a total opening area of the inner dilution hole of one inner combustion region 33 which the swirl flow T enters from the other inner side, and the outer dilution hole of the other outer combustion region 32 which the swirl flow enters from one outer side.SELECTED DRAWING: Figure 3
Inventors:
UCHIDA MASAHIRO
Application Number:
JP2015176598A
Publication Date:
March 16, 2017
Filing Date:
September 08, 2015
Export Citation:
Assignee:
IHI CORP
International Classes:
F23R3/06; F23R3/28; F23R3/50
Attorney, Agent or Firm:
Koji Nagato