Gas turbine combustor

Abstract

The present invention provides a gas turbine combustor in which the pressure loss and the flow deviation in the flow path reversing portion of the gas turbine combustor are reduced to uniformly mix a fuel with air to reduce NOx. The gas turbine combustor is characterized in that a combustor head portion has an inner casing that differentiates the inner periphery from the outer periphery and supplies air, an outer casing that surrounds the inner casing, and an airflow path provided between the inner casing and the outer casing; an opening portion that introduces the air flowing down the airflow path to an inner periphery side of the inner casing of the combustor is provided in the inner casing; a flow path deflection part deflecting the air flow at the opening portion is formed on the inner periphery side of the inner casing; an obstacle that impedes flow of the air is provided in the airflow path on an upstream side of the opening portion, and the obstacle is formed by a perforated plate comprising a plurality of holes that flow a stream of the air, and the obstacle is configured such that an opening ratio representing a ratio of the area of an opening portion to the area of a shielding portion aside from the hole that shields the flow of the air is low on an inner periphery side of the obstacle and high on an outer periphery side of the obstacle.

Description

technical field [0001] The present invention relates to a gas turbine combustor, and more particularly to a gas turbine combustor having a flow path structure that suppresses bias of air flowing inside the gas turbine combustor to reduce pressure loss. Background technique [0002] For gas turbine combustors, it is desired to reduce nitrogen oxides (NOx) and unburned amounts in combustion gas to obtain high environmental performance, and to reduce pressure loss of air flowing in gas turbine combustors to improve power generation efficiency. [0003] For the reduction of NOx, it is effective to apply a premix combustion method in which fuel and air are premixed before combustion to a gas turbine combustor. Fuel and air are mixed and burned in a lean state with less fuel, thereby lowering the flame temperature and suppressing NOx generated at high temperature. [0004] When this premixed combustion method is used for the gas turbine combustor, it is necessary to distribute th...

AI Technical Summary

Problems solved by technology

Therefore, there are problems that the support method becomes complicated, and the pressure loss increases due to the insertion of the structure

[0020] In the technology described in Patent Document 2, a method of increasing the flow rate on the inner peripheral side by a flow rate adjustment mechanism, and a method of suppressing separation of the flow at the inversion part by disturbing the entire flow path are proposed. However, in adjusting the flow rate, When the flow is disturbed, it is necessary to apply resistance to the flow, so there is a problem that the pressure loss increases due to the flow rate adjustment mechanism

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