Gas turbine combustor and a gas turbine combustor of the control device, the abnormality detecting method for a gas turbine combustor

摘要

PROBLEM TO BE SOLVED: To provide a means for detecting an abnormality and protecting a combustor or a gas turbine with a simple means even when an abnormality occurs for example, a part of a plurality of fuel nozzles or a part of a plurality of fuel jetting ports which are provided in a gas turbine combustor, and a section where the plurality of fuel jetting ports or the like are branched at the downstream of a fuel flow rate control valve of one fuel system.;SOLUTION: A means for detecting a difference pressure between fuel pressure at the downstream of a fuel flow rate control valve provided in a fuel system and pressure in a combustor is provided. A means for specifying a fuel flow rate flowing in the fuel system is also provided. A divider for calculating ratio of difference pressure signal of the fuel system and a fuel flow rate signal of the fuel system is provided. A comparator for determining a combustor abnormality based on a signal from the divider is included.;COPYRIGHT: (C)2014,JPO&INPIT