Method of protecting gas turbine combustor components against water erosion and hot corrosion
AssigneeGeneral Electric Company
InventorGilbert Farmer
Life of this patent
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Abstract
A method of preventing water erosion and hot corrosion in a combustor of a gas turbine engine, wherein water is injected into said combustor for NOx abatement, which involves the step of applying a dense vertically cracked thermal barrier coating to certain components thereof The dense vertically cracked thermal barrier coating has a porosity of less than approximately 8% and a tensile strength in the range of approximately 4-7 ksi. The dense vertically cracked thermal barrier coating is applied to such combustor components so as to produce a segmented ceramic structure having macrocracks formed therein which are oriented substantially perpendicular to an interface of the combustor component and the segmented ceramic structure.
Claims20
A method of preventing water erosion and hot corrosion in a combustor of a gas turbine engine, wherein water is injected into said combustor for NOx abatement, comprising the step of applying a dense vertically cracked thermal barrier coating to components of said combustor subject to impingement by said water.
A combustion apparatus for a gas turbine engine, comprising:
- (a) a combustor structure including at least one combustion chamber;
- (b) a dual cone fuel nozzle for injecting both fuel and water to said combustion chamber;
- and
- (c) a swirl cup package upstream of and adjacent to said combustion chamber, said swirl cup package including a swirler, a swirl cup, a splashplate and a venturi extending between said nozzle and said combustion chamber for mixing said fuel and water with air;
- wherein a dense vertically cracked thermal barrier coating is applied to selected portions of said swirl cup package so as to prevent water erosion and hot corrosion.
Dependencies are inferred from the claim text.