US 2013/0340403 A1 · EROSION AND CORROSION RESISTANT COATINGS FOR EXHAUST GAS RECIRCULATION BASED GAS TURBINES

Abstract

A compressor blade for use in a compressor section of a gas turbine engine, comprising: a martensitic stainless steel compressor blade and an abrasive coating having an anodic component. The compressor blade has a blade portion, a dovetail portion and a platform portion intermediate the blade portion and the dovetail portion, the blade portion terminating in a tip opposite the dovetail portion. A cobalt-based coating overlies at least the blade portion of the compressor blade. The cobalt-based coating comprises a cobalt based material that includes precipitates of tungsten carbide that provide erosion resistance and particles of a sacrificial metal-based material distributed through the cobalt-based coating that provide galvanic corrosion resistance to the system.

Claims30

Dependent claims

A wear component, comprising:

a martensitic stainless steel base material,
a cobalt-based wear coating overlying the martensitic stainless steel base material, wherein the cobalt-based wear coating comprises a cobalt based alloy that includes precipitates of tungsten carbide;
wherein the cobalt-based wear coating further includes particles of a sacrificial metal-based material distributed through the cobalt-based coating;
and
wherein the sacrificial material acts as an anode to prevent galvanic corrosion of the base material in a corrosive environment.

2 more elements

An exhaust gas recirculation system, comprising:

combustor section for combusting fuel;
a stoichiometric exhaust gas recirculation turbine section extracting energy from hot gases produced by combusting fuel;
an exhaust portion for receiving hot gases of combustion from the turbine section;
a heat recovery device for receiving at least a portion of the hot gases of combustion from the exhaust portion;
a steam generator for recovering heat from the heat recovery device;
a scrubbing system for scrubbing exhaust gases from the heat recovery device and separating CO2 gases from other gases;
a CO2 recapture system;
an exhaust line passageway for exhausting scrubbed exhaust gases to the atmosphere;
an axial flow compressor in communication with the exhaust portion via an exhaust gas recirculation line and with a static air input for providing compressed fluid to the combustor section for combusting fuel;
wherein the axial flow compressor includes a plurality of martensitic stainless steel compressor blades, each compressor blade further comprising;
a blade portion, a dovetail portion and a platform portion intermediate the blade portion and the dovetail portion, the blade portion terminating in a tip opposite the dovetail portion;
a cobalt-based alloy coating overlying the martensitic stainless steel compressor blade, wherein the cobalt-based coating comprises a cobalt based material that includes precipitates of tungsten carbide;
and
particles of a sacrificial metal-based material distributed through the cobalt-based coating.

11 more elements

Dependencies are inferred from the claim text.

Facts

Application

13/528,149Filed 20 Jun 2012

Published

26 Dec 2013

Term ends

Not estimatedThe source records don’t support an estimate.

Classification10 codes

C23C 30/00
Coating with metallic material characterised only by the composition of the metallic
F01D 5/288
Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion: protective coatings for blades
F05D 2230/90
Manufacture: coating; Surface treatment
Y02T 50/60
Aeronautics or air transport: efficient propulsion technologies, e.g. for aircraft

Erosion and corrosion resistant coatings for exhaust gas recirculation based gas turbines

Life of this patent

Erosion and corrosion resistant coatings for exhaust gas recirculation based gas turbines

Life of this patent

Abstract

Claims30