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Coating system for clearance control in rotating machinery

a technology for rotating machinery and sealing systems, which is applied in the direction of machines/engines, liquid fuel engines, superimposed coating processes, etc., can solve the problems of affecting the sealing effect, so as to reduce the loss of blade tips, improve sealing effect, and reduce the effect of sealing temperatur

Inactive Publication Date: 2011-07-07
PRAXAIR ST TECH INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes new coatings for blades used in gas turbines that can withstand high temperatures without losing their effectiveness. These coatings are made from two different types of ceramic material which work together to create an optimal surface design. When these coatings are applied to the blades, they help reduce damage caused by friction between parts during operation. Additionally, this technology helps generate smaller particles of worn-down material, resulting in improved performance at lower costs compared to traditional metal seals.

Problems solved by technology

The technical problem addressed in this patent text is the need for improved seal systems in gas turbine engines, particularly for wear-resistant, abrasive coatings on the tips of blades and abradable coatings on the stationary seal surfaces. These systems need to have a rub relationship that allows for a tight operating clearance between the tips and seal surfaces to prevent damage to the engine and minimize downtime for maintenance. The goal is to increase engine efficiency, reduce fuel consumption, and minimize damage to the engine.

Method used

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Embodiment Construction

[0011]As indicated above, this invention relates in part to a gas turbine engine seal system comprising a rotating member having an abrasive tip surface disposed in rub relationship to a stationary abradable seal surface, wherein said abrasive tip surface comprises an abrasive coating deposited onto at least a portion of the tip surface, wherein said abrasive coating comprises a metallic alloy matrix having ceramic abrasive particles at least partially embedded in said matrix and at least some of the ceramic abrasive particles projecting from said matrix, wherein said ceramic abrasive particles are selected from alumina polycrystal, alumina single crystal (sapphire), chromia-doped alumina single crystal (ruby), yttria-alumina garnet (YAG), titania-doped alumina polycrystal or single crystal (emerald), SiAlON, SiC, Si3N4 or diamond; wherein said abradable seal surface comprises an abradable ceramic coating deposited onto at least a portion of the seal surface; and wherein said gas tu...

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Abstract

The invention relates to gas turbine engine seal systems having a rotating member with an abrasive tip surface disposed in rub relationship to a stationary seal member with an abradable surface. The abrasive tip surface is coated with a metallic alloy matrix having ceramic abrasive particles embedded in and projecting from the matrix. The abradable seal surface is coated with a ceramic coating. The rub relationship affords a tight operating clearance between the rotating member and the stationary seal member, thereby improving engine efficiency, reducing fuel consumption and minimizing overhaul downtime.

Description

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Claims

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Application Information

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Owner PRAXAIR ST TECH INC
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