US 2013/0236302 A1 · IN-SITU GAS TURBINE ROTOR BLADE AND CASING CLEARANCE CONTROL

Abstract

A method and system for protecting the rotor blade tips of rotary machines, particularly the compressors of gas turbine engines, comprising a rotor assembly having a plurality of circumferentially spaced-apart rotor blades, with each blade extending radially outwardly from an inner wheel disk; a stator assembly comprising one or more rows of spaced-apart vanes extending between adjacent rows of the rotor blades; a casing extending circumferentially around the rotor and stator assemblies; and an abradable ceramic coating applied to selected areas of the interior cylindrical surface of the rotor casing to thereby provide a minimum clearance between the casing and rotor blades during start up and to thereafter ensure an effective compressor seal for compressed gas flow.

Claims19

Dependent claims

A gas turbine engine comprising:

a turbine;
one or more hydrocarbon gas combustors;
an air compressor;
a compressor rotor assembly for said compressor, comprising a plurality of circumferentially spaced-apart rotor blades extending radially outwardly from an inner wheel disk;
a compressor stator assembly comprising one or more rows of spaced-apart stator vanes extending between adjacent rows of said rotor blades;
a casing extending circumferentially around said rotor and stator assemblies forming a plurality of inner and outer flow paths defined by said rotor blades and said stator vanes;
and
a ceramic coating applied to the interior of said casing in an amount sufficient to cause the tips of said rotor blades to abrade portions of said ceramic coating during start-up and provide a minimum amount of clearance between said rotor blades and said casing.

5 more elements

Dependencies are inferred from the claim text.

In-situ gas turbine rotor blade and casing clearance control

Life of this patent

In-situ gas turbine rotor blade and casing clearance control

Life of this patent

Abstract

Claims19