In-situ gas turbine rotor blade and casing clearance control method and system

A technology for gas turbines and rotor blades, used in liquid fuel engines, components of pumping devices for elastic fluids, mechanical equipment, etc., to solve problems such as damage, weakening of the distal end of the blade tip, cracking, etc.

Inactive Publication Date: 2013-09-18
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Over time, the increased operating temperature of the blade may cause the distal end of the blade tip to weaken, crack, or even be damaged, thereby inevitably increasing the annular space between the blade tip and the casing (sometimes called the "seal Gap" increases)
During normal operation, any such increase in the space between the blade tip and the casing results in a reduction in rotor and stator efficiency, which in turn reduces the overall efficiency of the compressor and engine

Method used

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  • In-situ gas turbine rotor blade and casing clearance control method and system
  • In-situ gas turbine rotor blade and casing clearance control method and system
  • In-situ gas turbine rotor blade and casing clearance control method and system

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Embodiment Construction

[0011] As mentioned above, the coating method according to the invention can be implemented on a variety of rotating assemblies, in particular compressors comprising a rotor rotating around a central longitudinal axis, and a rotor mounted to the disc and extending radially outwards. Multiple leaves. Most rotor assemblies also include a housing that is generally cylindrical in shape and has an inner peripheral surface spaced radially outward from the rotor and blades such that the inner peripheral surface of the housing meets the ends of the rotor blades A narrow annular space is formed between the blade tips.

[0012] The abradable coating according to the present invention is applied to a selected portion of the inner circumference of the casing in an amount sufficient to define a minimum annular gap after abrasion, as defined by the inner circumference of the casing and the tips of the rotating blades. As the rotor grows differentially (for example, because heat is conducte...

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Abstract

The invention disclose an in-situ gas turbine rotor blade and casing clearance control method and system. The system comprises a rotor assembly having a plurality of circumferentially spaced-apart rotor blades (50), with each blade extending radially outwardly from an inner wheel disk (54); a stator assembly comprising one or more rows of spaced-apart vanes (52) extending between adjacent rows of the rotor blades (50); 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 (36) 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.

Description

technical field [0001] This invention relates to gas turbine engines and more particularly to a method for reducing the clearance between the stationary rotor casing of a compressor and the rotor blades without damaging the blade tips, especially during start-up and shutdown. Minimal methods and systems. Improvements in rotor casing design and methods for coating the interior of the casing have improved rotor efficiency, long-term performance and reliability, and gas turbine engine efficiency. Background technique [0002] A gas turbine engine typically includes a compressor, multiple combustors, and a gas turbine section. Compressed ambient air from the compressor is mixed with hydrocarbon fuel that is fed to the combustor. The fuel and compressed air mixture is then ignited, creating hot expanding combustion gases. Exhaust gas is passed through nozzles into a gas turbine to extract energy from the expanding gas and run it through a generator to generate electricity. Mo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/00F04D29/02
CPCF01D11/122F05B2280/10306F05D2300/125F05D2300/135F05D2300/2112
Inventor C.A.史密斯J.D.梅默T.S.德赛
Owner GENERAL ELECTRIC CO
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