Methods and apparatus for maintaining rotor assembly tip clearances
US7246996B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jan 4, 2005 |
| Grant date | Jul 24, 2007 |
| Priority date | — |
| Expiry date | Aug 12, 2025 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for assembling a rotor assembly for a gas turbine engine is provided. The engine includes an engine casing, a plurality of rotor blades, and at least one turbine shroud assembly. The method includes mounting a plurality of case segments together circumferentially to form the casing around the plurality of rotor blades and the at least one turbine shroud assembly, wherein each of the case segments includes at least two mounting flanges and a channel defined therebetween. The method also includes applying a thermal barrier coating to an inner surface of the channel and at least a portion of each mounting flange to facilitate maintaining axisymmetric running tip clearances between the plurality of rotor blades and the least one turbine shroud assembly during a cruise operation. The thermal barrier coating also facilitates controlling axisymmetric running tip clearances during a take-off operation such that an exhaust gas temperature and a specific fuel consumption is reduced.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.