Gas turbine engine and system for servicing a gas turbine engine
US8672606B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 17, 2009 |
| Grant date | Mar 18, 2014 |
| Priority date | — |
| Expiry date | Jan 15, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/53961
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a compressor having first annular connection structure at a forward end portion of an air inlet housing of the compressor. The gas turbine engine may also include intake ducting having second annular connection structure adjacent a central passage of the intake ducting. The first annular connection structure and the second annular connection structure may form at least part of an interface between the air inlet housing and the intake ducting during operation of the gas turbine engine. The first and second annular connection structures may have shapes allowing the first annular connection structure to be moved through and beyond the second annular connection structure in a forward direction, the forward direction being opposite a direction of compressed air flow in the compressor during operation.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.