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.

Title
Gas turbine engine and system for servicing a gas turbine engine
Application Number
12/654375
Publication Number
20100095683
Application Date
December 17, 2009
Publication Date
April 22, 2010
Inventor
Jason Michael Robertson
San Diego
CA, US
Daniel James Doll
Poway
CA, US
Ian Trevor Brown
Charles Cornelius
Coronado
CA, US
Gabriel James Glynn
San Diego
CA, US
Agent
Caterpillar Finnegan Henderson
DC, US
Assignee
Solar Turbines Incorporated
IPC
F04D 27/02
F02C 07/20
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