Cantor Colburn LLP
Mounting systems for gas turbine engines
A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inlet end of the compressor case. The outlet frame connects to an outlet end of the compressor case portion at an end opposite the compressor case inlet end. An axially fore mounting structure of the mounting structure connects to the inlet frame. An axially aft mounting structure of the mounting structure connects to the outlet frame. A bridging structure of the mounting structure is offset from the compressor case and connects the fore and aft mounting structures, thereby bridging engine loads across the inlet and outlet frames to reduce load induced distortion of the compressor case portion.
UNITED TECHNOLOGIES CORPORATION
F B Y F F B Y F F F B
F01D B64D Y02T F04D F05D B64D Y02T F02C F04D F04D B64D
inventional additional additional inventional additional additional additional inventional inventional inventional inventional
Jesse M. Gabriel L. James D.
Chandler Suciu Hill