초록 ▼

A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a

A mounting system for a gas turbine engine includes a mounting linkage assembly and a tangential link positioned generally transverse to the mounting linkage assembly. The mounting linkage assembly reacts at least a thrust load. The tangential link reacts at least a vertical load, a side load, and a torque load of the gas turbine engine.

대표청구항 ▼

1. A gas turbine engine, comprising: a compressor section, a combustor section, and a turbine section;a pylon; anda mounting system including a front mount and a rear mount each extending from said pylon, wherein said rear mount includes a mounting linkage assembly having a first body portion and a

1. A gas turbine engine, comprising: a compressor section, a combustor section, and a turbine section;a pylon; anda mounting system including a front mount and a rear mount each extending from said pylon, wherein said rear mount includes a mounting linkage assembly having a first body portion and a second body portion separate from said first body portion that provide a redundant connection between the gas turbine engine and said pylon wherein said rear mount includes at least one thrust link and at least one tangential link each connected between the gas turbine engine and said mounting linkage assembly; and wherein said at least one thrust link extends in a downstream direction relative to the gas turbine engine. 2. The gas turbine engine as recited in claim 1, wherein said rear mount is attached to said gas turbine engine adjacent a mid turbine frame. 3. The gas turbine engine as recited in claim 1, said rear mount is attached to said gas turbine engine adjacent a diffuser case. 4. The gas turbine engine as recited in claim 1, wherein said front mount is attached to a fan section of said gas turbine engine. 5. The gas turbine engine as recited in claim 1, wherein said front mount is attached to said compressor section of said gas turbine engine. 6. The gas turbine engine as recited in claim 1, wherein said rear mount is positioned between a diffuser case and a low pressure turbine case of said turbine section. 7. The gas turbine engine as recited in claim 1, wherein said at least one tangential link is positioned generally tangential relative to the gas turbine engine to react at least a vertical load, a side load and a torque load of the gas turbine engine.