Engine backbone bending reduction

Abstract

Methods, apparatus, systems and articles of manufacture are disclosed. A mechanical linkage for mounting a gas turbine engine to a pylon includes: a bending restraint having a first end and a second end; a first joint at the first end of the bending restraint to connect the first end of the bending restraint to a fan section of the gas turbine engine; and a second joint at the second end of the bending restraint to connect the second end of the bending restraint to the pylon.

What is claimed is: 
     
         1 . A mechanical linkage for mounting a gas turbine engine to a pylon, the mechanical linkage comprising:
 a bending restraint having a first end and a second end;   a first joint at the first end of the bending restraint to connect the first end of the bending restraint to a fan section of the gas turbine engine; and   a second joint at the second end of the bending restraint to connect the second end of the bending restraint to the pylon.   
     
     
         2 . The mechanical linkage of  claim 1 , wherein the first joint and the second joint are pin joints. 
     
     
         3 . The mechanical linkage of  claim 1 , wherein the bending restraint is a first bending restraint, and further including a second bending restraint having a first end and a second end and a third bending restraint having a first end and a second end. 
     
     
         4 . The mechanical linkage of  claim 3 , wherein the third bending restraint is a compression-only bending restraint. 
     
     
         5 . The mechanical linkage of  claim 3 , wherein the second end of the second bending restraint and the first end of the third bending restraint are connected via a third joint. 
     
     
         6 . The mechanical linkage of  claim 5 , wherein the third joint is a ball and socket joint. 
     
     
         7 . The mechanical linkage of  claim 3 , further including a buckling stabilizer shell. 
     
     
         8 . The mechanical linkage of  claim 1 , further including:
 a first thrust linkage having a first end and a second end;   a second thrust linkage having a first end and a second end;   a third joint at the first end of the first thrust linkage; and   a fourth joint at the second end of the first thrust linkage.   
     
     
         9 . The mechanical linkage of  claim 8 , wherein the third joint connects the first end of the first thrust linkage to the fan frame of the gas turbine engine. 
     
     
         10 . The mechanical linkage of  claim 8 , wherein the fourth joint connects the second end of the first thrust linkage to the second end of the first bending restraint. 
     
     
         11 . The mechanical linkage of  claim 10 , wherein the fourth joint is a whiffletree joint. 
     
     
         12 . The mechanical linkage of  claim 11 , wherein the whiffletree joint connects the second end of the first bending restraint, the second end of the first thrust linkage, and the second end of the second thrust linkage to the pylon. 
     
     
         13 . The mechanical linkage of  claim 11 , wherein the fourth joint further includes a gimbal joint to connect the second joint to the pylon. 
     
     
         14 . The mechanical linkage of  claim 1 , further including an actuator to apply a force on the fan section of the gas turbine engine. 
     
     
         15 . The mechanical link of  claim 14 , wherein the actuator is a hydraulic actuator. 
     
     
         16 . A gas turbine engine comprising:
 a first section including a fan section;   a second section including a pylon; and   a mechanical linkage between the first section and the second section.   
     
     
         17 . The gas turbine engine of  claim 16 , wherein the mechanical linkage further includes a bending restraint. 
     
     
         18 . The gas turbine engine of  claim 17 , wherein the bending restraint further includes an actuator. 
     
     
         19 . An apparatus comprising:
 first means for mounting a gas turbine engine to a pylon;   second means for attaching a first bending restraint with respect to a fan section of the gas turbine engine; and   third means for attaching the first bending restraint to the pylon.   
     
     
         20 . The apparatus of  claim 19 , further including means for attaching a second bending restraint to the fan section of the gas turbine engine.