Gas Turbine Engine With Accessory Gear Box

Abstract

A nacelle for incorporation into a gas turbine engine has an inner wall defining a bypass duct, and an outer wall, at least one drive shaft extending through said inner wall, said at least one drive shaft to be connected to a gas turbine engine receiving the nacelle, said at least one drive shaft being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being received between said inner and outer walls of said nacelle. A gas turbine engine is also disclosed.

1 . A nacelle for incorporation into a gas turbine engine, comprising:
 a nacelle having an inner wall defining a bypass duct, and an outer wall, at least one drive shaft extending through said inner wall, said at least one drive shaft to be connected to a gas turbine engine receiving the nacelle, said at least one drive shaft being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being received between said inner and outer walls of said nacelle.   
     
     
         2 . The nacelle as set forth in  claim 1 , wherein at least one of said gear boxes includes a starter for the gas turbine engine. 
     
     
         3 . The nacelle as set forth in  claim 1 , wherein at least one of said at least two gear boxes drives a fuel pump and a lubricant pump to support the gas turbine engine. 
     
     
         4 . The gas turbine engine as set forth in  claim 1 , wherein said at least one drive shaft includes at least two drive shafts, with one of said at least two drive shafts being connected to each said at least two accessory gear boxes. 
     
     
         5 . The nacelle as set forth in  claim 1 , wherein said at least two accessory gear boxes are received axially between an upstream end and a downstream end of said nacelle. 
     
     
         6 . A gas turbine engine comprising:
 a fan, a compressor section, a combustor section, and a turbine section, said turbine section for driving a shaft to in turn drive said fan and said compressor, at least one accessory shaft to be connected for rotation with said turbine section;   a nacelle having an inner wall defining a bypass duct receiving bypass air from said fan, and an outer wall, said at least one drive shaft extending through said inner wall, and being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being received between said inner and outer walls of said nacelle.   
     
     
         7 . The engine as set forth in  claim 7 , wherein at least one of said gear boxes includes a starter for the gas turbine engine. 
     
     
         8 . The engine as set forth in  claim 7 , wherein at least one of said at least two gear boxes drives a fuel pump and a lubricant pump to support the gas turbine engine. 
     
     
         9 . The engine as set forth in  claim 6 , wherein said at least one drive shaft includes at least two drive shafts, with one of said at least two drive shafts being connected to each said at least two accessory gear boxes. 
     
     
         10 . The engine as set forth in  claim 6 , wherein said at least two accessory gear boxes are received axially between an upstream end and a downstream end of said nacelle. 
     
     
         11 . The engine as set forth in  claim 6 , wherein said engine can be divided into two halves, and a mount bracket for mounting said engine to an aircraft is in one of the halves, and said at least two accessory gear boxes are in an opposed half. 
     
     
         12 . A gas turbine engine comprising:
 a fan, a compressor section, a combustor section, and a turbine section, said turbine section for driving a shaft to in turn drive said fan and said compressor, at least one accessory shaft to be connected for rotation with said turbine section;   a nacelle having an inner wall defining a bypass duct receiving bypass air from said fan, and an outer wall, said at least one drive shaft extending through said inner wall, and being connected to drive at least two accessory gear boxes, with said at least two accessory gear boxes being received between said inner and outer walls of said nacelle;   at least one of said gear boxes includes a starter for the gas turbine engine;   at least another of said at least two gear boxes drives a fuel pump and a lubricant pump to support the gas turbine engine;   said at least two accessory gear boxes are received axially between an upstream end and a downstream end of said nacelle; and   said engine can be divided into two halves, and a mount bracket for mounting said engine to an aircraft is in one of the halves, and said at least two accessory gear boxes are in an opposed half.   
     
     
         13 . The engine as set forth in  claim 12 , wherein said at least one drive shaft includes at least two drive shafts, with one of said at least two drive shafts being connected to each said at least two accessory gear boxes.