Rotor asymmetry

Abstract

A gas turbine engine has a section, such as a compressor section, with at least two spaced apart stator assemblies and an asymmetrical rotor assembly positioned between the spaced apart stator assemblies. The asymmetrical rotor assembly has a rotor array which is asymmetric about at least one diameter of the rotor assembly.

1 . A gas turbine engine comprising:
 an engine section having at least two spaced apart stator assemblies and an asymmetrical rotor assembly positioned between said spaced apart stator assemblies, wherein the asymmetrical rotor assembly has a rotor array which is asymmetric about at least one diameter of the rotor assembly.   
     
     
         2 . The gas turbine engine of  claim 1 , wherein said rotor assembly has a circumference with a first half and a second half and said rotor array has a first number of blades attached to said first half and a second number of blades attached to said second half, and the first number of blades is different in number from said second number of blades. 
     
     
         3 . The gas turbine engine of  claim 1 , wherein said engine section is a compressor section. 
     
     
         4 . The gas turbine engine of  claim 1 , wherein said engine section is a high pressure compressor section. 
     
     
         5 . The gas turbine engine of  claim 2 , wherein each of said rotor assemblies includes a hub, a rim defining said circumference, and a web connecting said hub to said rim. 
     
     
         6 . The gas turbine engine of  claim 1 , wherein at least one of said stator assemblies is an asymmetrical stator assembly. 
     
     
         7 . The gas turbine engine of  claim 1 , wherein at least one said stator assemblies is an asymmetrical cantilevered stator assembly. 
     
     
         8 . The gas turbine engine of  claim 1 , wherein said engine section has a plurality of asymmetrical rotor assemblies and each of said asymmetrical rotor assemblies is located between two spaced apart stator assemblies. 
     
     
         9 . The gas turbine engine of  claim 8 , wherein each of said asymmetrical rotor assemblies has said circumference with said first half and said second half and said first number of blades attached to said first half and said second number of blades attached to said second half, and the first number of blades is different from said second number of blades. 
     
     
         10 . The gas turbine engine of  claim 1 , wherein each of said blades has a tip that is disposed at a tip angle. 
     
     
         11 . The gas turbine engine of  claim 10 , wherein said tip angle is greater than zero. 
     
     
         12 . The gas turbine engine of  claim 8 , wherein each said blade has the same blade tip angle. 
     
     
         13 . The gas turbine engine of  claim 1 , wherein said asymmetrical rotor assembly comprises an integrally bladed rotor. 
     
     
         14 . A rotor assembly for use in a gas turbine engine comprising a rotor array which is asymmetric about at least one diameter of the rotor assembly. 
     
     
         15 . The rotor assembly according to  claim 14 , wherein said assembly comprises a disk having a rim defining a circumference, said circumference having a first half and a second half, and said rotor array comprises a first number of blades attached to said first half of said circumference and a second number of blades attached to said second half of said circumference, and the first number of blades is different in number from said second number of blades. 
     
     
         16 . A rotor assembly according to  claim 15 , wherein said disk further comprises a hub and a web connecting said hub to said rim. 
     
     
         17 . A rotor assembly according to  claim 15 , wherein at least one of said blades has a tip that is disposed at a tip angle relative to a centerline of said hub. 
     
     
         18 . A rotor assembly according to  claim 17 , wherein said angle is greater than zero. 
     
     
         19 . A rotor assembly according to  claim 17 , wherein each said blade has the same blade tip angle. 
     
     
         20 . A rotor assembly for use in a gas turbine engine comprising a rotor array which is asymmetric about a single diameter of the rotor assembly.