COMPRESSOR SECTION WITH TIE SHAFT COUPLING AND CANTILEVER MOUNTED VANES
A compressor section to be mounted in a gas turbine engine has a plurality of compressor rotors arranged from an upstream location toward a downstream location. A tie shaft applies an axial force at one end of the compressor section to a downstream one of the compressor rotors, and biases the compressor rotors against a hub at the opposite end. Vane sections are mounted intermediate the compressor rotors. The vane sections include at least some variable vanes driven by actuators mounted at a radially outer position and at least some of the fixed vanes are cantilever mounted , such that they are spaced from a compressor rotor, but unsecured at a radially inner end.
1 . A compressor section to be mounted in a gas turbine engine comprising:
a plurality of compressor rotors arranged from an upstream location toward a downstream location;
upstream and downstream hubs that bound the compressor rotor stack;
a tie shaft to apply a force at a downstream end of said compressor section to a downstream one of said compressor rotors; and
vane sections being mounted intermediate said compressor rotors, said vane sections including at least some variable vanes driven by actuators mounted at a radially outer position, and at least some of said fixed vanes being cantilever mounted from an outer housing, such that they are spaced from a compressor rotor, but unsecured at a radially inner end.
2 . The compressor section as set forth in claim 1 , wherein said plurality of cantilever mounted fixed vanes are at a downstream location.
3 . The compressor section as set forth in claim 2 , wherein said downstream one of said compressor rotors is an axial compressor.
4 . The compressor section as set forth in claim 1 , wherein said downstream one of said compressor rotors is an axial compressor.
5 . A gas turbine engine comprising:
a compressor section;
a combustion section downstream of said compressor section;
a turbine section downstream of said combustion section, said turbine section including turbine rotors to drive and rotate rotors associated with said compressor section; and
said compressor section including a plurality of compressor rotors arranged from an upstream location toward a downstream location, a tie shaft to apply a force at a downstream end of said compressor section to a downstream one of said compressor rotors, to clamp said compressor rotors against an upstream hub and provide the necessary friction to transmit torque, vane sections being mounted intermediate said compressor rotors, said vane sections including at least some variable vanes driven by actuators mounted at a radially outer position, and at least some of said fixed vanes being cantilever mounted from an outer housing, such that they are spaced from a compressor rotor, but unsecured at a radially inner end.
6 . The gas turbine engine as set forth in claim 5 , wherein said plurality of cantilever mounted fixed vanes are at a downstream location.
7 . The gas turbine engine as set forth in claim 6 , wherein said downstream one of said compressor rotors is an axial compressor.
8 . The gas turbine engine as set forth in claim 5 , wherein said downstream one of said compressor rotors is an axial compressor.