GAS TURBINE ENGINE WITH TIE SHAFT FOR AXIAL HIGH PRESSURE COMPRESSOR ROTOR
A compressor section to be mounted in a gas turbine engine has a plurality of axial 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 and biases the compressor rotors against a hub at the opposite end. The downstream compressor is an axial compressor rotor. A gas turbine engine incorporating this structure is also claimed.
1 . A compressor section to be mounted in a gas turbine engine comprising:
a plurality of axial compressor rotors arranged from an upstream rotor toward a downstream rotor;
upstream and downstream hubs at ends of the compressor rotor stack and join it to the shaft
a tie shaft to apply a force at the downstream hub of said compressor section to hold said plurality of axial compressor rotors together, and provide the friction necessary to transmit torque; and
said downstream rotor being an axial compressor rotor.
2 . The compressor section as set forth in claim 1 , wherein said downstream hub extends radially outwardly from a radially inner end, said radially inner end abutting a securement member to be secured to the tie shaft of a gas turbine engine, and a radially outer end abutting said downstream rotor.
3 . The compressor section as set forth in claim 2 , wherein said radially outer end including a contact face on said downstream rotor, said contact face being radially inward of a compressor blade in said downstream rotor such that air compressed by said downstream rotor passes radially outwardly of said downstream hub.
4 . The compressor section as set forth in claim 3 , wherein said securement member applies an axial force to said downstream hub.
5 . The compressor section as set forth in claim 1 , wherein said plurality of axial compressor rotors together form a high pressure compressor section.
6 . 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 compressor rotors associated with said compressor section; and
said compressor rotors include a plurality of compressor rotors arranged from an upstream rotor toward a downstream rotor, and a tie shaft to apply a force at said compressor rotor via a downstream hub, to clamp said compressor rotors against an upstream hub to provide friction to transmit torque, and said downstream compressor rotor being an axial compressor rotor.
7 . The gas turbine engine as set forth in claim 6 , wherein said downstream hub extends radially outwardly from a radial inner end, said radially inner end abutting a securement member, and said radially outer end abutting said downstream rotor.
8 . The gas turbine engine as set forth in claim 7 , wherein said radially outer end including a contact face at said downstream rotor, said contact face being radially inward of a compressor blade in said downstream compressor rotor such that air compressed by said downstream compressor rotor passes radially outwardly of said downstream tie shaft.
9 . The gas turbine engine as set forth in claim 8 , wherein said securement member is tightened on a tie shaft.
10 . The gas turbine engine as set forth in claim 6 , wherein said plurality of compressor rotors together form a high pressure compressor section and there is an upstream low pressure compressor upstream of said upstream tie shaft.