Mechanical drive shaft arrangements for tail cone generators
In accordance with at least one aspect of this disclosure, there is provided a drive shaft system. In embodiments, the drive shaft system includes a generator shaft extending along a longitudinal axis with a longitudinal bore defined through the generator shaft. A thru shaft extends through the longitudinal bore of the generator shaft. In embodiments, the thru shaft includes, a front coupler mount at a first end operative to receive torque input, and a rear coupler mount at a second end opposite the first end.
1. An aircraft drive shaft system comprising:
a generator shaft extending between a first end and a second end along a longitudinal axis with a longitudinal bore defined through the generator shaft, the generator shaft having a rear generator shaft coupler mount;
a thru shaft extending through the longitudinal bore of the generator shaft, the thru shaft having:
a front thru shaft coupler mount at a first end of the thru shaft operative to receive torque input; and
a rear thru shaft coupler mount at a second end of the thru shaft opposite the first end,
wherein the rear generator shaft coupler mount is coupled to the rear thru shaft coupler mount via a rear coupling operative to transmit torque from the front thru shaft coupler mount, through the thru shaft, and into the generator shaft;
wherein each of the rear through shaft coupler mount and the rear generator shaft coupler mount has n vertices, each vertex of the n vertices including a bore, and
wherein the rear coupling includes 2n vertices corresponding to each vertex of each respective one of the rear through shaft coupler mount and the rear generator shaft coupler mount, each vertex of the rear coupling having a bore operative to receive a fastener, the fastener extending through each respective bore of the rear coupling and a corresponding one of the bores of the respective one of the rear through shaft coupler mount and the rear generator shaft coupler mount.
2. The system as recited in claim 1 , wherein the rear thru shaft coupler mount is indirectly operatively connected the generator shaft via the rear coupling.
3. The system as recited in claim 1 , further comprising a shaft drive having a front coupler mount operative to fasten to the front thru shaft coupler mount to transmit torque from the shaft drive to the generator shaft through the thru shaft.
4. The system as recited in claim 3 , further comprising a front coupling, wherein the front coupler mount of the shaft drive is fastened directly to the front coupling, and wherein the front thru shaft coupler mount is directly fastened to the front coupling.
5. The system as recited in claim 3 , wherein the shaft drive includes a splined section.
6. The system as recited in claim 1 , further comprising a rotor operatively connected to the generator shaft to rotate within a generator housing to generate electrical energy.
7. An aircraft system comprising:
a gas turbine engine having a compressor section, a turbine section, and a spool shaft operatively connecting the compressor section to be driven by the turbine section;
a drive shaft system including:
a generator shaft extending between a first end and a second end along a longitudinal axis with a longitudinal bore defined through the generator shaft;
a thru shaft extending through the longitudinal bore of the generator shaft, the thru shaft having:
a front thru shaft coupler mount at a first end of the thru shaft operative to receive torque input; and
a rear thru shaft coupler mount at a second end of the thru shaft opposite the first end, wherein the generator shaft includes a rear generator shaft coupler mount at the second end of the generator shaft that is coupled to the rear thru shaft coupler mount operative to transmit torque from the front thru shaft coupler mount, through the thru shaft, and into the generator shaft, wherein the thru shaft is operatively connected to the spool shaft;
a rotor operatively connected to the generator shaft to rotate within a generator housing to generate electrical energy;
a stator operatively connected to the generator housing radially outward of the rotor; and
a tail cone at an outlet of the turbine section, wherein the rotor and stator are mounted in the tail cone.
8. The aircraft system as recited in claim 7 , wherein the gas turbine engine is selected from the group consisting of: turbojet, turbofan, turboprop, or turboshaft.
9. The aircraft system as recited in claim 7 , further comprising a coupling, wherein the rear thru shaft coupler mount of the thru shaft is fastened directly to the coupling, and wherein the rear generator shaft coupler mount is fastened directly to the coupling.
10. The aircraft system as recited in claim 9 , wherein each of the rear thru shaft coupler mount and the rear generator shaft coupler mount has n vertices, wherein each vertex of the n vertices includes a bore,
wherein the coupling includes 2n vertices corresponding to each vertex of each respective one of the rear thru shaft coupler mount and the rear generator shaft coupler mount, wherein each vertex of the coupling includes a bore operative to receive a fastener, where the fastener extends through each respective bore of the coupling and a corresponding one of the bores of the respective one of the rear through shaft coupler mount and the rear generator shaft coupler mount.
11. The system as recited in claim 7 , wherein the rear thru shaft coupler mount is indirectly operatively connected the generator shaft via a coupling.
12. The system as recited in claim 7 , wherein the spool shaft includes a front coupler mount operative to fasten to the front thru shaft coupler mount of the thru shaft operative to transmit torque from the spool shaft to the generator shaft through the thru shaft.
13. The system as recited in claim 12 , wherein the coupling is a rear coupling, and further comprising a front coupling, wherein the front coupler mount of the spool shaft is fastened directly to the front coupling, and wherein the front thru shaft coupler mount is directly fastened to the front coupling.