Aeroderivative jet engine accessory starter relocation to main shaft—directly connected to HPC shaft
In one aspect, the present disclosure is directed to a gas turbine starting system that includes a shaft coupling a compressor and a turbine. An annular housing extends circumferentially around the shaft such that the annular housing defines a compartment. A flange extends radially outward from the annular housing for mounting the annular housing to a stationary wall. A starter is positioned in the compartment. A collar rotatably couples to the annular housing and selectively couples to the starter. The collar includes a radially inner surface having a plurality of splines for engaging the shaft. The starter, when activated, rotates the collar, which rotates the shaft to start the gas turbine.
1. A gas turbine starting system, comprising:
a shaft coupling a high pressure compressor and a turbine;
an annular housing extending circumferentially around the shaft, wherein the annular housing defines a compartment, and wherein the annular housing is located axially between the high pressure compressor and a low pressure compressor;
a flange extending radially outward from the annular housing for mounting the annular housing to a stationary wall;
an electric starter motor including a rotor and a stator, the rotor and stator positioned in the compartment; and
a collar rotatably coupled to the annular housing and selectively coupled to the electric starter motor such that the rotor and stator of the electric starter motor is positioned axially between the collar and the flange; the collar comprising a radially inner surface comprising a plurality of splines for engaging the shaft;
wherein the electric starter motor, when activated, rotates the collar, which rotates the shaft to start a gas turbine.
2. The gas turbine starting system of claim 1 , wherein the shaft comprises a high pressure shaft.
3. The gas turbine starting system of claim 2 , wherein the collar rotatably couples to an upstream end of the high pressure shaft.
4. The gas turbine starting system of claim 3 , wherein the annular housing extends circumferentially around the high pressure shaft and a low pressure shaft.
5. The gas turbine starting system of claim 1 , wherein the annular housing comprises a first axial end and a second axial end, and further wherein the collar rotatably couples to the first axial end and an annular boss extends axially outward from the second axial end.
6. The gas turbine starting system of claim 5 , wherein the collar extends axially outward from the first axial end of the annular housing.
7. The gas turbine starting system of claim 1 , wherein the flange defines a plurality of apertures extending therethrough.
8. A gas turbine, comprising:
a compressor section having a high pressure compressor and a low pressure compressor;
a combustor;
a turbine section;
a shaft coupling the high pressure compressor and the turbine section;
an annular housing extending circumferentially around the shaft, wherein the annular housing defines a compartment, and wherein the annular housing is located axially between the high pressure compressor and a low pressure compressor;
a flange extending radially outward from the annular housing for mounting the annular housing to a stationary wall;
an electric starter motor including a rotor and a stator, the rotor and stator positioned in the compartment; and
a collar rotatably coupled to the annular housing and selectively coupled to the electric starter motor such that the rotor and stator of the electric starter motor is positioned axially between the collar and the flange; the collar comprising a radially inner surface comprising a plurality of splines for engaging the shaft;
wherein the electric starter motor, when activated, rotates the collar, which rotates the shaft to start the gas turbine.
9. The gas turbine of claim 8 , wherein the shaft comprises a high pressure shaft.
10. The gas turbine of claim 9 , wherein the collar rotatably couples to an upstream end of the high pressure shaft.
11. The gas turbine of claim 10 , wherein the annular housing extends circumferentially around the high pressure shaft and a low pressure shaft.
12. The gas turbine of claim 8 , wherein the annular housing comprises a first axial end and a second axial end, and further wherein the collar rotatably couples to the first axial end and an annular boss extends axially outward from the second axial end.
13. The gas turbine of claim 12 , wherein the collar extends axially outward from the first axial end of the annular housing.
14. The gas turbine of claim 8 , wherein the flange defines a plurality of apertures extending therethrough.
15. The gas turbine of claim 8 , wherein the annular housing is positioned in a sump within the compressor section.
16. The gas turbine of claim 8 , wherein the annular housing is positioned radially inward of a radially inner wall of the compressor section.