Thermal management of tail cone mounted generator
A gas turbine engine includes a turbine rotor connected to a main compressor rotor. A tail cone is mounted inward of an exhaust core flow. A generator rotor is adjacent a generator stator. The generator rotor and stator are mounted within the tail cone. A passage connects a bypass flow path to the tail cone. A cooling air compressor is operable within the passage. The turbine rotor drives a shaft to drive the generator rotor and the cooling compressor. A method is also disclosed.
1. A gas turbine engine comprising:
a turbine rotor connected to a main compressor rotor;
a tail cone mounted inward of an exhaust core flow;
a generator rotor adjacent a generator stator, said generator rotor and stator being mounted within said tail cone;
a passage connecting a bypass flow path to said tail cone;
a cooling air compressor operable within said passage; and
said turbine rotor driving a shaft to drive said generator rotor and said cooling compressor.
2. The gas turbine engine as set forth in claim 1 , wherein said tail cone is provided by an inner wall and an outer wall, and said cooling compressor is connected to deliver cooling air to a passage between said inner and outer walls.
3. The gas turbine engine as set forth in claim 2 , wherein said passage between said inner and outer walls extends across a majority of a circumference of said tail cone.
4. The gas turbine engine as set forth in claim 3 , wherein said passage between said inner and outer walls extends axially beyond a most downstream point on said generator.
5. The gas turbine engine as set forth in claim 1 , wherein said cooling compressor is also connected to deliver air across an outer periphery of said generator stator.
6. The gas turbine engine as set forth in claim 1 , wherein said generator rotor is supported by at least two bearings mounted at an axial location upstream of said generator rotor.
7. The gas turbine engine as set forth in claim 1 , wherein said passage is provided with an internal chamber receiving an output power lead from said generator stator to deliver electricity radially outwardly of said tail cone.
8. The gas turbine engine as set forth in claim 1 , wherein said shaft is connected to said generator rotor by a gear increase mechanism.
9. The gas turbine engine as set forth in claim 8 , wherein said gear increase mechanism drives said cooling compressor at a speed of rotation which is greater than a speed of rotation of said shaft.
10. The gas turbine engine as set forth in claim 9 , wherein a flexible connection connects said gear increase mechanism to said generator rotor and to said cooling compressor.
11. The gas turbine engine as set forth in claim 1 , wherein a pressure ratio provided by said cooling compressor is between 1.5 and 4.0.
12. A gas turbine engine comprising:
a turbine rotor connected to a main compressor rotor;
a tail cone mounted inward of an exhaust core flow path;
a generator rotor adjacent a generator stator, said generator rotor and said generator stator being mounted within said tail cone;
a passage connecting a bypass flowpath to said tail cone;
a cooling air compressor operable within said passage;
means for powering said cooling air compressor and said generator rotor.
13. The gas turbine engine as set forth in claim 12 , wherein the means for powering said cooling air compressor and said generator rotor is through a shaft of the turbine rotor directly or with a gearbox disposed therebetween.
14. A method of operating a gas turbine comprising the steps of:
driving a compressor rotor by a turbine rotor;
a shaft driven by said turbine rotor driving a generator rotor, said generator rotor positioned adjacent a generator stator, and said generator rotor and said generator stator being mounted within a tail cone; and
delivering cooling air to said generator and within said tail cone, by providing cooling air to a cooling air compressor, said cooling air compressor being connected to deliver air to said tail cone.
15. The method as set forth in claim 14 , wherein said tail cone is provided by an inner wall and an outer wall and cooling air is delivered to a passage, between said inner and outer walls.
16. The method as set forth in claim 15 , wherein said passage extends across a majority of a circumference of said tail cone.
17. The method as set forth in claim 16 , wherein said passage extends axially beyond a most downstream point on said generator.
18. The method as set forth in claim 14 , wherein said shaft is connected to said generator rotor by a gear increase mechanism.
19. The method as set forth in claim 18 , wherein said gear increase mechanism drives said cooling compressor at a speed of rotation which is greater than a speed of rotation of said shaft.