Cooling system for tail cone mounted generator
An engine system includes an engine duct and a tail cone arranged radially inwardly of the engine duct. The tail cone has an outer surface and an inner surface. A generator housing is arranged in the tail cone. The generator housing includes an outer surface portion spaced from the inner surface of the tail cone. A generator is mounted in the generator housing. An air duct extends from the generator, through the generator housing, through the tail cone, and through the engine duct. The air duct includes an opening exposed to an air stream passing over the engine duct.
1. An engine system comprising:
a high pressure spool;
a low pressure spool connected to the high pressure spool;
an engine duct extending about the high pressure spool and the low pressure spool, the engine duct including an outer surface section exposed to an external airstream;
a tail cone arranged radially inwardly of the engine duct, the tail cone having an outer surface and an inner surface;
a generator housing arranged in the tail cone, the generator housing including an outer surface portion spaced from the inner surface of the tail cone;
a generator mounted in the generator housing;
an air duct extending from the generator, through the generator housing, through the tail cone, and through the engine duct, the air duct including a first end arranged in the tail cone and a second end projecting outwardly of the outer surface section of the engine duct aft of the low pressure spool, the second end including an opening exposed to the external air stream passing over the engine duct; and
another air duct extending from the generator, through the generator housing, through the tail cone, and through the engine duct, the another air duct including another opening exposed to an air stream passing over the engine duct,
wherein the air duct comprises an inlet duct for directing an air flow into the generator housing and the another air duct comprises an outlet duct for directing the air flow out from the generator housing.
2. The engine system according to claim 1 , further comprising: a plenum defined between the outer surface portion of the generator housing and the inner surface of the tail cone.
3. The engine system according to claim 2 , wherein the outlet duct is fluidically connected to the plenum.
4. The engine system according to claim 3 , wherein the generator includes a drive shaft connectable to a low pressure spool of a turbine engine, the drive shaft having a hollow interior fluidically connected to the plenum through an outlet passage.
5. The engine system according to claim 1 , wherein the opening of the air duct faces a first direction relative to the engine duct and the another opening of the another air duct faces a second direction that is distinct from the first direction.
6. The engine system according to claim 5 , wherein the first direction is directly opposite the second direction.
7. The engine system according to claim 1 , further comprising: a plurality of electrical conductors connected to the generator, the plurality of electrical conductors pass from the generator through the air duct.
8. An aircraft comprising:
a fuselage;
a wing supported by the fuselage;
an engine system supported by the fuselage, the engine system including a turbine engine including a high pressure spool, a low pressure spool connected to the high pressure spool, and an engine duct extending about the high pressure spool and the low pressure spool, the engine duct including an outer surface section exposed to an external airstream;
a tail cone arranged radially inwardly of the engine duct, the tail cone having an outer surface and an inner surface;
a generator housing arranged in the tail cone, the generator housing including an outer surface portion spaced from the inner surface of the tail cone;
a generator mounted in the generator housing;
an air duct extending from the generator, through the generator housing, through the tail cone, and through the engine duct, the air duct including a first end arranged in the tail cone and a second end projecting outwardly of the outer surface section of the engine duct aft of the low pressure spool, the second end including an opening exposed to the external air stream passing over the engine duct; and
another air duct extending from the generator, through the generator housing, through the tail cone, and through the engine duct, the another air duct including another opening exposed to an air stream passing over the engine duct,
wherein the air duct comprises an inlet duct for directing an air flow into the generator housing and the another air duct comprises an outlet duct for directing the air flow out from the generator housing.
9. The aircraft according to claim 8 , further comprising: a plenum defined between the outer surface portion of the generator housing and the inner surface of the tail cone.
10. The aircraft according to claim 9 , wherein the outlet duct is fluidically connected to the plenum.
11. The aircraft according to claim 10 , wherein the generator includes a drive shaft connectable to a low pressure spool of the turbine engine, the drive shaft having a hollow interior fluidically connected to the plenum through an outlet passage.
12. The aircraft according to claim 8 , wherein the opening of the air duct faces a first direction relative to the engine duct and the another opening of the another air duct faces a second direction that is distinct from the first direction.
13. The aircraft according to claim 12 , wherein the first direction is directly opposite the second direction.
14. The aircraft according to claim 8 , further comprising: a plurality of electrical conductors connected to the generator, the plurality of electrical conductors pass from the generator through the air duct.
15. The aircraft according to claim 8 , wherein the turbine engine is supported in a nacelle mounted to the fuselage.
16. The aircraft according to claim 8 , wherein the wing is fixedly mounted to the fuselage.