Heat exchange system for a power gear box, a power gear box and a turbo engine with a power gear box
A heat exchange system for a power gear box mechanically coupling at least low pressure compressor stage with at least one turbine stage in a turbo engine, in particular an aircraft turbo engine, is provided. At least one heat transfer device is enclosed, embedded and/or attached with the casing of the power gear box, wherein at least one airflow is directed to the at least one heat transfer device for thermally controlling the power gear box.
1. A heat exchange system for a power gear box mechanically coupling at least one low pressure compressor stage with at least one turbine stage in a turbo engine, comprising:
a casing of the power gear box,
at least one heat transfer device which is at least one chosen from enclosed within and embedded in a portion of the casing that is positioned directly radially outwardly of a gear set of the power gear box,
a passage for directing at least one airflow to the at least one heat transfer device for thermally controlling the power gear box.
2. The heat exchange system according to claim 1 , wherein the at least one heat transfer device thermally links the power gear box containing oil with an exterior of the power gear box.
3. The heat exchange system according to claim 1 , wherein the at least one airflow is taken from a region downstream from at least one chosen from a fan of the turbo engine and a cone of the fan to cool the power gear box.
4. The heat exchange system according to claim 1 , wherein the at least one heat transfer device includes a cold side connected to at least one airflow downstream from a fan of the turbo engine and upstream of an annulus of a core of the turbo engine.
5. The heat exchange system according to claim 4 , wherein the at least one heat transfer device is connected to an airflow taken from compressor bleed air to heat up the power gear box.
6. The heat exchange system according to claim 1 , wherein the at least one heat transfer device is located in an axial direction of the turbo engine partially or completely between a tip of a fan cone of the turbo engine and the power gear box.
7. The heat exchange system according to claim 1 , wherein the at least one heat transfer device is positioned at least partially on a circumference of at least one chosen from the power gear box and the casing.
8. The heat exchange system according to claim 7 , wherein the at least one heat transfer device is positioned completely around a circumference of at least one chosen from the power gear box and the casing.
9. The heat exchange system according to claim 1 , wherein an airflow is heated by the at least one heat transfer device to be used for anti-icing.
10. The heat exchange system according to claim 1 , wherein the at least one heat transfer device comprises at least partially a porous medium comprising, at least partially, oil channels for enhancing heat transfer.
11. The heat exchange system according to claim 10 , wherein the porous medium is in thermal contact with the power gear box and comprises at least one chosen from a metal foam and a 3D printed mesh.
12. The heat exchange system according to claim 1 , and further comprising at least one valve system controlling at least one chosen from at least one input airflow, at least one input compressor airflow and at least one exit airflow from the at least one heat transfer device.
13. The heat exchange system according to claim 1 , wherein the at least one heat transfer device comprises a material with a higher thermal conductivity than the casing of the power gear box.
14. The heat exchange system according to claim 13 , wherein the material is at least one chosen from copper, aluminum, nickel, tungsten, molybdenum and an alloy comprising at least two chosen from copper, aluminum, nickel, tungsten and molybdenum.
15. The heat exchange system according to claim 1 , wherein the at least one heat transfer device is manufactured by a generative process including a laser cladding process.
16. A power gear box of a turbo engine coupled with at least one heat exchange system according to claim 1 .
17. A turbo engine with at least one power gear box according to claim 16 .
18. An aircraft turbo engine with at least one power gear box according to claim 17 .
19. A heat exchange system for a power gear box mechanically coupling at least one low pressure compressor stage with at least one turbine stage in a turbo engine, comprising:
a casing of the power gear box,
at least one heat transfer device which is at least one chosen from enclosed within, embedded in and attached to the casing of the power gear box,
a passage for directing at least one airflow to the at least one heat transfer device for thermally controlling the power gear box;
wherein the at least one heat transfer device is located in an axial direction of the turbo engine partially or completely between a tip of a fan cone of the turbo engine and the power gear box.
20. A heat exchange system for a power gear box mechanically coupling at least one low pressure compressor stage with at least one turbine stage in a turbo engine, comprising:
a casing of the power gear box,
at least one heat transfer device which is at least one chosen from enclosed within, embedded in and attached to the casing of the power gear box,
a passage for directing at least one airflow to the at least one heat transfer device for thermally controlling the power gear box;
wherein the at least one heat transfer device comprises a porous medium comprising at least partially, oil channels for enhancing heat transfer.