Aero engine with a bearing chamber and an appliance for introducing oil

Patent metadata

Field	Value
Publication number	US-10041410-B2
Application number	US-201514847500-A
Country	US
Kind code	B2
Filing date	Sep 8, 2015
Priority date	Sep 11, 2014
Publication date	Aug 7, 2018
Grant date	Aug 7, 2018

Abstract

An aero engine with a bearing chamber, which is confined by a first wall area and a second wall area which is embodied so as to be rotatable with respect to the first wall area and in which at least one bearing appliance as well as at least one appliance for introducing oil are arranged. Oil can be introduced into the bearing chamber via at least one appliance for introducing oil substantially against a rotational direction of the first wall area and/or of the second wall area and substantially tangentially to at least one surface of at least one wall area that is facing the bearing chamber.

First claim

The invention claimed is:

1. An aero engine comprising:
a bearing chamber that is confined by a first wall area and a second wall area which is rotatable with respect to the first wall area;
a bearing arranged in the bearing chamber;
an oil injector including an oil discharge opening arranged in the bearing chamber for introducing oil into the bearing chamber counter to a rotational direction of at least one chosen from the first wall area and the second wall area and tangentially to at least one surface of the at least one chosen from the first wall area and the second wall area that is facing an interior of the bearing chamber.

2. The aero engine according to claim 1 , wherein the first wall area forms a stationary external wall during operation of the aero engine and the second wall area forms a rotating internal wall of the bearing chamber during operation of the aero engine.

3. The aero engine according to claim 2 , wherein the first wall area and the second wall area of the bearing chamber are connected to each other in a rotatable manner via the bearing.

4. The aero engine according to claim 3 , wherein the oil injector introduces the oil into an area of the bearing chamber that is close to the at least one chosen from the first wall area and the second wall area.

5. The aero engine according to claim 4 , wherein the oil injector introduces the oil into the bearing chamber as a spray cone.

6. The aero engine according to claim 5 , wherein the oil injector introduces the oil into the bearing chamber as an elliptical spray cone.

7. The aero engine according to claim 6 , and further comprising a deflector positioned in a discharge path of the oil discharge opening.

8. The aero engine according to claim 7 , wherein the deflector includes a convex area.

9. The aero engine according to claim 1 , wherein the oil discharge opening is elliptical.

10. The aero engine according to claim 1 , wherein the oil injector is arranged in the area of an outlet opening for an air-oil mixture from the bearing chamber.

11. The aero engine according to claim 1 , wherein the oil injector is arranged in an area of an oil outlet from the bearing chamber.

12. The aero engine according to claim 1 , and further comprising a plurality of the oil injector respectively arranged to be distributed over a circumference of the at least one chosen from the first wall area and the second wall area.

13. The aero engine according to claim 1 , and further comprising at least one chosen from an oil separator and a cyclone arranged downstream of an outlet opening for an air-oil mixture from the bearing chamber.

14. The aero engine according to claim 1 , wherein the first wall area and the second wall area of the bearing chamber are connected to each other in a rotatable manner via the bearing.

15. The aero engine according to claim 1 , wherein the oil injector introduces the oil into an area of the bearing chamber that is close to the at least one chosen from the first wall area and the second wall area.

16. The aero engine according to claim 1 , wherein the oil injector introduces the oil into the bearing chamber as a spray cone.

17. The aero engine according to claim 1 , wherein the oil injector introduces the oil into the bearing chamber as an elliptical spray cone.

18. The aero engine according to claim 1 , and further comprising a deflector positioned in a discharge path of the oil discharge opening.

19. The aero engine according to claim 18 , wherein the deflector includes a convex area.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Beier Juergen

Classifications

• F05D2250/14

  elliptical · CPC title

• F16C2360/23

  Gas turbine engines · CPC title

• F05D2250/232

  conical · CPC title

• F16C33/6659

  Details of supply of the liquid to the bearing, e.g. passages or nozzles · CPC title

• F02C7/06 Primary

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title