Gas turbine engine breather exhaust oil collector

• US 8,621,839 B2
• Filed: 09/28/2009
• Issued: 01/07/2014
• Est. Priority Date: 09/28/2009
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Alecu, Daniel T., Olver, Bryan William
• Primary Examiner(s): Kim, Ted
• Application Number:
  US12/568,006
• Publication Number:
  US 20120060508A1
• Time in Patent Office: 1,562 Days
• Field of Search: 60/390.8, 602/261, 60/390.94, 184/6.11, 554/101
• US Class Current: 60/39.08
• CPC Class Codes: F01D 25/20 using lubrication pumps
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: F05D 2260/60 Fluid transfer

Abstract

A gas turbine engine oil system has an air-oil separator for removing air from an air/oil mixture. A breather tube is connected to an exhaust of the air-oil separator for receiving hot air removed from the air/oil mixture in the air-oil separator. The gas turbine engine oil separator exhaust is directed in a cooled oil collector to cause the oil mist remaining in the air at the exit from the engine air-oil separator to condensate. The oil condensate is returned back into the engine oil system.

Claims

1. A gas turbine engine oil system comprising an air-oil separator for removing air from an air/oil mixture, a breather tube connected to an exhaust of the air-oil separator for receiving hot air removed from the air/oil mixture in the air-oil separator, the hot air still carrying oil aerosol and vapour, an oil collector having an outer surface exposed to a coolant flow and an inner surface defining a cooled chamber, the breather tube extending upwardly into the cooled chamber of the oil collector, the oil collector having an internal volume for collecting oil condensate separated from the hot air discharged in the cooled chamber during engine running, the breather tube having multiple perforations distributed at different axial position along a distal end portion thereof to cause a two-way fluid exchange between the hot air inside the breather tube and cooler air in the cooled chamber outside the breather tube, an exhaust window defined in said oil collector for venting the air from the cooled chamber, and a drain in said oil collector for returning the oil condensate collected during engine running in the internal volume of the oil collector back into an engine gear box at engine shut down when air flow through the breather tube ceases.

2. The gas turbine engine oil system defined in claim 1, wherein the multiple perforations are oriented away from the exhaust window of the oil collector.

3. The gas turbine engine oil system defined in claim 1, wherein the oil collector is integrated in a strut extending through an air bypass passage of a turbofan engine.

4. The gas turbine engine oil system defined in claim 3, wherein the exhaust window opens to the air bypass passage.

5. The gas turbine engine oil system defined in claim 3, wherein said exhaust window is defined in a trailing edge portion of the strut.

6. The gas turbine engine oil system defined in claim 5, wherein the perforations face opposite the oil collector ventilation window.

7. The gas turbine engine oil system defined in claim 5, wherein at least four vortex generators are provided on the exterior of the strut to impart a swirl to the air flowing through the exhaust window.

8. The gas turbine engine oil system defined in claim 1, wherein the breather tube has a top open distal end, said top open distal end being spaced from the inner surface of the oil collector in the cooled chamber.

9. A gas turbine engine oil system comprising a breather tube connected in fluid flow communication with a gas outlet of an air-oil separator, the breather tube receiving a flow of hot air separated from the oil in the air-oil separator, and an oil collector disposed downstream of the air-oil separator for recuperating at least a portion of the oil remaining in the flow of hot air vented from the air-oil separator, the oil collector comprising a cooled enclosure mounted about a delivery end portion of the breather tube in a coolant flow passage, the cooled enclosure having a wall including opposed outer and inner surfaces in heat exchange relationship, the wall, including its inner and outer surfaces, being cooled by a flow of coolant flowing over the outer surface of the wall in the coolant passage, the coolant flowing over the cooled enclosure causing the oil carried by the hot air flowing through an outlet of the breather tube to condense in the cooled enclosure, the cooled enclosure having an oil drain and a gas exhaust;

the outlet of the breather tube comprises a plurality of holes distributed at different axial positions along the delivery end portion of the breather tube, the plurality of holes providing a two-way fluid exchange between the hot air inside the breather tube and cooler air in the cooled enclosure outside the breather tube.

10. The gas turbine engine oil system defined in claim 9, wherein at least one baffle is provided inside the cooled enclosure to prevent oil condensate from flowing out of the cooled enclosure through the gas exhaust.

11. The gas turbine engine oil system defined in claim 9, wherein the outlet of the breather tube comprises a plurality of holes vertically distributed along an upper end portion of the breather tube.

12. The gas turbine engine oil system defined in claim 9, wherein the cooled enclosure is integrated in a service strut extending through a gas turbine engine bypass passage.

13. The gas turbine engine oil system defined in claim 12, wherein the gas exhaust comprises a window defined in a trailing edge of the service strut, the window opening to the gas turbine bypass passage.

14. The gas turbine engine oil system defined in claim 13, wherein a plurality of vertically spaced-apart holes are defined in the breather tube, all said plurality of vertically spaced-apart holes facing away from said window.

15. The gas turbine engine oil system defined in claim 13, wherein fluid flow deflectors are provided on the service strut adjacent said window, one flow deflector being provided at each corner of the window.