Jet engine with multiple chambers and a bearing chamber support

• US 10,458,276 B2
• Filed: 10/19/2016
• Issued: 10/29/2019
• Est. Priority Date: 10/19/2015
• Status: Active Grant

• Current Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Inventors: Friedl, Winfried-Hagen
• Primary Examiner(s): Brockman, Eldon T
• Application Number:
  US15/297,592
• Publication Number:
  US 20170107854A1
• Time in Patent Office: 1,105 Days
• CPC Class Codes: F01D 11/04 using sealing fluid, e.g. steam
• CPC Class Codes: F01D 25/125 of bearings
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 25/183 Sealing means
• CPC Class Codes: F02C 7/25 Fire protection or prevention in general A62
• CPC Class Codes: F02K 1/805 Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2230/21 by casting
• CPC Class Codes: F05D 2250/185 serpentine-like
• CPC Class Codes: F05D 2260/6022 of leakage having past a seal
• CPC Class Codes: F05D 2260/608 Aeration, ventilation, dehumidification or moisture removal of closed spaces
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A jet engine with a bearing chamber, a sealing chamber, a de-aeration chamber and a bearing chamber support, the support delimiting the bearing chamber comprising at least one bearing appliance in certain areas. The bearing chamber is separated from the sealing chamber via a sealing appliance, with the sealing chamber being separated via a further sealing appliance from the de-aeration chamber that is arranged at the side of the sealing chamber facing away from the bearing chamber. The sealing chamber is connected to a sealing air conduit, by which the bearing chamber can be supplied with a sealing air volume flow. The de-aeration chamber is connected to a de-airing appliance via which a volume flow can be discharged from the de-aeration chamber into a core flow channel of the jet engine. The de-airing appliance is embodied as at least one air extraction duct with a tubular flow cross-section.

Claims

1. A jet engine, comprising:

a bearing chamber,

a sealing chamber,

a de-aeration chamber, and

a bearing chamber support that delimits the bearing chamber and includes at least one bearing appliance in certain areas,

wherein the bearing chamber is separated from the sealing chamber via a sealing appliance,

a further sealing appliance separating the sealing chamber from the de-aeration chamber that is arranged at a side of the sealing chamber that is facing away from the bearing chamber, and

wherein the sealing chamber is connected to a sealing air conduit by which the bearing chamber is supplied with a sealing air volume flow, and

wherein the de-aeration chamber is connected to a de-airing appliance via which a volume flow can be discharged from the de-aeration chamber into a core flow channel of the jet engine,

wherein the de-airing appliance includes an air extraction duct with a tubular flow cross-section;

wherein the air extraction duct includes an area with a defined cross-sectional expansion.

2. The jet engine according to claim 1, wherein the bearing chamber support is a cast component and the air extraction duct is a part of the bearing chamber support.

3. The jet engine according to claim 1, wherein the air extraction duct is a separate conduit that at least in certain areas is arranged in a circumferential area of the bearing chamber support.

4. The jet engine according to claim 1, wherein the flow cross-section of the air extraction duct increases in the area by a factor of at least two.

5. The jet engine according to claim 1, wherein in the area, a wall of the air extraction duct has an angle with respect to a central axis of the air extraction duct that is larger than 15°

.

6. The jet engine according to claim 1, wherein a flow cross-section of the air extraction duct is not enlarged downstream of the area with respect to a flow cross-section in the area.

7. The jet engine according to claim 1, wherein the sealing chamber and the de-aeration chamber are respectively arranged downstream of the bearing chamber.

8. The jet engine according to claim 7, wherein the air extraction duct is connected to the de-aeration chamber upstream of the bearing chamber, and further comprising a further air extraction duct is-connected to the de-aeration chamber downstream of the bearing chamber.

9. The jet engine according to claim 8, wherein the air extraction duct and the further air extraction duct are arranged in different circumferential areas of the jet engine.

10. The jet engine according to claim 8, wherein the air extraction duct and the further air extraction duct are connected to each other upstream of the core flow channel.

11. The jet engine according to claim 1, wherein the bearing chamber support is arranged in at least one chosen from an area of a turbine of the jet engine and an area of a compressor of the jet engine.

12. The jet engine according to claim 1, wherein the flow cross-section of the air extraction duct increases in the area by a factor of at least ten.

13. The jet engine according to claim 1, wherein in the area, a wall of the air extraction duct has an angle with respect to a central axis of the air extraction duct that is larger than 60°

.

14. The jet engine according to claim 1, wherein in the area, a wall of the air extraction duct has an angle with respect to a central axis of the air extraction duct that is larger than 75°

.

15. The jet engine according to claim 1, wherein in the area, a wall of the air extraction duct has an angle with respect to a central axis of the air extraction duct that is 90°

.

16. The jet engine according to claim 1, wherein the sealing chamber and the de-aeration chamber are respectively arranged upstream of the bearing chamber.