Twin-spool aircraft turbomachine comprising a lubricant tank in a compartment between flow streams, and improved means of filling the tank

Patent metadata

Field	Value
Publication number	US-10975741-B2
Application number	US-201916441316-A
Country	US
Kind code	B2
Filing date	Jun 14, 2019
Priority date	Jun 18, 2018
Publication date	Apr 13, 2021
Grant date	Apr 13, 2021

Abstract

An aircraft twin-spool turbomachine comprises an inter flow compartment ( 50 ) housing a fuel tank ( 54 ), the exterior of the inter flow compartment being delimited by a cover ( 52 ) delimiting the interior of a bypass flow ( 14 b ) of the turbomachine, the cover comprising a closable access ( 64 ) to a remote lubricant tank filling orifice ( 74 ). The turbomachine also comprises: an overflow evacuation orifice ( 82 ) located on the tank lower than the lubricant inlet orifice ( 68 ); a lubricant overflow evacuation conduit ( 84 ) routed downwards from the overflow evacuation orifice ( 82 ); a controlled evacuation valve ( 88 ), associated with the overflow evacuation orifice ( 82 ); and a control device ( 90, 94 ) for the evacuation valve ( 88 ), the control device being accessible through the access ( 64 ).

First claim

The invention claimed is:

1. An aircraft twin-spool turbomachine ( 1 ) comprising:
an inter flow compartment ( 50 ) housing a lubricant tank ( 54 ), the exterior of the inter flow compartment being delimited by a cover ( 52 ) delimiting an interior of a bypass flow stream ( 14 b ) of the aircraft twin-spool turbomachine ( 1 ), said cover ( 52 ) comprising a closable access ( 64 ) to a remote lubricant tank filling orifice ( 74 ),
a filling conduit ( 72 ) connecting the remote filling orifice ( 74 ) to a lubricant inlet orifice ( 68 ) provided on a top part ( 54 a ) of the lubricant tank ( 54 );
an overflow evacuation orifice ( 82 ) located on the lubricant tank ( 54 ) lower than the lubricant inlet orifice ( 68 );
lubricant overflow evacuation conduit ( 84 ) routed downwards from the overflow evacuation orifice ( 82 );
a controlled evacuation valve ( 88 ), associated with the overflow evacuation orifice ( 82 ); and
a control device ( 90 , 94 ) for the evacuation valve ( 88 ), the control device being accessible through said closable access ( 64 ).

2. The aircraft twin-spool turbomachine ( 1 ) according to claim 1 , wherein the control device ( 90 , 94 ) comprises a control element ( 90 ) accessible through said closable access ( 64 ).

3. The aircraft twin-spool turbomachine ( 1 ) according to claim 2 , wherein the aircraft twin-spool turbomachine ( 1 ) comprises a controlled filling valve ( 70 ), associated with the lubricant inlet orifice ( 68 ) provided on the upper part ( 54 a ) of the reservoir, and in that the control device ( 90 , 94 ) is configured to also control said controlled filling valve ( 70 ), through the control element ( 90 ).

4. The aircraft twin-spool turbomachine ( 1 ) according to claim 3 , wherein a mechanical coupling link is provided to connect the evacuation valve ( 88 ) and the controlled filling valve ( 70 ), so that actuation of one of these valves ( 70 , 88 ) also causes actuation of the other valve.

5. The aircraft twin-spool turbomachine ( 1 ) according to claim 2 , wherein the control element ( 90 ) is a lever.

6. The aircraft twin-spool turbomachine ( 1 ) according to claim 5 , wherein the lever is articulated close to the remote filling orifice ( 74 ).

7. The aircraft twin-spool turbomachine ( 1 ) according to claim 2 , wherein the aircraft twin-spool turbomachine ( 1 ) comprises lubricant non return means ( 70 ′), associated with the lubricant inlet orifice ( 68 ) provided on the top part ( 54 a ) of the lubricant tank.

8. The aircraft twin-spool turbomachine ( 1 ) according to claim 2 , wherein the control device ( 90 , 94 ) comprises a cable ( 94 ) connecting the control element ( 90 ) to the evacuation valve ( 88 ).

9. The aircraft twin-spool turbomachine ( 1 ) according to claim 1 , wherein a bottom end ( 84 a ) of the lubricant evacuation overflow conduit ( 84 ) is free, or is connected to a drain ( 80 ) connected to a lubricant filling dish ( 76 ) through which said remote filling orifice ( 74 ) is formed.

10. The aircraft twin-spool turbomachine ( 1 ) according to claim 9 , wherein said bottom end ( 84 a ) of the lubricant overflow evacuation conduit ( 84 ) is closed by a removable plug ( 98 ).

11. The aircraft twin-spool turbomachine ( 1 ) according to claim 1 , wherein the lubricant tank ( 54 ) is located upstream from a high pressure body ( 60 b ) of the aircraft twin-spool turbomachine ( 1 ).

12. The aircraft twin-spool turbomachine ( 1 ) according to claim 11 , wherein the lubricant tank ( 54 ) is located around a low pressure compressor ( 5 ) belonging to a low pressure body ( 60 a ) of the turbomachine.

13. The aircraft twin-spool turbomachine ( 1 ) according to claim 12 , wherein said closable access ( 64 ) is located downstream from the low pressure compressor ( 5 ).

14. The aircraft twin-spool turbomachine ( 1 ) according to claim 13 , wherein said closable access ( 64 ) is located around a combustion chamber ( 11 ) of the aircraft twin-spool turbomachine ( 1 ).

15. The aircraft twin-spool turbomachine ( 1 ) according to claim 14 , wherein said closable access ( 64 ) is located around a high pressure compressor ( 7 ) of the turbomachine.

16. The aircraft twin-spool turbomachine ( 1 ) according to claim 13 , wherein said closable access ( 64 ) is located around a high pressure compressor ( 7 ) of the turbomachine.

17. A method of filling the lubricant tank ( 54 ) of the aircraft twin-spool turbomachine ( 1 ) according to claim 1 , the method comprising the following steps in sequence:
open the closable access ( 64 );
add lubricant into the remote filling orifice ( 74 ), with the controlled evacuation valve ( 88 ) arranged in an open position through the control device ( 90 , 94 );
monitor lubricant evacuation through the lubricant overflow evacuation conduit ( 84 );
stop filling lubricant and close the evacuation valve ( 88 ) after detection of lubricant evacuation through the lubricant overflow evacuation conduit ( 84 ); and
close the closable access ( 64 ).

Assignees

• Safran Aircraft Engines

Inventors

• Guillou Pierrot

Classifications

• F05D2260/98

  Lubrication · CPC title

• F01M11/0458 Primary

  Lubricant filling and draining · CPC title

• F01M1/02

  using lubricating pumps (pumps in general F04; lubricating pumps per se F16N) · CPC title

• F01D25/18 Primary

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F02C7/06

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