Turbomachine with double flow and its lubricant reservoir

Patent metadata

Field	Value
Publication number	US-11035294-B2
Application number	US-201816156770-A
Country	US
Kind code	B2
Filing date	Oct 10, 2018
Priority date	Oct 12, 2017
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

Abstract

Bypass turbine engine, comprising a gas generator surrounded by a nacelle and connected to the latter by tubular arms, a primary flow duct within the gas generator being externally delimited by a first annular casing of the gas generator, and a bypass flow duct of a secondary flow around the gas generator being internally delimited by a second annular casing of the gas generator and externally by a third annular casing of the nacelle, the second and third casings being connected together by at least some of the tubular arms, characterized in that it comprises at least one lubricant tank located in the annular space that extends between the first and second casings, and lubricant supply means of the tank or of each tank that comprise at least one supply line extending from the or each tank to at least one filler opening located at the level of the third casing, passing within at least one of said arms connecting the second and third casings.

First claim

The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:

1. A bypass turbine engine comprising:
a gas generator surrounded by a nacelle and connected to the nacelle by a plurality of tubular arms,
a primary flow duct within the gas generator being externally delimited by a first annular casing of the gas generator,
a bypass flow duct of a secondary flow around the gas generator being internally delimited by a second annular casing of the gas generator and externally by a third annular casing of the nacelle,
the second and third casings being connected together by at least some of the plurality of tubular arms,
at least one lubricant tank located in an annular space extending between the first and second casings, and
lubricant supply means of the at least one lubricant tank that comprise at least one supply line extending from the at least one lubricant tank to at least one filler opening located in a vicinity of the third casing, passing within at least one of the at least some of the plurality of tubular arms connecting the gas generator and the nacelle, wherein
the supply means comprises means to visualize a lubricant level in the at least one lubricant tank and a vent pipe of the at least one lubricant tank, extending from the at least one lubricant tank up to a vicinity of the filler opening, passing inside the at least one of the at least some of the plurality of tubular arms connecting the second and third casings.

2. The turbine engine of claim 1 wherein the tank has a generally curved shape and extends partially about a longitudinal axis of the turbine engine.

3. The turbine engine of claim 1 wherein the at least one tank is located substantially perpendicular to a low pressure compressor of the gas generator.

4. The turbine engine of claim 1 wherein the nacelle comprises an outer annular cowling comprising at least one hatch providing access to the at least one filler opening.

5. The turbine engine of claim 1 wherein the supply means are configured so that lubricant that is poured in the at least one filler opening flows by gravity only to the at least one lubricant tank.

6. The turbine engine of claim 1 wherein the visualization means comprise at least one float.

7. The turbine engine of claim 1 wherein the at least one supply line comprises a first substantially straight section that extends substantially radially, with respect to a longitudinal axis of the turbine engine, inside the at least one of the at least some of the plurality of tubular arms, and a second substantially straight section that extends substantially parallel to the longitudinal axis, in the downstream direction, inside said space.

8. The turbine engine of claim 1 wherein said at least one filler opening is located upstream from a cascade thrust reverser of the turbine engine.

9. The turbine engine of claim 1 wherein said at least one filler opening is located in a filling chamber of which at least some of walls are secured to an outer annular cowling of the nacelle.

Assignees

• Safran Aircraft Engines

Inventors

• Eichstadt Frédéric Paul
• Aussedat Nicolas Maurice Hervé
• Waissi Bellal

Classifications

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F05D2260/80

  Diagnostics · CPC title

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F01M11/12

  concerning lubricant level · CPC title