Intermediate case for an aircraft turbomachine made from a single casting with a lubricant duct

Patent metadata

Field	Value
Publication number	US-11143045-B2
Application number	US-201715653976-A
Country	US
Kind code	B2
Filing date	Jul 19, 2017
Priority date	Jul 20, 2016
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

Abstract

The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet guide vanes (24) performing a heat exchanger function and comprising a lubricant passage (50a, 50b) designed to be cooled by the fan flow (58) following an outer surface of the outlet guide vane. According to the invention, the case also comprises at least one lubricant duct (55) passing along a circumferential direction of the hub (26) and at least part of which is made from a single casting with the hub, the lubricant duct (55) having at least one lateral opening communicating with the lubricant passage (50a, 50b) of at least one of the vanes (24).

First claim

The invention claimed is:

1. An intermediate case for a twin spool turbomachine for an aircraft, comprising a hub, an outer shell and outlet guide vanes removably mounted at their ends on the hub and on the outer shell, and each of at least some of said outlet guide vanes performing a heat exchanger function and comprising a lubricant passage designed to be cooled by a fan flow following an outer surface of the outlet guide vane,
wherein the intermediate case also comprises at least one lubricant duct passing along a circumferential direction of the hub and at least part of which is made from a single casting with said hub,
wherein each outlet guide vane comprises holes through which attachment elements pass to fix said outlet guide vane to the hub,
wherein said lubricant duct has at least three lateral openings spaced relative to one another along the circumferential direction, and respectively communicating with said lubricant passage of at least three of the outlet guide vanes, and
wherein each lubricant duct extends in an annular configuration around an angular sector of approximately 360°.

2. The intermediate case according to claim 1 , wherein the entire lubricant duct is made of a single casting with said hub.

3. The intermediate case according to claim 1 , wherein only part of the lubricant duct is made in a single casting with said hub, said part of the lubricant duct being closed by an end plate to complete said lubricant duct.

4. The intermediate case according to claim 3 , wherein said integrated part is open radially outwards, and/or that the end plate integrates said at least one lateral opening.

5. The intermediate case according to claim 1 , wherein a first end piece is provided at one of the outlet guide vanes and a second end piece is provided at the lubricant duct and defines the lateral opening, the first end piece being inserted in the second end piece, or vice versa, and wherein at least one seal is provided for each lateral opening in the lubricant duct, loaded in the radial direction from a central axis of this opening, between the first end piece and the second end piece.

6. The intermediate case according to claim 1 , wherein at least one seal is provided for each lateral opening in the lubricant duct, loaded along the axial direction of a central axis of this opening, between a first end piece of one of the outlet guide vanes and a second end piece of the lubricant duct defining said opening, said first and second end pieces being forced into contact with each other along the direction of the central axis.

7. The intermediate case according to claim 1 , wherein said holes of each outlet guide vane includes first holes and second holes, and wherein the root of each outlet guide vane is provided with the first holes on the upstream side for attachment to the hub formed closer to a leading edge than to a trailing edge, and the second holes on the downstream side for attachment to the hub formed closer to the trailing edge than to the leading edge.

8. The intermediate case according to claim 5 , wherein said holes of each outlet guide vane includes first holes and second holes, and wherein the root of each outlet guide vane is provided with the first holes on the upstream side for attachment to the hub formed close to a leading edge, and the second holes on the downstream side for attachment to the hub formed close to a trailing edge, and in that the first end piece of the outlet guide vane is formed between the upstream and downstream vane attachment holes.

9. A twin spool turbomachine for an aircraft, comprising the intermediate case according to claim 1 , located downstream from a fan of this turbomachine.

Assignees

• Safran Aircraft Engines

Inventors

• Zaccardi Cédric
• Jacquemard Christophe Paul
• Papin Thierry Georges Paul
• Perdrigeon Christophe Marcel Lucien

Classifications

• F02K3/06 Primary

  with front fan · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2260/98

  Lubrication · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title

• F28D2021/0089

  Oil coolers · CPC title