De-Icing Splitter Lip for Axial Turbomachine Compressor

Patent metadata

Field	Value
Publication number	US-2016305322-A1
Application number	US-201615131206-A
Country	US
Kind code	A1
Filing date	Apr 18, 2016
Priority date	Apr 20, 2015
Publication date	Oct 20, 2016
Grant date	—

Abstract

The present application relates to a de-icing splitter lip for a low-pressure compressor of a turbofan aircraft engine. The splitter lip surrounds the primary flow and includes an annular splitter wall with a circular leading edge, an outer shroud connected to the splitter wall, and a heating device in an electric ribbon that de-ices the splitter lip. The splitter lip further includes an elastic element made of elastomer, holding the heating device on the inside of the splitter wall. The elastic element is compressed, pre-loaded, in the splitter lip. Thus, the elastic element exerts a force F clamping the heating device against the splitter wall and the outer shroud in order to improve thermal contact. The present application also provides a method for assembling a splitter lip.

First claim

We claim:

1 . A splitter lip for a turbomachine, the splitter lip comprising:
an annular splitter wall with a circular leading edge; a heating device configured in order to de-ice the splitter lip; and at least one elastic element holding the heating device on the inside of the splitter wall; wherein the at least one elastic element is pre-stressed in the splitter lip so as to exert a clamping force F on the heating device towards the splitter wall.

2 . The splitter lip of claim 1 , wherein the at least one elastic element and the heating device is arranged along the leading edge so as to clamp the heating device along the leading edge.

3 . The splitter lip of claim 1 , wherein the at least one elastic element is compressed axially or radially or any combination thereof.

4 . The splitter lip of claim 1 , wherein the at least one elastic element has an arcuate shape along the leading edge.

5 . The splitter lip of claim 1 , further comprising:
an annular row of stator vanes inside the splitter wall.

6 . The splitter lip of claim 1 , further comprising:
an outer shroud surrounded by the splitter wall.

7 . The splitter lip of claim 6 , wherein the heating device is in contact with the outer shroud.

8 . The splitter lip of claim 6 , wherein the at least one elastic element is compressed radially between the splitter wall and the outer shroud so as to clamp the heating device radially against the outer shroud.

9 . The splitter lip of claim 6 , wherein the outer shroud and the splitter wall form an annular channel that extends axially in the downstream direction, and wherein the heating device is placed at the upstream end of the channel.

10 . The splitter lip of claim 6 , wherein the outer shroud comprises:
a composite material having an organic matrix.

11 . The splitter lip of claim 1 , wherein the heating device comprises:
a heating ribbon that fits against the splitter wall.

12 . The splitter lip of claim 1 , wherein the at least one elastic element comprises:
an elastomer material and forms a block of elastic material.

13 . The splitter lip of claim 1 , further comprising:
an annular cavity generally filled by the at least one elastic element and by the heating device.

14 . The splitter lip of claim 1 , wherein the splitter wall comprises:
an annular attachment flange, the at least one elastic element pressing axially against the annular flange.

15 . The splitter lip of claim 1 , further comprising:
thrust elements exerting a compressive force on the at least one elastic element so as to pre-load it.

16 . The splitter lip of claim 1 , further comprising:
reversible locking means which hold the heating device in place.

17 . A turbomachine, comprising:
a de-icing splitter lip comprising:
an annular splitter wall with a circular leading edge;
a heating device configured so as to be able to de-ice the splitter lip;
at least one elastic element holding the heating device on the inside of the splitter wall;
wherein the at least one elastic element is compressed by at least 1% of the axial length thereof in the splitter lip so as to exert a clamping force F on the heating device towards the splitter wall.

18 . A method for assembling a de-icing splitter lip for a turbomachine, comprising:
providing an annular splitter wall with a circular leading edge; providing a heating device configured in order to de-ice the splitter lip; providing at least one elastic element holding the heating device on the inside of the splitter wall; compressing the at least one elastic element during assembly, such that the at least one elastic element is pre-loaded in order to exert a force F clamping the heating device against the splitter wall.

19 . The method according of claim 18 , wherein during assembly, the heating device is placed in the splitter lip before the at least one elastic element.

20 . The method according of claim 18 , wherein during assembly, the at least one elastic element is introduced into the splitter lip then compressed and remains compressed in the assembled state of the splitter lip.

Assignees

• Techspace Aero Sa

Inventors

• Bouillon David
• Herbaut Ghislain

Classifications

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• F05D2260/38

  by a spring, i.e. spring loaded or biased towards a certain position · CPC title

• F05D2260/221

  Improvement of heat transfer · CPC title

• F01D25/02 Primary

  De-icing means for engines having icing phenomena · CPC title

• F05D2230/60

  Assembly methods · CPC title