Labyrinth seal for a turbine engine of an aircraft

Patent metadata

Field	Value
Publication number	US-10947857-B2
Application number	US-201816140439-A
Country	US
Kind code	B2
Filing date	Sep 24, 2018
Priority date	Sep 26, 2017
Publication date	Mar 16, 2021
Grant date	Mar 16, 2021

Abstract

Labyrinth seal for a turbine engine, in particular of an aircraft, including a rotor element rotating about an axis of rotation, and a stator element extending around the rotor element The rotor element includes a series of annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element. Each lip includes an inner peripheral body portion, an outer peripheral body portion and an upstream annular face for impact of an air flow during operation. At least one lip has, looking from the upstream annular face, a first annular cavity with a concave rounded cross-section on its inner peripheral body portion and a second annular cavity with a concave rounded cross-section on its outer peripheral body portion.

First claim

The invention claimed is:

1. A labyrinth seal for a turbine engine, comprising a rotor element rotating about an axis of rotation, and a stator element extending around the rotor element, the rotor element comprising a series of annular lips extending radially outwards and surrounded by at least one abradable element carried by the stator element, each said annular lip comprising an inner peripheral body portion, an outer peripheral body portion and an upstream annular face for impact of an air flow during operation, at least one lip of said series of annular lips having, looking from said upstream annular face, a first annular cavity with a concave rounded cross-section on its inner peripheral body portion and a second annular cavity with a concave rounded cross-section on its outer peripheral body portion, wherein the radius of curvature of the first cavity is between 0.5 mm and 2 mm, and the radius of curvature of the second cavity is between 0.8 mm and 2.5 mm.

2. The seal according to claim 1 , wherein each one of said first and second cavities is shaped to direct the air flow of air upstream and radially outwards.

3. The seal according to claim 1 , wherein said at least one lip having its inner peripheral body portion which has symmetry in relation to a median plane substantially perpendicular to said axis of rotation, wherein said second cavity extends from said upstream annular face in the downstream direction, and passes through said median plane.

4. The seal according to claim 1 , wherein at least two lips of said series of annular lips are separated from one another by an annular space a maximum radial dimension E1 of which is greater than the maximum radial dimensions E2, E3 respectively of said first and second cavities.

5. The seal according to claim 4 , wherein the ratio E2/E1 is between 20 and 80%.

6. The seal according to claim 4 , wherein the ratio E3/E1 is between 20 and 80%.

7. The seal according to claim 1 , wherein the outer peripheral body portion is tapered towards a top of the at least one lip.

8. The seal according to claim 1 , wherein the second cavity opens onto a top of the at least one lip.

9. The seal according to claim 1 , wherein the radius of curvature of the first cavity is between 0.5 mm and 2 mm, and the radius of curvature of the second cavity is between 0.8 mm and 2.5 mm.

10. The seal according to claim 1 , wherein the at least one lip comprises at least one additional annular cavity with a concave rounded cross-section on its upstream annular face.

11. A turbine engine, which comprises a least one seal according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Jarossay Clement
• Verron Guilhem Camille Francois
• Judet Maurice Guy
• Laroche Clement Raphael
• Giliberti Guillaume Michel Maurice

Classifications

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F05D2250/293

  lathed, e.g. rotation symmetrical · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title