Device for sealing between a rotor and a stator of a turbine engine
AssigneeSafran Aircraft Engines
InventorsBaptiste Marie Aubin Pierre Jouy, Josselin Luc Florent Sicard, Mathieu Charles Jean Verdiere, Loïc Fabien François Villard
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Abstract
A sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.
Claims16
A sealing device arranged to cooperate with a rotor part and a stator part, both of an aircraft gas turbomachine in which a gas stream is to circulate from upstream to downstream, the rotor part being adapted to rotate relative to the stator part about an axis, the sealing device comprising:
- two labyrinth seal lips, respectively an upstream one and a downstream one, both being elements of the rotor part;
- and,
- at least one block made of an abradable material:
- attached to the stator part, and
- adapted to cooperate with said two labyrinth seal lips, each projecting radially to said axis over an end portion of the rotor part,
- the at least one block has, radially to said axis, a first upstream free axial sealing surface and a downstream free axial sealing surface, and
- said two labyrinth seal lips have, radially to said axis, respective free ends, the free end of the downstream labyrinth seal lip and the downstream free axial sealing surface being located at positions radial to said axis which are each further from the axis than the free end of the upstream labyrinth seal lip and the first upstream free axial sealing surface,
- wherein, upstream of said two labyrinth seal lips, the sealing device comprises a circumferential wall which extends radially to said axis upstream and adjacent to the first upstream free axial sealing surface of said at least one block, by penetrating radially to said axis into the gas stream, and wherein:
- the sealing device further has a second upstream free axial sealing surface which is adjacent to said circumferential wall, upstream of the circumferential wall, and,
- the circumferential wall projects radially with respect to the first upstream free axial sealing surface and second upstream free axial sealing surface of the sealing device, and
- wherein said first upstream free axial sealing surface and downstream free axial sealing surface have a radial connection wall between them, and:
- 1≤D1/D2≤1.5, or
- 1≤L2/L1≤4, or
- 1≤L3/L1≤3, wherein:
- D1 is a radial distance between the first upstream free axial sealing surface of said at least one block and the free end of the circumferential wall,
- D2 is a radial distance between the free end of the circumferential wall and a radially outer face of an upstream facing spoiler,
- L1 is an axial thickness of the upstream labyrinth seal lip, at the free end,
- L2 is an axial distance between a downstream face of the circumferential wall and an upstream face, at the free end, of the upstream labyrinth seal lip, and
- L3 is an axial distance between a downstream face, at the free end, of the upstream labyrinth seal lip and the radial connecting wall.
A sealing device arranged to cooperate with a rotor part and a stator part, both of an aircraft gas turbomachine in which a gas stream is to circulate from upstream to downstream, the rotor part being adapted to rotate relative to the stator part about an axis, the sealing device comprising:
- two labyrinth seal lips, respectively an upstream one and a downstream one, both being elements of the rotor parts, and,
- at least one block made of an abradable material:
- attached to the stator part, and
- adapted to cooperate with said two labyrinth seal lips, each projecting radially to said axis over an end portion of the rotor part,
- the at least one block has, radially to said axis, an upstream free axial sealing surface and a downstream free axial sealing surface, and
- said two labyrinth seal lips have, radially to said axis, respective free ends, the free end of the downstream labyrinth seal lip and the downstream free axial sealing surface being located at positions radial to said axis which are each further from the axis than the free end of the upstream labyrinth seal lip and the upstream free axial sealing surface,
- wherein, upstream of said two labyrinth seal lips, the sealing device comprises a circumferential wall which extends radially to said axis beyond the upstream free axial sealing surface of said at least one block, by penetrating radially to said axis into the gas stream, and wherein:
- the end portion of the rotor part over which said two labyrinth seal lips radially project comprises a platform provided at an upstream end with an upstream facing spoiler, and
- radially to the axis, the circumferential wall extends opposite, but at a distance from, the upstream facing spoiler,
- wherein the circumferential wall projects radially with respect to the upstream free axial sealing surface of the sealing device, which the upstream free axial sealing surface is adjacent to the circumferential wall, axially, upstream of the circumferential wall;
- wherein said upstream free axial sealing surface and downstream free axial sealing surface have a radial connection wall between them, and:
- 1≤D1/D2≤1.5,
- 1≤L2/L1≤4,
- 1≤L3/L1≤3, wherein
- D1 is a radial distance between the upstream free axial sealing surface of said at least one block and the free end of the circumferential wall,
- D2 is a radial distance between the free end of the circumferential wall and a radially outer face of the upstream facing spoiler,
- L1 is an axial thickness of the upstream labyrinth seal lip 40a, at the free end,
- L2 is an axial distance between a downstream face of the circumferential wall and an upstream face, at the free end, of the upstream labyrinth seal lip, and
- L3 is an axial distance between a downstream face, at the free end, of the upstream labyrinth seal lip and the radial connecting wall.
Dependencies are inferred from the claim text.