Spline for a turbine engine
AssigneeGeneral Electric Company
InventorsRobert Charles Groves, II, David Scott Stapleton
Life of this patent
Estimating the term…
Abstract
A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.
Claims17
A shroud assembly for a turbine engine comprising:
- a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces, with a forward edge spanning to an aft edge to define an axial direction;
- a first seal channel provided in at least one of the confronting end faces and having a first axial portion;
- a second seal channel having a second axial portion and a second radial portion, the second seal channel provided in the at least one of the confronting end faces with the second axial portion radially spaced from the first axial portion of the first seal channel such that the first seal channel is radially closer to the first surface and the second seal channel is radially closer to the second surface;
- and
- a gap formed in the first seal channel between the first axial portion and the second radial portion located at a transition between the second axial portion and the second radial portion to provide for passing of fluid through the gap toward the second seal channel.
An engine component for a turbine engine comprising:
- a plurality of circumferentially arranged peripheral walls defining a mainstream flow path and having confronting end faces defining first and second radially spaced surfaces, with a forward edge spanning to an aft edge to define an axial direction;
- a first seal channel provided in at least one of the confronting end faces and having a first axial portion;
- a second seal channel having a second axial portion and a second radial portion, the second seal channel provided in the at least one of the confronting end faces with the second axial portion radially spaced from the first axial portion of the first seal channel such that the first seal channel is radially closer to the first surface and the second seal channel is radially closer to the second surface;
- and
- a gap formed in the first seal channel between the first axial portion and the second radial portion located at the transition between the second axial portion and the second radial portion to provide for a passing of fluid through the first seal channel to the second seal channel.
A method of cooling a shroud segment having confronting end faces and a first set of seal channels having a first axial portion and second set of seal channels having a second axial portion and a second radial portion, each set of seal channels provided in each of the confronting end faces where a gap is formed in the first seal channel between the first axial portion and the second radial portion at a transition between the second axial portion and the second radial portion;
- the method comprising passing fluid through the first seal channel to the second seal channel.
Dependencies are inferred from the claim text.