US 12,188,359 B2
Blade outer air seal with retainer ring
Daniel S. Rogers, Lyman, ME (US); James E. Weisheit, Kennebunk, ME (US); Morely S. Sherman, Portsmouth, NH (US); Mikayla M. Rogers, Portland, ME (US); Timothy J. Harding, Wethersfield, CT (US); Marshall F. Thayer, Waterboro, ME (US); and Joseph Micucci, Scarborough, ME (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Sep. 29, 2023, as Appl. No. 18/477,912.
Claims priority of provisional application 63/411,903, filed on Sep. 30, 2022.
Prior Publication US 2024/0110487 A1, Apr. 4, 2024
Int. Cl. F01D 11/08 (2006.01); F01D 9/04 (2006.01); F01D 25/24 (2006.01)
CPC F01D 11/08 (2013.01) [F01D 9/04 (2013.01); F01D 25/246 (2013.01); F05D 2300/6033 (2013.01)] 12 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a turbine section including,
a static structure including a retainer ring;
a first vane disposed about an engine axis, the first vane having a first vane platform bearing against the retainer ring, the retainer ring preventing movement of the first vane in a first axial direction, a second vane axially spaced from the first vane, the second vane having a second vane platform, and a blade axially between the first vane and the second vane;
a row of blade outer air seals situated radially outwardly of the blade, each of the blade outer air seals including a ceramic matrix composite body defining a core gaspath side facing the blade, a forward end, an aft end, and circumferential sides; and
a spring seal at the aft end of at least one of the blade outer air seals and sealing against the second vane platform of the second vane, the spring seal providing a preload biasing the at least one of the blade outer air seals against the first vane platform and thereby biasing the first vane against the retainer ring.