US 11,933,195 B2
Gas turbine engine with pre-conditioned ceramic matrix composite components
Michael J. Whittle, London (GB); Louise J. Gale, London (GB); Stephan J. Pattison, London (GB); Anthony G. Razzell, London (GB); Ian M. Edmonds, London (GB); and Michael G. Abbott, Cypress, CA (US)
Assigned to Rolls-Royce plc; and Rolls-Royce High Temperature Composites Inc., Cypress, CA (US)
Filed by Rolls-Royce plc, London (GB); and Rolls-Royce High Temperature Composites Inc., Cypress, CA (US)
Filed on Feb. 3, 2022, as Appl. No. 17/592,226.
Application 17/592,226 is a division of application No. 16/774,793, filed on Jan. 28, 2020, granted, now 11,255,200.
Prior Publication US 2022/0154582 A1, May 19, 2022
Int. Cl. F01D 5/28 (2006.01); C04B 35/64 (2006.01); F01D 5/14 (2006.01); F01D 9/04 (2006.01)
CPC F01D 5/284 (2013.01) [F01D 5/141 (2013.01); F01D 5/282 (2013.01); F01D 9/041 (2013.01); C04B 35/64 (2013.01); F01D 5/288 (2013.01); F05D 2240/12 (2013.01); F05D 2260/941 (2013.01); F05D 2300/6033 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A component adapted for use in a gas turbine engine, the component comprising
a body comprising ceramic matrix composite material having a peak-stress region and an off-peak stress region, and
a strain concentration feature located at the off-peak stress region and configured to cause stresses to form in the off-peak stress region instead of at the peak-stress region to reduce stress at the peak-stress region.