US 12,241,380 B2
Bolted joint of gas turbine engine
Paul M. Lutjen, Kennebunkport, ME (US); and Dairus D. McDowell, Springvale, ME (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Mar. 9, 2023, as Appl. No. 18/181,149.
Prior Publication US 2024/0301805 A1, Sep. 12, 2024
Int. Cl. F01D 25/24 (2006.01); F01D 9/02 (2006.01)
CPC F01D 25/243 (2013.01) [F01D 9/023 (2013.01); F05D 2240/40 (2013.01); F05D 2260/36 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A component of a gas turbine engine, comprising:
a continuous hoop portion extending at least partially around an engine central longitudinal axis of the gas turbine engine; and
a bolting feature extending from the hoop portion, the bolting feature configured for securing the component to an adjacent part, the bolting feature including:
a circumferential arm extending radially and circumferentially from the hoop portion, the circumferential arm defining a radial gap between the circumferential arm and the hoop portion, the circumferential arm including a bolt opening for installation of a bolt through the circumferential arm and into the adjacent part;
a connecting leg extending radially from the hoop portion across the radial gap toward the circumferential arm; and
an arm interlocking feature disposed at the circumferential arm configured to radially interlock directly with a complementary leg interlocking feature of the connecting leg, the arm interlocking feature and the leg interlocking feature having a radial interconnect gap therebetween in a free state;
wherein the leg interlocking feature is a dovetail-shaped tab installed into the arm interlocking feature defined as a complimentary dovetail-shaped slot.