公开(公告)号：US20230315946A1

公开(公告)日：2023-10-05

申请号：US18194937

申请日：2023-04-03

Applicant: Raytheon Technologies Corporation

Inventor： Sergei F. Burlatsky ,  David U. Furrer ,  Vasisht Venkatesh ,  Ryan B. Noraas ,  Stephen J. Barker

IPC: G06F30/20

CPC classification number: G06F30/20 ,  G06F2111/08

Abstract: The present disclosure provides advantageous probabilistic models and applications for component (e.g., titanium component) design optimization, and related methods of use. More particularly, the present disclosure provides advantageous probabilistic models, systems and applications for component design optimization and related methods of use, and where the probabilistic models, systems and applications can accurately predict the life/failure of components (e.g., titanium components) based on material microstructure statistics and/or product mission specifics and/or variations. Disclosed are probabilistic systems and methods for predicting dwell fatigue behavior of a component (e.g., titanium component). The present disclosure advantageously provides an analytical modeling framework that captures the various physics-based mechanisms for dwell fatigue damage accumulation, crack nucleation, crack propagation and fracture in components or materials (e.g., anisotropic components/materials). The probabilistic modeling framework thereby enables the prediction of dwell fatigue behavior as a function of microstructure (e.g., material microstructure statistics) and/or loading conditions (e.g., product mission specifics).

公开(公告)号：US11725516B2

公开(公告)日：2023-08-15

申请号：US16657436

申请日：2019-10-18

Applicant: Raytheon Technologies Corporation

Inventor： Sara Ann Beck ,  David Ulrich Furrer ,  Vasisht Venkatesh

IPC: F01D5/00 ,  B23P6/00 ,  C22F1/18

CPC classification number: F01D5/005 ,  B23P6/002 ,  C22F1/183 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2300/174 ,  Y10T29/49318 ,  Y10T29/49723

Abstract: A method of servicing a gas turbine engine is disclosed. According to the method, a component including a titanium alloy is removed from the gas turbine engine after operating the gas turbine engine with the component in service. The removed component is subjected to heat treatment, and the heat-treated component is re-installed into the gas turbine engine or installed into a different gas turbine engine.