公开(公告)号：US11281821B2

公开(公告)日：2022-03-22

申请号：US16026586

申请日：2018-07-03

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  Kurt R. Heinemann

IPC: G06F30/20 ,  G06F111/10 ,  G06N20/00

Abstract: An exemplary method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set of substantially identical gas turbine engine components, determining a variance model of the first set of substantially identical gas turbine engine components, and determining a plurality of predicted response models based at least in part on the variance model, each of the predicted response models corresponding to one of an engine type and an engine assembly, and each of the predicted response models being configured to determine a predicted response of including a gas turbine engine component from the first set of substantially identical gas turbine engine components in the corresponding one of the engine type and the engine assembly. The system then identifies as-manufactured parameters of a second engine component, and applies the as-manufactured parameters of the second engine component to each of the predicted response models, thereby generating a predicted response output from each of the predicted response models. An optimum predicted response from each of the generated predicted response models is identified and the engine type or engine assembly that corresponds with the optimum predicted response is associated with a unique part identifier of the second engine component.

公开(公告)号：US20200012750A1

公开(公告)日：2020-01-09

申请号：US16026586

申请日：2018-07-03

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  Kurt R. Heinemann

IPC: G06F17/50

Abstract: An exemplary method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set of substantially identical gas turbine engine components, determining a variance model of the first set of substantially identical gas turbine engine components, and determining a plurality of predicted response models based at least in part on the variance model, each of the predicted response models corresponding to one of an engine type and an engine assembly, and each of the predicted response models being configured to determine a predicted response of including a gas turbine engine component from the first set of substantially identical gas turbine engine components in the corresponding one of the engine type and the engine assembly.The system then identifies as-manufactured parameters of a second engine component, and applies the as-manufactured parameters of the second engine component to each of the predicted response models, thereby generating a predicted response output from each of the predicted response models. An optimum predicted response from each of the generated predicted response models is identified and the engine type or engine assembly that corresponds with the optimum predicted response is associated with a unique part identifier of the second engine component.

公开(公告)号：US20200012749A1

公开(公告)日：2020-01-09

申请号：US16026547

申请日：2018-07-03

Applicant: United Technologies Corporation

Inventor： Daniel A. Snyder ,  David J. Yudichak ,  Kurt R. Heinemann ,  Perry Bowes ,  Evan Selin

IPC: G06F17/50

Abstract: A qualification system for gas turbine engine components includes a computer system configured to receive a set of measured parameters for each gas turbine engine component in a plurality of substantially identical gas turbine engine components, and determine a variation model based on the set of measured parameters. The computer system includes at least one simulated engine model configured to determine a predicted operation of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, a correlation system configured to correlate variations in the set of parameters for each of the gas turbine engine components with a set of the predicted operations of each gas turbine engine, thereby generating a predictive model based on the variations. The computer system also includes a qualification module configured to generate a qualification formula based on the predictive model. The qualification formula is configured to receive a set of measured parameters of an as-manufactured gas turbine engine component and determine when the as manufactured gas turbine engine component is qualified for inclusion in at least one engine.

公开(公告)号：US10339225B1

公开(公告)日：2019-07-02

申请号：US14599946

申请日：2015-01-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William A. Sowa ,  Charles Gregory Jensen ,  Kurt R. Heinemann ,  Andrew D. Milliken ,  Diane K. Emmerson ,  Joshua Daniel Winn ,  Christopher Farnum ,  Robert Ivan Yorgason

IPC: G06F17/50 ,  H04L29/08

Abstract: A computerized method and system for computer-aided design access control is disclosed. The method includes receiving a part definition for a part at a server, the part definition comprising a plurality of components and a level of access required for each component of the plurality of components, receiving a request from a user to manipulate the part, the user being associated with a user access level, verifying the user access level against each level of access required for each component of the plurality of components, and presenting a render of the part to the user based on the part definition, the render comprising each component of the plurality of components where the user access level meets the associated level of access required and a placeholder for each component of the plurality of components where the user access level does not meet the associated level of access required.

公开(公告)号：US20180211336A1

公开(公告)日：2018-07-26

申请号：US15412293

申请日：2017-01-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Kurt R. Heinemann ,  Glenn Levasseur

IPC: G06Q50/04 ,  G06Q10/06 ,  G06Q10/08

CPC classification number: G06Q50/04 ,  G01M5/0016 ,  G01M15/14 ,  G05B23/0283 ,  G06Q10/06315 ,  G06Q10/0875 ,  Y02P90/30

Abstract: A method of determining a use for substantially the same gas turbine engine components and comprises the steps of receiving manufacturing information about a plurality of gas turbine engine components; classifying each of the plurality of gas turbine engine components into at least two categories, with a first category being components closer to a specification than a second category; and recommending a suggested future use for the first category on aircraft that will operate in more challenging flight conditions and for the second category on aircraft that will operate in less challenging flight conditions. A system is also disclosed.