Raytheon Technologies Corporation

United Technologies Corporation

Rtx Corporation

Kurt R Heinemann

Frederick M Schwarz

Mark David Ring

Xuedong Zhou

Christopher B Jelks

Sumin Tao

Glenn Levasseur

Kate Hudon

Daniel A Snyder

Konstantinos Panagiotis Giannakopoulos

John Joseph Papalia

Evan Selin

Jose R Paulino

Joshua Daniel Winn

William Arthur Sowa

Nagendra Somanath

Charles H Warner

Mark John Rogers

Lisa I Brilliant

Charles Gregory Jensen

Scot Adams Webb

Andrew D Milliken

Steven D Jenkel

Perry Bowes

Robert Ivan Yorgason

Paul S Bean

Michael D Werkheiser

Steven R Chabot

Chester D Blackman, Jr

Christopher Farnum

Diane K Emmerson

Konstantinos Panagiotis Giannakopolous

David J Yudichak

Mark Rogers

A repair 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 wherein each of the gas turbine engine components is an as-run component and has been exposed to a substantially identical general wear pattern. The computer system includes at least one simulated engine model. The simulated engine model is 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 is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A repair module is configured to generate a repair formula based on the predictive model. The repair formula is configured to receive a set of measured parameters of an as-run gas turbine engine component and determine a suggested repair capable of repairing the as-run gas turbine engine component.

Aircraft component repair system and process

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.

Aircraft component qualification system and process

A maintenance scheduling 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. Each of the gas turbine engine components is a single route component and has been utilized in a substantially identical single route. The computer system includes at least one simulated engine model. The simulated engine model is 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 is configured to correlate variations in the set of parameters for each of the gas turbine engine components in the plurality of substantially identical gas turbine engine components with a set of the predicted operations of each gas turbine engine component in the plurality of substantially identical gas turbine engine components, thereby generating a predictive model based on the variations. A maintenance schedule module is configured determine a predictive model operable to determine a predicted wear pattern of a second single route component that is substantially identical to the gas turbine engine components.

Aircraft component repair scheduling system and process

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.

Aircraft component qualification system and process for target based inventory qualification

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.47-4.77 inch (113.5-121.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297&#xb1;10% Hz, a second mode with a frequency of 1035&#xb1;10% Hz, a third mode with a frequency of 1488&#xb1;10% Hz, a fourth mode with a frequency of 1524&#xb1;10% Hz, a fifth mode with a frequency of 2855&#xb1;10% Hz and a sixth mode with a frequency of 4462&#xb1;10% Hz.

Gas turbine engine airfoil frequency design

A 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, and determining a variance model of the first set. The variance model includes a representative parameter profile, which includes a plurality of component parameter profiles. The sum of each of the component parameter profiles is the representative parameter profile. The method also includes determining at least one predicted response models based at least in part on the variance model, identifying as-manufactured parameters of a second engine component, applying the as-manufactured parameters of the second engine component to the at least one predicted response models, thereby generating a predicted response output, and qualifying the second engine component for usage in at least one gas turbine engine corresponding to the at least one predicted response model.

Aircraft component qualification system and process including variation modeling

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.68-3.98 inch (93.5-101.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 1.75-2.05 inch (44.5-52.1 mm). The airfoil element includes at least two of a first mode with a frequency of 436&#xb1;10% Hz, a second mode with a frequency of 1557&#xb1;10% Hz, a third mode with a frequency of 1424&#xb1;10% Hz, a fourth mode with a frequency of 1870&#xb1;10% Hz, a fifth mode with a frequency of 3321&#xb1;10% Hz and a sixth mode with a frequency of 3957&#xb1;10% Hz.

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.99-3.29 inch (75.9-83.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430&#xb1;10% Hz, a second mode with a frequency of 1459&#xb1;10% Hz, a third mode with a frequency of 2036&#xb1;10% Hz, a fourth mode with a frequency of 3615&#xb1;10% Hz, a fifth mode with a frequency of 4722&#xb1;10% Hz and a sixth mode with a frequency of 5591&#xb1;10% Hz.

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.85-3.15 inch (72.4-80.0 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506&#xb1;10% Hz, a second mode with a frequency of 1732&#xb1;10% Hz, a third mode with a frequency of 2268&#xb1;10% Hz, a fourth mode with a frequency of 4007&#xb1;10% Hz, a fifth mode with a frequency of 4851&#xb1;10% Hz and a sixth mode with a frequency of 6416&#xb1;10% Hz.

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.

Secure access frustrom culling for multi user CAx

A system for collaborating on a component according to an exemplary aspect of the present disclosure includes, among other things, a computing device configured to execute a first multi-user CAx environment including a synchronization module. The synchronization module is configured to selectively cause a display module at a first multi-user CAx environment to display data corresponding to changes to at least one subcomponent feature relating to an assembly model caused by a second multi-user CAx environment during an assembly session when at least one predetermined criterion is met. A method for collaborating on a component design is also disclosed.

Multi-user CAx assembly updater

An apparatus includes a substrate having one or more fastener apertures that extend therethrough. Each fastener aperture has a centerline and includes first and second circular segmented regions and a central channeled region. Each circular segmented region has a diameter and a segment length that extends along the centerline, wherein the segment length is greater than one-half the diameter. The central channeled region extends along the centerline between the first and the second circular segmented regions. The central channeled region has a height that is less than the diameter of the first and the second circular segmented regions.

Fastener aperture having an elongated geometry

Gas turbine engine seals and engines incorporating such seals are provided. In this regard, a representative seal includes: an annular seal body having an inner diameter and an outer diameter, the seal body extending along an axis of symmetry between a first end and a second end; the seal body being formed of a strip of material having first and second opposing edges, the strip of material being deformed to exhibit a first sealing surface at the first end, a second sealing surface at the second end, and a third sealing surface along the inner diameter, the first edge being located adjacent to the third sealing surface, the second edge being located adjacent to the second sealing surface; the first edge being spaced from the second edge to define an annular opening, the annular opening providing access to an annular cavity of the seal body.

Gas turbine engine seals and engines incorporating such seals

A method of assembling a stator apparatus includes providing a first vane having an airfoil section located between a first platform section and a second platform section, positioning a first shroud ring adjacent to the first vane, welding the first platform section of the first vane to the first shroud ring relative to a first edge of the of the first platform section of the first vane, and welding the first platform section of the first vane to the first shroud ring relative to a second edge of the of the first platform section. The second edge is located opposite the first edge.

Growing community of inventors

East Hampton, CT, United States of America

Kurt R Heinemann