United Technologies Corporation

Raytheon Technologies Corporation

Andrew D Milliken

Raymond C Surace

Joshua Daniel Winn

William Arthur Sowa

Edward F Pietraszkiewicz

Bryan P Dube

William Abdel-Messeh

Jeffrey R Levine

Charles Gregory Jensen

Kurt R Heinemann

John H Mosley

Eleanor D Kaufman

Scott Henry Lamson

John C Calderbank

Conan P Cook

Robert Ivan Yorgason

Christopher Farnum

Diane K Emmerson

A system for component visualization according to an exemplary aspect of the present disclosure includes, among other things, a data module configured to access data corresponding to a component design. The component design includes at least one feature corresponding to a group of feature types. A display module is configured to display the data in an environment corresponding to a first user profile. A comparison module is configured to cause the display module to display the at least one feature when the at least one feature meets at least one predetermined criterion relating to the first user profile, and is configured to cause the display module to display a representation of the at least one feature when the at least one predetermined criterion is not met. The representation has a representation geometry that is a different geometry than a feature geometry of the at least one feature. A method for designing a component is also disclosed.

Export decomposition filter for a multi-user CAx environment

A component according to an exemplary aspect of the present disclosure includes, among other things, a wall, a first channel extending at least partially through the wall to a first outlet, and a second channel adjacent to the first channel and extending to a second outlet. The first channel is configured to communicate a cooling fluid along a first swirl flow path and the second channel is configured to communicate the cooling fluid along a second swirl flow path that is opposite the first swirl flow path.

Gas turbine engine component cooling channels

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 data module configured to access data corresponding to a component design, the component design corresponding to a group of feature types. A comparison module is configured to cause the data module to store data corresponding to the component design in a first data container when at least one predetermined criterion is met, and configured to cause the data module to store the data in a second data container when the at least one predetermined criterion is not met. A method for collaborating on a component is also disclosed.

Feature based control system for multi-user CAx

A gas turbine engine includes a compressor section, a combustor section and a turbine section. The turbine section includes components having a platform and an airfoil extending from the platform. The platform includes an outer surface, a cover plate and a cooling channel extending between the outer surface and the cover plate. The cooling channel receives cooling airflow to cool the platform and the airfoil.

Gas turbine engine component cooling scheme

A method of cooling a gas turbine engine component includes creating a cooling channel within a platform of the component, communicating cooling air into the cooling channel to cool the platform, and recycling the cooling airflow used to cool the platform by communicating the cooling airflow from the cooling channel into the airfoil to cool the airfoil.

Systems and methods for cooling vane platforms are provided. In this regard, a representative method for cooling a vane platform includes: providing a cooling channel on a platform from which a vane airfoil extends, the cooling channel being defined by a cooling surface and a channel cover, the channel wall being spaced from the cooling surface and located such that the cooling surface is positioned between a gas flow path of the vane and the channel cover; and directing a flow of cooling air through the cooling channel such that heat is extracted from the cooling surface of the platform by the flow of cooling air.

Systems and methods for providing vane platform cooling

A gas turbine engine component includes a platform and an airfoil extending from the platform. The platform includes an outer surface. A cover plate is positioned adjacent to the outer surface of the platform. A cooling channel extends between the outer surface and the cover plate and receives cooling air to cool the platform and the airfoil.

An internally cooled gas turbine engine turbine vane has an outboard shroud and an airfoil extending from an outboard end at the shroud to an inboard end. A cooling passageway has an inlet in the shroud, a first turn at least partially within the airfoil, a first leg extending from the inlet inboard through the airfoil to the first turn, and a second leg extending from the first turn. A dividing wall is in the passageway and has an upstream end in an outboard half of a span of the airfoil and has a plurality of vents. The vane may be formed as a reengineering of a baseline configuration lacking the dividing wall.

Turbine airfoil cooling passageway

The present invention relates to a system for delivering cooling air to a seal arrangement in a turbine stage of a gas turbine engine. The system comprises at least one vane having a passageway extending from an outer platform of the at least one vane to an inner platform of the at least one vane. A tube insert is positioned within the passageway. The tube insert has an inlet at one end for receiving cooling air from a source of cooling air and an outlet at a second end. A cover assembly is attached to the second end of the tube for receiving cooling air from the tube and delivering the cooling air to the seal arrangement. In a preferred embodiment, the cooling air is pre-swirled in the direction of rotation of a rotor stage of the turbine stage.

Growing community of inventors

Middletown, CT, United States of America

Andrew D Milliken