Abstract: A system for conflict resolution in a multi-user design package includes a host computer having a memory and a processor, wherein the host computer is configured to operate a multi-user CAx environment, and is configured to receive edit commands from a plurality of local computers. A conflict resolution module is configured to be executed by the host computer, and the conflict resolution module is configured to prevent implementation of conflicting edit commands received from the plurality of local computers in the multi-user CAx environment.

Abstract: The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.

Abstract: 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.

Abstract: A system for multi-user design includes a host computer having a memory and a processor. The host computer is configured to operate a multi-user CAx environment including a part file, a plurality of local computers in communication with the host computer, a plurality of data storage systems in communication with the host computer, and a load balancing module within the CAx environment. Each of the local computers includes a local CAx environment portion of the multi-user CAx environment. Each of the data storage systems includes at least a portion of the part file. The load balancing module is configured to cause the host computer to assign edits originating at one of the local computers to one of the plurality of data storage systems.

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract: A system for collaborating on a component according to an example of the present disclosure includes, among other things, a computing device configured to execute a first multi-user CAx environment including a data module and an import module. The data module is configured to access a database relating to a component design. The component design relates to a group of function-based commands. The import module is configured to cause a user defined object to be imported into the first multi-user CAx environment in response to the user defined object being located based on an identifier. The user defined object relates to the component design.

Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes a cooling airflow passage that extends in a radial direction and an axial direction, an elongated cylindrical portion, and a flange.

Abstract: A spoke for a mid-turbine frame on a gas turbine engine includes a cylindrical portion. A flange is attached to the cylindrical portion. At least one gusset extends between the cylindrical portion and the flange. At least one gusset extends to a perimeter of the flange.

Abstract: 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 an editing module. The editing module is configured to generate at least one developed feature of the component design in response to executing at least one global command relating to a multi-user CAx command set, and to generate at least one undeveloped feature of the component design in response to executing at least one local command relating to a local CAx command set.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. At least one spoke includes a cooling airflow passage that extends through the inner frame case and the bearing support member.

Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange and between adjacent spokes. A method of cooling a portion of a gas turbine engine is also disclosed.

Abstract: A washer includes a hub and a first lobe connected to the hub. The first lobe includes a first hole. A second lobe is also connected to the hub and includes a second hole. A third lobe is also connected to the hub and includes a third hole. The first lobe extends from the hub at least partially in a first direction opposite the second lobe and the third lobe.

Abstract: A mid-turbine frame assembly includes an inner frame case which includes a first plurality of holes and a second plurality of holes. A plurality of tie rods is circumferentially spaced around the inner frame case and includes an inlet passage that is aligned with the first plurality of holes. A plurality of hollow airfoils is aligned with the second plurality of holes.

Abstract: A mid-turbine frame includes an inner frame case including a fluid passage. At least one hollow spoke is attached to the inner frame case. At least one hollow spoke includes an inlet passage. A transfer tube includes a first end that forms a first connection with at least one hollow spoke and a second end forms a second connection with the inner frame case.

Abstract: A system for authorization level verification includes a host computer having a processor and a memory. The processor and memory are configured to operate a multi-user CAx environment. The host computer further includes an authorization level module and an authorization level adjustment module. The host computer is configured to communicate with a plurality of local computers. Each of the local computers are configured to operate a local CAx environment of the multi-user CAx environment. A data storage element is in communication with the host computer and is configured to store a part file compatible with the multi-user CAx environment. The authorization level module is configured to facilitate a user login from one or more of the plurality of local computers.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. A passage extends through at least one spoke, the inner frame case, and the bearing support member.

Abstract: The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.

Abstract: A washer includes a hub and a first lobe connected to the hub. The first lobe includes a first hole. A second lobe is also connected to the hub and includes a second hole. A third lobe is also connected to the hub and includes a third hole. The first lobe extends from the hub at least partially in a first direction opposite the second lobe and the third lobe.

Abstract: A spoke for a mid-turbine frame on a gas turbine engine includes a cylindrical portion. A flange is attached to the cylindrical portion. At least one gusset extends between the cylindrical portion and the flange. At least one gusset extends to a perimeter of the flange.

Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. A passage extends through at least one spoke, the inner frame case, and the bearing support member.