Abstract: A set of user interface tools is described facilitating asynchronous adjudication of one or more regions-of-interest in a medical image by a group of two or more graders, each of which has access to the set of tools in a workstation environment. The set of tools include (1) a feature for enabling the graders to assess the medical image and manually delineate one or more specific regions-of-interest (ROI) in the medical image, (2) a feature for assessing the ROI(s) delineated by other graders, including display of the ROI delineated by other graders; (3) dialog features for explaining and discussing the assessments, including a text feature for discussing the assessments. The dialog features and the ROIs delineated by all the graders are visible to all the graders on the workstation display as they collectively adjudicate the medical image in a round-robin manner. The set of tools further include (4) a feature for manually verifying grader agreement with the other graders' assessments.

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.

Abstract: The walls of the liner of a gas turbine combustor are segmented and disposed axially and circumferentially to define a combustion chamber. The liner is formed by radially spaced walls preferably fabricated from a ceramic or other high temperature brittle material. The wall adjacent the hot combustion products is prestressed at room temperature and the juxtaposed wall is cooperatively shaped to define a supporting frame for the prestressed wall so as to minimize the overall stresses occasioned in the hostile environment to which the prestressed wall is subjected.

Abstract: Apparatus for impeding the leakage of a gaseous medium between the rotating and stationary components of a machine is disclosed. Various construction details which are specifically adapted for use in gas turbine engines are developed. Wide channel type sealing techniques are discussed in combination with honeycomb facing materials.