Abstract: In accordance with some embodiments, systems, methods, and media for fault localization in declarative specification languages are provided. In some embodiments, a method comprises: receiving a model in a declarative specification language; querying an automated analysis of the declarative specification language for a counterexample, wherein the counterexample is an instance of the model that does not satisfy a property; using a partial max satisfiability solver to find an instance that satisfies the property; determining one or more differences in an expression from the model between the counterexample and the satisfying instance; analyzing the differences between the counterexample and the satisfying instance; determining a suspicion score for the expression in the model; and causing the suspicion score to be presented.

Abstract: Past gas turbine engines have been manufactured with a variety of systems which have attempted to compensate for the varying radial clearance or interface between a tip of a turbine blade and a surrounding shroud. Such systems have engineered in large clearances, utilized special tips on blades and provided abradable structures. The present system controls a radial clearance or an interface or spaced distance between a tip of a blade and a stationary shroud. The system includes an introduction of a cool fluid or a hot fluid flow or a combination of cool fluid and hot fluid into a support case cavity. The flow is controlled by modulating a flow control apparatus and controlling the expansion of a nozzle support case and a stationary shroud relative to the position of the tip of the turbine blade. The system improves efficiency, longevity and operation of the gas turbine engine.

Abstract: A turbine nozzle vane assembly having a preestablished rate of thermal expansion is positioned in a gas turbine engine and being attached to conventional metallic components. The metallic components having a preestablished rate of thermal expansion being greater than the preestablished rate of thermal expansion of the turbine nozzle vane assembly. The turbine nozzle vane assembly includes an outer shroud and an inner shroud having a plurality of vanes therebetween. Each of the plurality of vanes have a device for heating and cooling a portion of each of the plurality of vanes. Furthermore, the inner shroud has a plurality of bosses attached thereto. A cylindrical member has a plurality of grooves formed therein and each of the plurality of bosses are positioned in corresponding ones of the plurality of grooves.