Abstract: A gas turbine engine includes a controller that controls a fan blade flutter characteristic through control of a variable area fan nozzle.

Abstract: A novel probabilistic method for analyzing high cycle fatigue (HCF) in a design of a gas turbine engine is disclosed. The method may comprise identifying a component of the gas turbine engine for high cycle fatigue analysis, inputting parametric data of the component over a predetermined parameter space into at least one computer processor, using the at least one computer processor to build a plurality of flexible models of the component based on the parametric data of the component over the predetermined parameter space, using the at least one computer processor to build a plurality of emulators of the component based on the plurality of flexible models, and using the at least one computer processor to predict a probability of HCF based at least in part on the parametric data of the component over the predetermined parameter space and the plurality of emulators.

Abstract: An exemplary gas turbine engine assembly includes a fan casing within a nacelle, a variable area fan nozzle. A controller is operable to move the variable area fan nozzle to influence a discharge airflow area associated with the variable area fan nozzle in response to an airfoil flutter condition. A gear train reduces a rotational speed of a fan in the gas turbine engine relative to another portion of the gas turbine engine.

Abstract: A method of manufacturing a thermal sensor array comprises: (a) providing a first wafer comprising an integrated circuit; (b) providing a second wafer comprising a carrier substrate, a thermally sensitive layer, a first electrode and a second electrode; (c) applying a polymer to a bonding surface of at least one of the first wafer and the second wafer; (d) contacting the first wafer and the second wafer for a period of time and at a temperature and pressure sufficient to create a bond; (e) removing the carrier substrate; and (f) patterning and etching the thermally sensitive layer, the first electrode and the second electrode to create an array of pixels, wherein the first wafer and the second wafer are bonded without the need for fine alignment of the wafers.

Abstract: A stator for a turbo-machine having a plurality of airfoils extending radially therefrom has a base from which the airfoils depend, and slits disposed in the base, each slit disposed adjacent a pair of airfoils, wherein a first set of adjacent slits and a distance between a second set of adjacent slits varies

Abstract: A gas turbine engine has a section, such as a compressor section, with at least two spaced apart stator assemblies and an asymmetrical rotor assembly positioned between the spaced apart stator assemblies. The asymmetrical rotor assembly has a rotor array which is asymmetric about at least one diameter of the rotor assembly.

Abstract: A gas turbine engine includes a controller that controls a fan blade flutter characteristic through control of a variable area fan nozzle.

Abstract: An exemplary gas turbine engine assembly includes a fan casing within a nacelle, a variable area fan nozzle. A controller is operable to move the variable area fan nozzle to influence a discharge airflow area associated with the variable area fan nozzle in response to an airfoil flutter condition. A gear train reduces a rotational speed of a fan in the gas turbine engine relative to another portion of the gas turbine engine.

Abstract: A system and method of controlling a fan blade flutter characteristic of a gas turbine engine includes adjusting a variable area fan nozzle in response to a neural network.

Abstract: An exemplary gas turbine engine assembly includes a nacelle, a core engine casing within the nacelle, a low pressure turbine having a pressure ratio that is greater than five, and a bypass passage established between the nacelle and the core engine casing. About 80% or more of airflow entering the engine is moved through the bypass passage.

Abstract: A blade includes an airfoil portion which defines at least one cavity with a damper located within the cavity, the damper includes a corrugated surface.

Abstract: A blade includes an airfoil portion which defines at least one cavity with a damper located within the cavity, the damper includes a corrugated surface.

Abstract: A method and control for predicting the remaining useful life of an airfoil for a gas turbine engine includes the steps of monitoring conditions of the blade such as flutter, leaning, etc. A measured amount of deflection of the airfoil is compared to tabulated data to predict an expected crack length which is likely causing the deflection, etc. Once a predicted crack length has been identified, the amount of accumulated damage to the airfoil at the crack is monitored and stored. The amount of useful life for the blade can be predicted by compiling the accumulated damage over time. The useful life remaining can be displayed such that flight plans or maintenance schedules for the aircraft can be modified as appropriate.

Abstract: A system and method of controlling a fan blade flutter characteristic of a gas turbine engine includes adjusting a variable area fan nozzle in response to a neural network.

Abstract: A gas turbine engine system includes a nacelle, a fan casing within the nacelle, a variable area fan nozzle, a sensor and a controller. The sensor detects an airfoil flutter condition. The controller communicates with the sensor and is operable to move the variable area fan nozzle to influence a discharge airflow area in response to the detection of the airfoil flutter condition.

Abstract: A method and control for predicting the remaining useful life of an airfoil for a gas turbine engine includes the steps of monitoring conditions of the blade such as flutter, leaning, etc. A measured amount of deflection of the airfoil is compared to tabulated data to predict an expected crack length which is likely causing the deflection, etc. Once a predicted crack length has been identified, the amount of accumulated damage to the airfoil at the crack is monitored and stored. The amount of useful life for the blade can be predicted by compiling the accumulated damage over time. The useful life remaining can be displayed such that flight plans or maintenance schedules for the aircraft can be modified as appropriate.

Abstract: The compressor shaft in a gas turbine engine is supported on a bearing having four independently hydraulically pressurized cells. The pressure in the cells is controlled by a signal processor based on engine operating parameters, including stall margin and blade tip to compressor case clearance.

Abstract: A pig for a fluid conducting system includes a support member, a first rim extending substantially longitudinally from an end of the support member, and a second rim extending substantially longitudinally from an opposite end of the support member. In a preferred embodiment, the pig also includes an axially located actuator, disposed beyond the first rim, for actuating a first location signal signifying the pig has reached a first predetermined location. This embodiment also includes another actuator, disposed beyond the second rim, for actuating a second location signal signifying the pig has reached a second predetermined location.

Abstract: A gauge protector comprising a body, connector, cap assembly, piston with inter-relief valve assembly, valve extension assembly, and tattletale tube assembly with plug and plug level indicator assembly.