United Technologies Corporation

Massachusetts Institute of Technology

Raytheon Technologies Corporation

Rtx Corporation

Carroll V Sidwell

Frederick M Schwarz

Alexander Staroselsky

Marc J Muldoon

Michael Winter

Thomas J Martin

Robert J Morris

Zhong Ouyang

Kevin D Smith

David L Darmofal

Anthony R Parente

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a plurality of upstream airfoils, a plurality of downstream airfoils, a sensor, an actuator and a controller. The upstream airfoils include a first upstream airfoil. The downstream airfoils are arranged downstream of and adjacent the upstream airfoils. The downstream airfoils include a first downstream airfoil. The sensor is arranged with the first upstream airfoil. The sensor is configured to provide sensor data indicative of a parameter for the first upstream airfoil. The actuator is coupled to the first downstream airfoil. The controller is configured to signal the actuator to move the first downstream airfoil based on the sensor data.

Monitoring and adjusting airfoils of an aircraft propulsion system

Aircraft hydrogen fuel systems and methods and systems of starting such systems are described. The aircraft hydrogen fuel systems include a hydrogen burning main engine, a main tank configured to contain liquid hydrogen to be supplied to the main engine during a normal operation, and a starter tank configured to contain gaseous hydrogen to be used during a startup operation of the main engine. Methods and processes for starting and/or restarting such systems are described.

Methods and systems for starting hydrogen powered gas generators

A method for improving the strength, creep and failure resistance of a single crystal component, such as a turbine engine component, is provided. The method comprises the steps of forming a component, such as a turbine engine component, having a single crystal microstructure with a plurality of &#x3b3;' cuboids forming a limited amount of oriented platens in a particular direction prior to the component being placed into service to delay coalescence of the platens relative to the applied load.

Preferential hardening of single crystal blades

A method of identifying a flaw in a part is provided that includes vibrating a part to induce heat. The heat originates in any flaws in the part. A thermal image is obtained using, for example, an infrared camera. A mathematical representation of the thermophysics, such as the heat conduction or thermal energy equations using the boundary element method or finite element method is used to identify a source and an intensity of the heat identified with the thermal image. Using the source and intensity of the heat, flaw characteristics for the part can be determined. The method is employed using an inspection system that includes a vibration device for vibrating the part. An imaging device, such as an infrared camera, measures temperature on the surface of the part. An assumption is made or additional measurements are taken to obtain values for surface flux or surface heat transfer coefficients. A processor communicates with the imaging device for receiving the surface temperature. The processor includes computer memory having part characteristics and mathematical equations. The processor uses the measured surface temperature, assumed or measured heat flux or heat transfer coefficients, part characteristics and mathematical equations to determine the flaw characteristics in the part.

Inverse thermal acoustic imaging part inspection

Method for assembling into turbine sets turbine components having internal cooling passages. The turbine components are classified according to flow capability through the internal cooling passages and turbine sets are assembled in which the turbine components have the same flow capability classification.

Method for assembling gas turbine engine components

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Wethersfield, CT, United States of America

Carroll V Sidwell