A hybrid electric propulsion system includes a gas turbine engine having at least one compressor section and at least one turbine section operably coupled to a shaft. The hybrid electric propulsion system includes an electric motor configured to augment rotational power of the shaft of the gas turbine engine. A controller is operable to determine hybrid electric propulsion system parameters based on a composite system model and sensor data, determine a prediction based on the hybrid electric propulsion system parameters and the composite system model, determine a model predictive control optimization for a plurality of hybrid electric system control effectors based on the prediction using a plurality of reduced-order partitions of the composite system model, and actuate the hybrid electric system control effectors based on the model predictive control optimization.

According to an aspect, a waveguide system includes a first node, a second node, and a double-ridge waveguide. The double-ridge waveguide includes a metallic shell surrounding a waveguide core that forms a communication and radio frequency power transmission path in an aerospace environment. The first node is configured to propagate at least one communication channel and a radio frequency power transmission through the waveguide core to the second node during operation of the waveguide system in the aerospace environment.

A fuel control system for an aircraft includes first and second electric motor controlled fuel pumps connect in parallel with one another to a fuel line. A plurality of fuel nozzles are connected to the fuel line to issue pressurized fuel from the fuel line with the ability to throttle flow based on system needs along with the electric pumping. At least one fuel nozzle in the plurality of fuel nozzles includes a respective sensor system. A fuel controller is operatively connected to receive input from the respective sensor system of the at least one fuel nozzle, and operatively connected to control the first and second electric motor controlled pumps based on input from the respective sensor system of the at least one fuel nozzle.

A heat management system for turbomachinery is provided. The heat management system includes a thermal delivery system configured to providing heating, cooling, or a combination thereof, to a turbomachinery. The thermal delivery system includes a first heat transfer conduit and a second heat transfer conduit. The second heat transfer conduit is disposed on the turbomachinery adjacent to the first heat transfer conduit. The heat management system additionally includes a controller operatively coupled to the thermal delivery system and configured to control the heating, the cooling, or the combination thereof, of the turbomachinery via the thermal delivery system.

An electric blower system is described. The blower system includes a blower, an airflow system, a sensor, and an electric motor. The electric motor includes a motor controller. The motor controller is configured to operate the motor at a first torque and a first speed to generate a first airflow, determine a first airflow value wherein the first airflow value, the first torque, and the first speed define a first benchmark data point. The motor controller is also configured to operate the motor at a second torque and a second speed to generate a second airflow and determine a second airflow value wherein the second airflow value, the second torque, and the second speed define a second benchmark data point. The motor controller is further configured to generate an operating profile for the blower system defining torque, speed, and airflow points for different system resistances.

The present invention provides a thermal barrier coated component, monitoring or evaluation of the soundness of which is able to be adequately carried out on the basis of the thermal boundary conditions that are detected by a sensor. A thermal barrier coated component according to the present invention comprises: a base material; a first bond coat layer that is a metal bonding layer formed on the base material; a sensor unit that comprises a sensor and a conductive wire, which are formed on the first bond coat layer; a second bond coat layer that is formed on the first bond coat layer so as to cover at least the sensor unit, while having a surface roughness higher than that of the first bond coat layer; and a top coat layer that is formed on the second bond coat layer.

A mixed-flow turbine wheel includes: a plurality of rotor blades disposed on a circumferential surface of the hub at intervals in a circumferential direction and configured such that each of the plurality of rotor blades has a leading edge which includes, in a meridional view, an oblique edge portion where a distance between the leading edge and an axis of the rotational shaft decreases from a tip side toward a hub side, and a sensor detection surface having a flat shape and being applied with a marking which is detectable by an optical sensor device. The sensor detection surface is formed on at least one of the circumferential surface of the hub or an edge portion of a reference rotor blade being one of the plurality of rotor blades, such that, in the meridional view, a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the sensor detection surface is smaller than a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the oblique edge portion.

Methods and systems are provided for a turbocharger. In one example, a method may include bypassing exhaust gases flowing to the turbocharger in response to a catalyst temperature being less than a threshold temperature. The bypassing includes opening a bypass valve and adjusting a position of one or more turbine nozzle vanes.

A control system for turbine systems configured to utilize an intelligent model of particulate presence and accumulation within turbine systems to address engine maintenance, erosion, corrosion, and parts failure mitigation is disclosed. The control system may build an intelligent model of fluid flow based on the data value measured by at least one sensor and based on a database of known data values to provide an estimation of amount of ingress of air intake particles into the turbine system, fouling within the turbine system, erosion of at least a portion of the turbine system, and performance degradation rate of the turbine system.

A method of cooling a gas turbine engine case assembly includes moving a fan air valve that is operatively connected to a pre-cooler having a bypass inlet that is configured to receive bypass air that bypasses a gas turbine engine core to facilitate a provision of bypass air through a fan air valve inlet to the bypass inlet to a first open position, in response to a core compartment temperature being greater than a target core compartment temperature. The method further includes bleeding the bypass air through a bypass outlet of the pre-cooler into a core compartment.