Cantilevered airfoils and methods of forming the same are disclosed herein. An example airfoil disclosed herein includes an airfoil including an airfoil body including a first face and a second face, a first recessed portion formed in the first face and internal temperature-regulating features and a first insert disposed within the first recessed portion, the first insert causing the airfoil body to assume a first predefined curvature profile at a first temperature, the first insert causing the airfoil body to assume a second predefined curvature profile at a second temperature.

The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.

The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.

A method for inhibiting particulate ingress in a combustion system includes acquiring particulate ingress data, determining a probable particulate ingress location on an air inlet of the combustion system in dependence upon the particulate ingress data, and deploying a filter screen at the determined probable particulate ingress location to inhibit particulate ingress at the determined probable particulate ingress location.

A pressure regulating valve assembly includes: a valve having an upstream side receiving an input flow and a downstream side providing an output flow, an actuator for opening and closing the valve, including partially opening the valve, and a regulator controlling the actuator to open, close or partially open the valve. The regulator includes a sense pressure port, wherein pressure at the port is maintained constant by the regulator. A chamber has a first entry orifice, a second entry orifice and an exit orifice. The first entry orifice is connected to the upstream side, the second entry orifice is connected to the downstream side, and the exit orifice is connected to the port. The exit orifice provides that the pressure at the exit orifice lies between the pressure at the first entry orifice and the pressure at the second entry orifice.

The present invention discloses a supersonic inlet with synchronous adjustment of capture area and throat area, wherein the throat area may be adjusted by providing a movable throat section, while the capture area may be adjusted by providing a movable cowl section at the front end of the cowl lip, thereby realizing the effect that the capture area and the throat area of the inlet may be adjusted in synchronization. Meanwhile, the present invention also provides a control method and a design method of the above-mentioned inlet. The present invention greatly simplifies the actuation system and control system, significantly reduces the weight of the accessory system, and enables the performance of the inlet within a wide envelope range to be maintained in an excellent state.

The present invention discloses a supersonic inlet with synchronous adjustment of capture area and throat area, wherein the throat area may be adjusted by providing a movable throat section, while the capture area may be adjusted by providing a movable cowl section at the front end of the cowl lip, thereby realizing the effect that the capture area and the throat area of the inlet may be adjusted in synchronization. Meanwhile, the present invention also provides a control method and a design method of the above-mentioned inlet. The present invention greatly simplifies the actuation system and control system, significantly reduces the weight of the accessory system, and enables the performance of the inlet within a wide envelope range to be maintained in an excellent state.

An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.

An inlet flow distortion control system employs a plurality of flow control devices forming at least one array integrated into an internal surface of the inlet. The at least one array extends over an azimuthal range relative to a normal flow axis of the inlet and has a plurality of circumferential rows spaced at increasing distance from a highlight of the inlet. A control system is operably connected to the flow control devices and adapted to activate flow control devices in selected subarrays of the array responsive to a predetermined flight condition.

There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.