A method for controlling a gas turbine assembly includes: a compressor in which compression of the outside air occurs for producing a flow of compressed air; a sequential combustor including a first combustor, in which combustion of a mixture of fuel and compressed air arriving from the compressor occurs for producing a flow of hot gasses, and a second combustor which is located downstream of the first combustor and in which combustion of a mixture of fuel and hot gasses arriving from the first combustor occurs; an intermediate turbine in which a partial expansion of the hot gasses arriving from the first combustor occurs; and a second combustor in which combustion of a mixture of fuel and hot gasses arriving from the intermediate turbine occurs; the method further includes, on a start-up transient operating phase of the gas turbine assembly, the step of controlling the fuel mass flow-rate supplied to the first and/or the second combustor on the basis of the flame temperature inside the first combustor.

A method for controlling a gas turbine assembly includes: a compressor in which compression of the outside air occurs for producing a flow of compressed air; a sequential combustor including a first combustor, in which combustion of a mixture of fuel and compressed air arriving from the compressor occurs for producing a flow of hot gasses, and a second combustor which is located downstream of the first combustor and in which combustion of a mixture of fuel and hot gasses arriving from the first combustor occurs; an intermediate turbine in which a partial expansion of the hot gasses arriving from the first combustor occurs; and a second combustor in which combustion of a mixture of fuel and hot gasses arriving from the intermediate turbine occurs; the method further includes, on a start-up transient operating phase of the gas turbine assembly, the step of controlling the fuel mass flow-rate supplied to the first and/or the second combustor on the basis of the flame temperature inside the first combustor.

In one embodiment, a system includes an inlet grid configured to reduce distortion of an incoming airflow. The system may also include a vibration device coupled to the inlet grid and a controller communicatively coupled to the vibration device. The controller may transmit a vibration signal to the vibration device causing the vibration device to vibrate the inlet grid such that the inlet grid resonates at a natural frequency inducing a mode shape in the inlet grid. The mode shape may break up and prevent ice on the inlet grid.

In one embodiment, a system includes an inlet grid configured to reduce distortion of an incoming airflow. The system may also include a vibration device coupled to the inlet grid and a controller communicatively coupled to the vibration device. The controller may transmit a vibration signal to the vibration device causing the vibration device to vibrate the inlet grid such that the inlet grid resonates at a natural frequency inducing a mode shape in the inlet grid. The mode shape may break up and prevent ice on the inlet grid.

The invention relates to an engine nacelle, including: a nacelle wall that has an inner side and an outer side; an inlet lip that is embodied at that end of the engine nacelle that is formed upstream; and an engine intake that takes in the air required for the respective engine and that is formed by the inner side of the nacelle wall. It is provided that the nacelle wall includes an air-permeable structure that extends from the outer side to the inner side of the nacelle wall, and that is configured for passing air that flows against the outer side from the outer side to the inner side. The invention further relates to a method for influencing the flows inside an engine nacelle.

The invention relates to an engine nacelle, including: a nacelle wall that has an inner side and an outer side; an inlet lip that is embodied at that end of the engine nacelle that is formed upstream; and an engine intake that takes in the air required for the respective engine and that is formed by the inner side of the nacelle wall. It is provided that the nacelle wall includes an air-permeable structure that extends from the outer side to the inner side of the nacelle wall, and that is configured for passing air that flows against the outer side from the outer side to the inner side. The invention further relates to a method for influencing the flows inside an engine nacelle.

An engine inlet cover and a method for covering an engine inlet are provided. A method for covering an engine inlet includes providing a collapsible cover comprising a connection pin defining an axis; a frame including interconnected arms; and a web. Further, the method includes storing the collapsible cover in a stowed configuration in which the arms are aligned. Also, the method includes rotating the arms from the stowed configuration to an operating configuration in which the arms are radially spaced about the axis, enclosing the frame in the operating configuration with the web to define an interior volume, and placing the cover over the engine inlet.

An engine inlet cover and a method for covering an engine inlet are provided. A method for covering an engine inlet includes providing a collapsible cover comprising a connection pin defining an axis; a frame including interconnected arms; and a web. Further, the method includes storing the collapsible cover in a stowed configuration in which the arms are aligned. Also, the method includes rotating the arms from the stowed configuration to an operating configuration in which the arms are radially spaced about the axis, enclosing the frame in the operating configuration with the web to define an interior volume, and placing the cover over the engine inlet.

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.

A turbofan engine has a fan drivingly engaged by a shaft for rotation about a rotation axis and having: fan blades circumferentially distributed about the rotation axis and drivingly engaged by the shaft; an ice-accruing feature located on a surface of the fan exposed to an air flow flowing between the fan blades, the ice-accruing feature having a shape providing a non-axisymmetric ice accumulation on the fan to create a rotational imbalance; a balancing feature secured to the fan or to the shaft to counteract the ice-accruing feature such that the fan is rotationally balanced when the fan is free of ice, the balancing feature being located such as to be outside the air flow; an aircraft controller; and a sensor operatively connected to the fan and operable to send a signal to the aircraft controller, the signal indicative of the rotational imbalance caused by the ice-accruing feature.