General Electric Company

Keith Blodgett

Vishnu Vardhan Venkata Tatiparthi

Sai Venkata Kathik Saripella

Brandon Wayne Miller

Arthur William Sibbach

Jeffrey Donald Clements

Randy M Vondrell

Bhaskar Nanda Mondal

Scott Alan Schimmels

Arnab Sen

Mustafa Dindar

Arvind Namadevan

Shankar Jayaraman

Sai Venkata Karthik Saripella

A turbine engine including a fan having a plurality of fan blades, a turbo-engine positioned downstream of the fan and having a core inlet, an engine intake that extends to the core inlet, and a variable engine intake system. Air enters the turbine engine through the engine intake. The variable engine intake system includes a plurality of wind condition sensors for sensing wind conditions about the turbine engine, and a controller. The plurality of wind condition sensors includes a first wind condition sensor on a first side of the turbine engine and a second wind condition sensor on a second side of the turbine engine. The controller adjusts the engine intake based on the wind conditions about the turbine engine from the first wind condition sensor and the second wind condition sensor.

Turbine engine having a variable engine intake system

Methods, apparatus, systems, and articles of manufacture are to control air flow separation of an engine. An example turbofan includes a nacelle having an outer lip surface, an inner lip surface, a first opening and a second opening, the first opening coupled to a first region forward of a fan of the turbofan, the second opening coupled to a second region aft of the fan, the nacelle including a first pressure sensor coupled to the outer lip surface, a second pressure sensor coupled to the inner lip surface, and an actuator, and a conduit coupled to the actuator, the conduit configured to have a first end and a second end, the first end coupled to the first opening, the second end coupled to the second opening.

Methods and apparatus to control air flow separation of an engine

A turbine engine including a fan, a nacelle circumscribing at least the fan, a compressor section downstream of the fan, and a conduit defined, at least in part, by the nacelle. The conduit includes a first opening at the compressor section, a second opening downstream of the fan and upstream of the compressor section, and a third opening upstream of the fan. Pressure sensors coupled to the nacelle are communicatively coupled to at least one actuator. The at least one actuator can adjust airflow between the first opening and the second opening, or between the first opening and the third opening. The pressure sensors can provide outputs for generating commands that control the at least one actuator.

Methods and apparatus to detect air flow separation of an engine

Methods, apparatus, systems, and articles of manufacture are disclosed to detect air flow separation of an engine. An example apparatus includes hardware, and memory including instructions that, when executed, cause the hardware to at least determine an inlet flow separation parameter based on a first pressure value from a first pressure sensor included in a nacelle of a turbofan and a second pressure value from a second pressure sensor included in the nacelle, determine a severity level parameter based on the inlet flow separation parameter, the severity level parameter based on a difference between the first pressure value and the second pressure value, and adjust a contribution of airflow from aft of a fan of the turbofan based on the severity level parameter.

An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft includes a fuselage extending longitudinally between the forward end of the aircraft and the aft end of the aircraft; a primary wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; a first engine mounted to the primary wing assembly; and a first engine wing assembly extending outward from the first engine.

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Milford, OH, United States of America

Keith Blodgett