United Technologies Corporation

Wayne Hurwitz

Glenn Levasseur

Ashok K Jain

William J McVey

Stuart S Ochs

William J Mcvey

The disclosed turbine engine includes a fan nacelle surrounding a fan and including an inlet arranged upstream from the fan. The inlet includes an inlet surface having a boundary layer flow. A flow control actuator is in fluid communication with the inlet surface. A boundary layer sensing device is associated with the inlet surface for detecting a boundary layer condition at the inlet surface. A controller is in communication with the flow control actuator and the boundary layer sensing device. The controller is programmed to command the flow control actuator in response to the boundary layer sensing device detecting an undesired boundary layer condition. In this manner, the flow control actuator generates a desired boundary layer condition.

Active flow control for nacelle inlet

A turbofan engine control system and method includes a core nacelle housing (), a compressor and a turbine. A turbofan is arranged upstream from the core nacelle and is surrounded by a fan nacelle (). A bypass flow path () is arranged downstream from the turbofan between the core and fan nacelles. The bypass flow path includes a nozzle exit area (). A controller () detects at least one of a take-off condition and a landing condition. The controller changes effectively the nozzle exit area to achieve a thrust vector in response to the take-off and landing conditions.

Reduced take-off field length using variable  nozzle

A turbofan engine control system is provided for managing a low pressure compressor operating line. The engine includes a low spool having a low pressure compressor housed in a core nacelle. A turbofan is coupled to the low spool. A fan nacelle surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area. A controller is programmed to effectively change the nozzle exit area in response to an undesired low pressure compressor stability margin which can result in a stall or surge condition. In one example, the physical nozzle exit area is decreased at the undesired stability condition occurring during engine deceleration. A low pressure compressor pressure ratio, low spool speed and throttle position are monitored to determine the undesired stability margin.

Operational line management of low pressure compressor in a turbofan engine

(A) A turbofan engine control system is provided for managing a fan operating line. The engine () includes a spool having a turbine housed in a core nacelle (). A turbofan () is coupled to the spool (). A fan nacelle () surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area (). A controller () is programmed to effectively change the nozzle exit area in response to an undesired turbofan stability margin which may result in a stall or flutter condition. In one example, the physical nozzle exit area is increased at the undesired stability condition in which the airflow into the engine creates a destabilizing pressure gradient at the inlet side of the turbofan. A turbofan pressure ratio, turbofan pressure gradient, low spool speed and throttle position are monitored to determine the undesired turbofan stability margin.

Growing community of inventors

West Hartford, CT, United States of America

Wayne Hurwitz