General Electric Company

Timothy Joseph Higgins

William Steyer

Walter Jackson Tingle

John Paul Petrowicz

Carl E Pearson

A turbine engine includes a compressor section including a compressor, the compressor including an axial compressor stage, a variable outlet guide vane, and a centrifugal compressor stage, the variable outlet guide vane positioned between the axial compressor stage and the centrifugal compressor stage; a bleed assembly including a bleed airflow duct in airflow communication with the compressor and a bleed valve operable with the bleed airflow duct, the bleed valve including a bleed valve actuator; and a linkage assembly coupling the bleed valve actuator with the variable outlet guide vane such that that variable outlet guide vane is moveable with the bleed valve.

Axial and centrifugal compressor

A method for assembling a turbine engine including a compressor is disclosed. The method includes coupling an inlet including an inertial particle separator (IPS) and a first surface that is defined using a segment angle, to a gas turbine engine, and coupling the first surface substantially flush against a fuselage of an aircraft to reduce drag.

Segmented inertial particle separators and methods of assembling turbine engines

A method for operating a gas turbine engine including a compressor is provided. The method includes defining a predetermined concentration, placing at least one sensor in an inlet of the gas turbine engine, detecting a sand and dust concentration value using the at least one sensor; and deploying a boot to facilitate preventing particles from entering the compressor when the sand and dust concentration value equals or exceeds the predetermined concentration. The boot includes a plurality of fluid exit slots such that clean air is facilitated to be adhered to a flow path surface downstream from the boot.

Adaptive inertial particle separators and methods of use

An infrared suppressor system for a gas turbine engine is provided for suppressing infrared radiation associated with the hot metal parts of the engine and with the hot exhaust gases exhausted from the engine. The system features a unique arrangement of multiple baffles that are connected together as a single baffle module. The baffle arrangement permits mixing of hot and cool gas flows while eliminating line-of-sight infrared radiation in an axially compact suppressor. The baffles are additionally linked together into a single insertable baffle module that permits removal of the baffle module when infrared suppression is unnecessary.

Infrared suppressor

A gas turbine engine is provided with an improved fuel system that features a fuel manifold with a primary and secondary fuel flowpath circumventing a combustor section of the engine. The manifold is formed with a double-walled construction for the purpose of withstanding high temperatures or fires around the combustor section and, additionally, to provide a secondary flowpath for draining any fuel leakage from the manifold. The two walls of the manifold include an inner wall that encloses the primary fuel flowpath through the fuel system. A concentric outer wall encloses the inner wall and protects the primary fuel flowpath. The double-walled system is made possible with a unique manifold assembly utilizing double-walled manifold segments that interconnect fuel flowpaths through fuel injector base sections. When assembled, these parts connect together to form an integral double-walled fuel manifold assembly.

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Topsfield, MA, United States of America

Timothy Joseph Higgins