A motor cooling system including, an engine nacelle defining a primary axis, a stator housing within the engine nacelle, a plurality of stator guide vanes attached to the stator circumferentially disposed around the primary axis, where at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to receive a fluid from a first engine component in the engine nacelle and wherein at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to pass the fluid to a second engine component in the engine nacelle.

A motor cooling system including, an engine nacelle defining a primary axis, a stator housing within the engine nacelle, a plurality of stator guide vanes attached to the stator circumferentially disposed around the primary axis, where at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to receive a fluid from a first engine component in the engine nacelle and wherein at least one stator guide vane of the plurality of stator guide vanes includes at least one conduit configured to pass the fluid to a second engine component in the engine nacelle.

A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references.

A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references.

A combustion liner for a gas turbine engine. The combustion liner defines a bypass direction which extends between an upstream portion and a downstream portion of the combustion liner in use, the combustion liner. The combustion liner comprises a liner wall for defining at least a portion of a combustion chamber, the liner wall having an outer surface and an inner surface and a depth between the outer and inner surfaces of the combustion liner in use. The combustion liner comprises a chute formed through the liner wall for conveying fluid from the outer surface through the liner wall and ejecting fluid from an exhaust hole of the chute on the inner surface, the exhaust hole having a length L along the bypass direction. The combustion liner also comprises a fluid-guiding surface at an upstream side of the chute which defines an arc terminating at the exhaust hole, the fluid guiding surface configured to guide fluid from a direction generally parallel to the outer surface into the chute to be ejected from the chute exhaust hole at a direction generally perpendicular to the inner surface.

A combustion liner for a gas turbine engine. The combustion liner defines a bypass direction which extends between an upstream portion and a downstream portion of the combustion liner in use, the combustion liner. The combustion liner comprises a liner wall for defining at least a portion of a combustion chamber, the liner wall having an outer surface and an inner surface and a depth between the outer and inner surfaces of the combustion liner in use. The combustion liner comprises a chute formed through the liner wall for conveying fluid from the outer surface through the liner wall and ejecting fluid from an exhaust hole of the chute on the inner surface, the exhaust hole having a length L along the bypass direction. The combustion liner also comprises a fluid-guiding surface at an upstream side of the chute which defines an arc terminating at the exhaust hole, the fluid guiding surface configured to guide fluid from a direction generally parallel to the outer surface into the chute to be ejected from the chute exhaust hole at a direction generally perpendicular to the inner surface.

An objective-driven system for blade tip clearance control may comprise a BOAS and a controller in operable communication with the BOAS. A tangible, non-transitory memory may be configured to communicate with the controller, the tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an operating objective definition, and modulating a location of the BOAS using an optimization loop comprising the operating objective definition, input vector variables, and output vector variables driven by the input vector variables.

An objective-driven system for blade tip clearance control may comprise a BOAS and a controller in operable communication with the BOAS. A tangible, non-transitory memory may be configured to communicate with the controller, the tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an operating objective definition, and modulating a location of the BOAS using an optimization loop comprising the operating objective definition, input vector variables, and output vector variables driven by the input vector variables.

A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.

A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.