Abstract: A propulsor for a gas turbine engine may comprise a case including a duct disposed along an axis to define a flow path, a rotor including a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path, and a row of guide vanes situated in the flow path. A first guide vane may comprise a radially inner length (LI), a radially outer length (LO), and a midspan length (LM). The first guide vane may have a first dimensional relationship defined as LO/LM. The first guide vane may have a second dimensional relationship defined as LI/LM. The first dimensional relationship and/or the second dimensional relationship may be greater than 1.05.

Abstract: A propulsor for a gas turbine engine may comprise a case including a duct disposed along an axis to define a flow path, a rotor including a row of propulsor blades extending in a generally radial direction outwardly from a hub, the hub rotatable about the axis such that the propulsor blades deliver airflow into the flow path, and a row of guide vanes situated in the flow path. A first guide vane may comprise a radially inner length (LI), a radially outer length (LO), and a midspan length (LM). The first guide vane may have a first dimensional relationship defined as LO/LM. The first guide vane may have a second dimensional relationship defined as LI/LM. The first dimensional relationship and/or the second dimensional relationship may be greater than 1.05.

Abstract: A method for detecting integrity degradation of a turbine engine component includes the steps of detecting oxygen in a cavity of a turbine engine component; receiving a signal confirming the detection of oxygen; and detecting an integrity degradation of the turbine engine component by the detection of oxygen.

Abstract: A heat exchange system for use in operating equipment in which a working fluid is utilized needing a heat exchange system to provide air and working fluid heat exchanges to cool the working fluid at selectively variable rates in airstreams. The system comprises a plurality of heat exchangers including a first heat exchanger in the plurality of heat exchangers that is mounted with respect to the equipment so as to permit corresponding portions of the airstreams to pass through the core thereof during at least some such uses of the equipment. Also, a second heat exchanger is mounted with respect to the equipment so as to selectively permit corresponding portions of the airstreams to pass through the core thereof during such uses of the equipment. A core actuator is mounted with respect to the second heat exchanger to selectively increase or reduce the passing of those corresponding portions of the airstreams through the core.

Abstract: A heat exchange system for use in fluid operated equipment to provide air and working fluid heat exchanges to cool the working fluid in airstreams on a stream side of a wall. An actuator is mounted to be substantially located on a side of the wall opposite the stream side thereof having a positionable motion effector. A heat exchanger core having a plurality of passageway structures therein to enable providing the working fluid to, and removal therefrom. The heat exchanger core is mounted on the motion effector so as to be extendable and retractable thereby through the opening for selected distances into that region to be occupied by the airstreams.

Abstract: A method for detecting integrity degradation of a turbine engine component includes the steps of detecting oxygen in a cavity of a turbine engine component; receiving a signal confirming the detection of oxygen; and detecting an integrity degradation of the turbine engine component by the detection of oxygen.

Abstract: A gas turbine engine is provided that includes one or more rotor assemblies, one or more shroud segments, and an actuator. The rotor assemblies are rotatable around an axially extending rotational axis, and each rotor assembly has a plurality of blades. Each blade has a blade tip. The one or more shroud segments each has a blade seal surface disposed radially outside of the one or more rotor assemblies. The blade tips and blade seal surfaces (collectively referred to as the blade seal surface) have mating conical geometries and a clearance distance extending between the blade tips and blade seal surface. The blade tips and blade seal surface are disposed at an angle relative to the axial centerline of the engine, which angle is greater than zero. The actuator is selectively operable to axially move one or both of the shroud segments and rotor assemblies relative to the other of the shroud segments and rotor assemblies to alter the clearance distance.

Abstract: A zero running clearance system for gas turbine engines includes a gas turbine engine compressor having one or more first rotor assemblies and one or more first stator assemblies disposed adjacent the one or more first rotor assemblies; a gas turbine engine turbine having one or more second rotor assemblies and one or more second stator assemblies disposed adjacent the one or more second rotor assemblies; one or more shroud segments having blade seal surfaces disposed radially outside of the tips of blades of both the first and second rotor assemblies and a clearance distance extending between the blade tips and blade seal surfaces; and, an actuator selectively operable to axially move the first and said second rotor assemblies to alter the clearance distance.