Abstract: A heat exchanger includes a fin body and a heat pipe having a first portion disposed on or at least partially within the fin body and a second portion extending from the fin body, wherein the heat pipe includes a hollow core filled with a heat pipe working fluid having a liquid phase that is configured to transition to gas and to be returned to the liquid phase at an operational temperature of the heat exchanger.

Abstract: A device and methods are provided for controlling blade outer air seal of a gas turbine engine. In one embodiment, a method includes receivg blade outer air seal clearance from an integrated sensor actuator, determining blade outer seal control by an electronic engine control unit, and controlling the blade outer air seal clearance by the electronic engine control unit, wherein an interleaved blade outer air seal is positioned by an integrated sensor actuator.

Abstract: A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.

Abstract: A turbomachine blade clearance system includes an actuator including an actuating portion that can be fixed to an interior surface of a turbomachine housing and a shaft for actuating movement relative to the turbomachine housing, a turbomachine blade seal operatively connected to the shaft of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade, a waveguide disposed within the shaft, and at least one antenna disposed in electromagnetic communication with the waveguide such that a signal from the antenna can be directed by the waveguide.

Abstract: A vibration sensor includes a probe body with a vibration isolator operatively connected to the probe body for isolation of the probe body from vibrations of a structure to be monitored for vibration. A waveguide is operatively connected to the probe body to convey microwaves to and from a surface for sensing vibration of the structure to be monitored for vibration.

Abstract: A heat exchanger includes a fin body and a heat pipe having a first portion disposed on or at least partially within the fin body and a second portion extending from the fin body, wherein the heat pipe includes a hollow core filled with a heat pipe working fluid having a liquid phase that is configured to transition to gas and to be returned to the liquid phase at an operational temperature of the heat exchanger.

Abstract: An apparatus includes a blade clearance detection system. A probe is configured to communication detection frequencies from and gather reflected signals for the blade tip detection system. The probe has an end supported relative to the casing. A material provides a reference point. The blade tip clearance detection system is configured to generate a first detection frequency configured to pass through the material to detect the position of a target structure, generate a second detection frequency configured to reflect from and detect the reference point, and determine a position of a surface approximate to the target structure based upon the reference point.

Abstract: A turbomachine blade clearance system includes an actuator including an actuating portion that can be fixed to an interior surface of a turbomachine housing and a shaft for actuating movement relative to the turbomachine housing, a turbomachine blade seal operatively connected to the shaft of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade, a waveguide disposed within the shaft, and at least one antenna disposed in electromagnetic communication with the waveguide such that a signal from the antenna can be directed by the waveguide.

Abstract: A rotor blade measurement system includes a microwave source and a probe. A directional coupler is attached to the source and the probe. A detector is attached to the directional coupler. The probe directs a microwave signal toward a rotor such that during rotation the rotor blade will pass through the path of the microwave signal. As the rotor blade passes the microwave signal is reflected back to the probe. The directional coupler separates the original microwave signal and the reflected signal. The detector then determines the energy level of the reflected signal. As each rotor blade passes the microwave signal it generates a reflected signal that can be analyzed over time. From the length and shape of the waveform of the reflected signal the amount of twisting and flutter in a rotor blade can be determined.

Abstract: A gas turbine engine section has a rotor carrying a plurality of blades. The blades have airfoils which define a radially outer tip. A blade outer air seal is positioned radially outwardly of the tips of the blades. The blade outer air seal is provided by at least a plurality of circumferentially spaced segments, which slide circumferentially relative to each other to adjust an inner diameter of an inner surface of the blade outer air seal segments. An actuator actuates the blade outer air seal segments to slide towards each other to control a clearance between the inner periphery of the blade outer air seal segments and the radially outer tip of the blade airfoils. A gas turbine engine is also disclosed.

Abstract: A heat exchanger includes a heat exchanger housing having a first flow path with a first inlet and a first outlet, and having a second flow path with a second inlet and a second outlet. A first fluid flows from the first inlet to the first outlet in the first flow path, and a second fluid flows from the second inlet to the second outlet in the second flow path. A heat pipe array within the housing extends between the first flow path and the second flow path for transferring heat from the first fluid to the second fluid.

Abstract: A vibration sensor includes a probe body with a vibration isolator operatively connected to the probe body for isolation of the probe body from vibrations of a structure to be monitored for vibration. A waveguide is operatively connected to the probe body to convey microwaves to and from a surface for sensing vibration of the structure to be monitored for vibration.

Abstract: A conditioner for conditioning fuel passing therethrough includes a deoxygenator having a body in which oxygen is removed from the fuel, and a heat exchanger attaching directly to the body for moderating a temperature of the fuel.

Abstract: A gas turbine engine section has a rotor carrying a plurality of blades. The blades have airfoils which define a radially outer tip. A blade outer air seal is positioned radially outwardly of the tips of the blades. The blade outer air seal is provided by at least a plurality of circumferentially spaced segments, which slide circumferentially relative to each other to adjust an inner diameter of an inner surface of the blade outer air seal segments. An actuator actuates the blade outer air seal segments to slide towards each other to control a clearance between the inner periphery of the blade outer air seal segments and the radially outer tip of the blade airfoils. A gas turbine engine is also disclosed.

Abstract: A conditioner for conditioning fuel passing therethrough includes a deoxygenator having a body in which oxygen is removed from the fuel, and a heat exchanger attaching directly to the body for moderating a temperature of the fuel.

Abstract: A system for managing thermal transfer in an aircraft includes a fuel stabilization unit, a fuel-air heat exchanger, and a turbine. The fuel-air heat exchanger is located downstream from the fuel stabilization unit. The fuel-air heat exchanger places deoxygenized fuel in a heat exchange relationship with compressor bleed air to produce heated deoxygenized fuel and cooled bleed air. The turbine is operationally connected to the engine compressor and receives cooled bleed air from the fuel-air heat exchanger.

Abstract: A turbine engine includes a target structure, for example, a rotating turbine blade. A probe is arranged near the target structure for communicating a detection frequency relative to the target structure for gathering information such as tip clearance. A housing is arranged adjacent to the target structure. In one example, the housing is a blade outer air seal. The housing includes a structural material that supports a window material. The window material is arranged between the probe and the target structure. The window material is transparent to the detection frequency permitting the detection frequency to pass through the window to the target structure for measurement of its position relative to the housing. The window material prevents probe contamination and provides a seal between the cooling path and turbine gas flow path.

Abstract: An apparatus includes a blade clearance detection system. A probe is configured to communication detection frequencies from and gather reflected signals for the blade tip detection system. The probe has an end supported relative to the casing. A material provides a reference point. The blade tip clearance detection system is configured to generate a first detection frequency configured to pass through the material to detect the position of a target structure, generate a second detection frequency configured to reflect from and detect the reference point, and determine a position of a surface approximate to the target structure based upon the reference point.

Abstract: A system and method for determining thermal growth of motor or engine parts to thereupon control the clearance of motor or engine fan blades is disclosed herein. In addition, a system and method for monitoring the health of a turbine engine, its components and sub-components is also described herein. The system(s) and method(s) described herein permit continuous monitoring during the life of the engine for radial clearances and blade and rotor vibration problems, which will assist in correcting and retaining performance for a longer on-wing time in operation. In addition, inconsistent engine-to-engine performance variations due to component tolerances, engine operation characteristics, and operation during extremes in ambient temperatures can be eliminated or significantly minimized when employing the system(s) and method(s) described herein.

Abstract: A turbine engine includes a target structure, for example, a rotating turbine blade. A probe is arranged near the target structure for communicating a detection frequency relative to the target structure for gathering information such as tip clearance. A housing is arranged adjacent to the target structure. In one example, the housing is a blade outer air seal. The housing includes a structural material that supports a window material. The window material is arranged between the probe and the target structure. The window material is transparent to the detection frequency permitting the detection frequency to pass through the window to the target structure for measurement of its position relative to the housing. The window material prevents probe contamination and provides a seal between the cooling path and turbine gas flow path.