Abstract: A system for magnetically inspecting a metallic component uses a manipulator configured to manipulate a relative position between a part fixture that holds the metallic component and a probe fixture that holds a magnetic probe, thereby causing the probe tip to trace an inspection route along the surface of the metallic component so that the probe tip contacts the metallic component such that an angular difference between the probe axis and a vector normal to the surface is less than a predetermined angle delta. The magnetic probe has a probe tip that measures magnetic permeability of the metallic component along the inspection route, which the controller receives. A method of performing the magnetic inspection is also disclosed.

Abstract: A system for magnetically inspecting a metallic component uses a manipulator configured to manipulate a relative position between a part fixture that holds the metallic component and a probe fixture that holds a magnetic probe, thereby causing the probe tip to trace an inspection route along the surface of the metallic component so that the probe tip contacts the metallic component such that an angular difference between the probe axis and a vector normal to the surface is less than a predetermined angle delta. The magnetic probe has a probe tip that measures magnetic permeability of the metallic component along the inspection route, which the controller receives. A method of performing the magnetic inspection is also disclosed.

Abstract: A method is provided that involves rotational equipment that includes a case and a first rotor blade within the case. During the method, a probe is arranged within the case adjacent the first rotor blade. A magnetic characteristic of the first rotor blade is measured using the probe. Presence of internal corrosion within the first rotor blade is determined based on the measured magnetic characteristic.

Abstract: Disclosed is a method of detecting mixed mode corrosion of a turbine airfoil. The method includes heat treating the turbine airfoil at a temperature of 1600 to 2100° F. in a Ni/Co oxide reducing atmosphere; and scanning the heat treated turbine airfoil with a magnetometer to determine the presence of mixed mode corrosion, wherein the turbine airfoil comprises a nickel superalloy and has internal passages.

Abstract: A method is provided that involves rotational equipment that includes a case and a first rotor blade within the case. During the method, a probe is arranged within the case adjacent the first rotor blade. A magnetic characteristic of the first rotor blade is measured using the probe. Presence of internal corrosion within the first rotor blade is determined based on the measured magnetic characteristic.

Abstract: A magnetoscop inspection system includes a magnetoscop, a computed tomography unit, and a corrosion model unit. The magnetoscop measures a permeability at a plurality of inspection points of a turbine component. The computed tomography unit generates a measured profile of a hollowed portion of the turbine component based at least in part on the permeability at the measured inspection points. The corrosion model unit stores in memory at least one reference computed tomography profile of a known turbine component. The magnetoscop inspection system determines a structural integrity of the turbine component based on a comparison between the measured profile and the reference profile corresponding to the turbine component currently under inspection.

Abstract: A system for magnetically inspecting a metallic component uses a manipulator configured to manipulate a relative position between a part fixture that holds the metallic component and a probe fixture that holds a magnetic probe, thereby causing the probe tip to trace an inspection route along the surface of the metallic component so that the probe tip contacts the metallic component such that an angular difference between the probe axis and a vector normal to the surface is less than a predetermined angle delta. The magnetic probe has a probe tip that measures magnetic permeability of the metallic component along the inspection route, which the controller receives. A method of performing the magnetic inspection is also disclosed.

Abstract: Disclosed is an apparatus and method for inspecting a component of a gas turbine engine, which includes a sleeve configured to surround a component of a gas turbine engine, the sleeve including: a pair of opposing wall members being secured to each other at at least one of a pair of opposite ends; an internal cavity located between the pair of opposing wall members, wherein the internal cavity extends from one end of the sleeve to an opposite end of the sleeve; and a plurality of orifices extending through the pair of opposing wall members, and wherein a probe is inserted in each orifice in one of the pair of opposing wall members to determine the state of the internal cavities of a gas turbine component and determine the structural integrity of the component.

Abstract: A magnetoscop inspection system includes a magnetoscop, a computed tomography unit, and a corrosion model unit. The magnetoscop measures a permeability at a plurality of inspection points of a turbine component. The computed tomography unit generates a measured profile of a hollowed portion of the turbine component based at least in part on the permeability at the measured inspection points. The corrosion model unit stores in memory at least one reference computed tomography profile of a known turbine component. The magnetoscop inspection system determines a structural integrity of the turbine component based on a comparison between the measured profile and the reference profile corresponding to the turbine component currently under inspection.

Abstract: Disclosed is an apparatus and method for inspecting a component of a gas turbine engine, which includes a sleeve configured to surround a component of a gas turbine engine, the sleeve including: a pair of opposing wall members being secured to each other at at least one of a pair of opposite ends; an internal cavity located between the pair of opposing wall members, wherein the internal cavity extends from one end of the sleeve to an opposite end of the sleeve; and a plurality of orifices extending through the pair of opposing wall members, and wherein a probe is inserted in each orifice in one of the pair of opposing wall members to determine the state of the internal cavities of a gas turbine component and determine the structural integrity of the component.

Abstract: Disclosed is a method of detecting mixed mode corrosion of a turbine airfoil. The method includes heat treating the turbine airfoil at a temperature of 1600 to 2100° F. in a Ni/Co oxide reducing atmosphere; and scanning the heat treated turbine airfoil with a magnetometer to determine the presence of mixed mode corrosion, wherein the turbine airfoil comprises a nickel superalloy and has internal passages.

Abstract: Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.

Abstract: A method and system for depositing multiple materials onto a substrate is described. The method broadly comprises the steps of providing a source of a first powder material to be deposited, providing a source of a second powder material to be deposited, and sequentially depositing the first powder material and the second powder material onto the substrate at a velocity sufficient to deposit the materials by plastically deforming the materials without metallurgically transforming the particles of powder forming the materials.

Abstract: Methods are described for applying abradable material onto a seal backing material to form an abradable seal between rotating and stationary components of turbines using cold spray deposition technology to control the density, porosity and thickness of the sealing layer.

Abstract: A method of manufacturing homogenous metal matrix composite (MMC) powders and using the powders as the feedstock with cold spray deposition is described to produce composite coatings and freestanding bulk forms. Measured quantities of metal and ceramic powders having predetermined particle sizes are blended to produce homogeneous MMC powders. Spray parameters and procedures are controlled to produce dense, strong and well-bonded MMC coatings on any substrate.

Abstract: Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.

Abstract: A method of manufacturing homogenous metal matrix composite (MMC) powders and using the powders as the feedstock with cold spray deposition is described to produce composite coatings and freestanding bulk forms. Measure quantities of metal and ceramic powders having predetermined particle sizes are blended to produce homogeneous MMC powders. Spray parameters and procedures are controlled to produce dense, strong and well-bonded MMC coatings on any substrate.

Abstract: Methods are described for applying abradable material onto a seal backing material to form an abradable seal between rotating and stationary components of turbines using cold spray deposition technology to control the density, porosity and thickness of the sealing layer.

Abstract: Methods are described for applying braze filler material onto a component part interface having a uniform thickness regardless of the interface contour using cold spray deposition technology.

Abstract: A method and system for depositing multiple materials onto a substrate is described. The method broadly comprises the steps of providing a source of a first powder material to be deposited, providing a source of a second powder material to be deposited, and sequentially depositing the first powder material and the second powder material onto the substrate at a velocity sufficient to deposit the materials by plastically deforming the materials without metallurgically transforming the particles of powder forming the materials.