Abstract: An electrodeposited nickel-chromium-aluminum (Ni—Cr—Al) composite including nickel-chromium alloy and aluminum, and alloys or compounds formed by Al, Cr and Ni applied on turbine components comprises from 2 to 50 wt % chromium, from 0.1 to 6 wt % aluminum, and a remaining balance of nickel, wherein the Ni—Cr—Al composite is heat-treated to form an aluminum compound and to restore materials lost during repair processes of the turbine components.

Abstract: A nickel-chromium (Ni—Cr) alloy and a method for electrodepositing the Ni—Cr alloy on a turbine engine component for dimensionally restoring the engine component are described. The engine component is restored by re-building wall thickness with the Ni—Cr alloy including from 2 to 50 wt % chromium balanced with nickel. The turbine component coated with the Ni—Cr alloy is heat-treated at a high temperature to homogenize composition of the alloy to mimic the base alloy and to restore materials lost during repair of the turbine component.

Abstract: Aspects of the disclosure are directed to a servicing of an airfoil of an aircraft engine. A first portion of a first bondcoat layer may be removed from the airfoil while leaving a second portion of the first bondcoat layer intact on the airfoil. A second bondcoat layer may be applied to the airfoil using a coating technique subsequent to the removal of the first portion of the first bondcoat layer.

Abstract: Systems and techniques are disclosed for removing contaminants from a surface of a thermal barrier coating (TBC) and, optionally, estimating the remaining lifetime of the TBC. Laser induced breakdown spectroscopy (LIBS) is one method that may be used to remove contaminants from a surface the TBC prior to performing photo luminescence piezo spectroscopy (PLPS) or another spectroscopic technique on a thermally grown oxide (TGO). LIBS may facilitate monitoring substantially in real-time the chemical composition of the material removed. LIBS may be used to remove substantially only the contaminants with minimal effects on the underlying TBC. One technique for determining when to stop removal of material from the TBC is cross-correlation between a spectrum collected from the ablated material and a reference spectrum collected from a reference substrate. In some embodiments, the same system may be used to perform LIBS to remove impurities and PLPS to measure stress in the TGO.

Abstract: In one form a maintenance device includes a flexible member with an inspection end sized to be inserted through an inspection port of a workpiece such as a gas turbine engine or a blade of a gas turbine engine. The maintenance device includes a directed energy member that in one form is configured to produce a double pulse laser with an interval time between a first one of the pulses and a second one of the pulses greater than the time of either the first one of the pulses or the second one of the pulses. The first one of the pulses is sufficiently powerful to produce a quantity of debris upon irradiation of the workpiece. The debris produced from the first one of the pulses can be evaporated by the second one of the pulses to eliminate and/or reduce a recast layer on the workpiece.

Abstract: Systems and techniques are disclosed for removing contaminants from a surface of a thermal barrier coating (TBC) and, optionally, estimating the remaining lifetime of the TBC. Laser induced breakdown spectroscopy (LIBS) is one method that may be used to remove contaminants from a surface the TBC prior to performing photo luminescence piezo spectroscopy (PLPS) or another spectroscopic technique on a thermally grown oxide (TGO). LIBS may facilitate monitoring substantially in real-time the chemical composition of the material removed. LIBS may be used to remove substantially only the contaminants with minimal effects on the underlying TBC. One technique for determining when to stop removal of material from the TBC is cross-correlation between a spectrum collected from the ablated material and a reference spectrum collected from a reference substrate. In some embodiments, the same system may be used to perform LIBS to remove impurities and PLPS to measure stress in the TGO.

Abstract: In one form a maintenance device includes a flexible member with an inspection end sized to be inserted through an inspection port of a workpiece such as a gas turbine engine or a blade of a gas turbine engine. The maintenance device includes a directed energy member that in one form is configured to produce a double pulse laser with an interval time between a first one of the pulses and a second one of the pulses greater than the time of either the first one of the pulses or the second one of the pulses. The first one of the pulses is sufficiently powerful to produce a quantity of debris upon irradiation of the workpiece. The debris produced from the first one of the pulses can be evaporated by the second one of the pulses to eliminate and/or reduce a recast layer on the workpiece.

Abstract: A improved thermal barrier coating and method for producing and applying such is disclosed herein. The thermal barrier coating includes a high temperature substrate, a first bond coat layer applied to the substrate of MCrAlX, and a second bond coat layer of MCrAlX with particles of a particulate dispersed throughout the MCrAlX and the preferred particulate is Al.sub.2 O.sub.3. The particles of the particulate dispersed throughout the second bond coat layer preferably have a diameter of less then the height of the peaks of the second bond coat layer, or a diameter of less than 5 .mu.m. The method of producing the second bond coat layer may either include the steps of mechanical alloying of particles throughout the second bond coat layer, attrition milling the particles of the particulate throughout the second bond coat layer, or using electrophoresis to disperse the particles throughout the second bond coat layer.

Abstract: A improved thermal barrier coating and method for producing and applying such is disclosed herein. The thermal barrier coating includes a high temperature substrate, a first bond coat layer applied to the substrate of MCrAlX, and a second bond coat layer of MCrAlX with particles of a particulate dispersed throughout the MCrAlX and the preferred particulate is Al.sub.2 O.sub.3. The particles of the particulate dispersed throughout the second bond coat layer preferably have a diameter of less then the height of the peaks of the second bond coat layer, or a diameter of less than 5 .mu.m. The method of producing the second bond coat layer may either include the steps of mechanical alloying of particles throughout the second bond coat layer, attrition milling the particles of the particulate throughout the second bond coat layer, or using electrophoresis to disperse the particles throughout the second bond coat layer.

Abstract: A coating for protecting titanium aluminide alloys, including the TiAl .gamma.+Ti.sub.3 Al (.alpha..sub.2) class, from oxidative attack and interstitial embrittlement at temperatures up to at least 1000.degree. C. is disclosed. This protective coating consists essentially of titanium, aluminum, and chromium in the following approximate atomic ratio:Ti(41.5-34.5)Al(49-53)Cr(9.5-12.

Abstract: A diffusion barrier to help protect titanium aluminide alloys, including the coated alloys of the TiAl.gamma.+Ti.sub.3 Al (.alpha..sub.2) class, from oxidative attack and interstitial embrittlement at temperatures up to at least 1000.degree. C. is disclosed. The coating may comprise FeCrAlX alloys. The diffusion barrier comprises titanium, aluminum, and iron in the following approximate atomic percent:Ti-(50-55)Al-(9-20)Fe.This alloy is also suitable as an oxidative or structural coating for such substrates.

Abstract: An oxidation resistant coating for titanium alloys and titanium alloy matrix composites comprises an MCrAlX material. M is a metal selected from nickel, cobalt, and iron. X is an active element selected from Y, Yb, Zr and Hf.