Abstract: The present invention relates to a system used for inspecting the position of a compressor rotor within a compressor rotor case. A compressor rotor blade is moved about the rotor blade path of the compressor rotor case, a probe holder attached to the rotor blade has a scanning device as part of the holder used for gathering information relative to the compressor rotor case. A fixture attached to the compressor rotor gathers information about the position of the compressor rotor with respect to the compressor rotor case to determine the relative position of both the compressor rotor in relation to the compressor rotor case.

Abstract: A method for securing, in an opening, an insert or a helical coil, comprising means for fusing the coil, wherein fine laser welds are provided, in an individual or overlapping pattern added, on one or more than one turns of the coil.

Abstract: The present invention relates to a thin impermeable top coat on a thermal barrier coating for a metal part, such as a turbine blade, wherein the composite thin top coat is porous, inert, non-sacrificial, less permeable ceramic layer that eliminates the infiltration of environmental contaminants into the thermal barrier coating during operation of the metal part, thereby extending the life of the underlying thermal barrier coating and metal part thereunder.

Abstract: The effective flow area of a restriction in a gas flow passage, such as that of a gas turbine nozzle or vane, is determined by use of a large reservoir containing pressurized gas which is discharged through the passage in a blowdown operation in which the ratio of back pressure of the restriction to gas pressure in the reservoir is maintained below critical for sonic flow; a timer may be used to measure the time for a predetermined fall of pressure in the reservoir whilst there is sonic flow through the restriction.

Abstract: An improved gas turbine engine diagnostic system is disclosed which is particularly adapted for direct measurement of compressor performance, including efficiency and mass flow, for aircraft engines, without having to remove the engine form the aircraft. The system includes an instrumented compressor air discharge tube which has probes for total pressure, static pressure and temperature. The instrumented air discharge tube may be substituted for an existing air discharge tube for the engine to be tested, without having to remove the engine. Transducers attached to these probes provide signals which are connected to a data recorder or computer. Data can be taken as the engine is run, either on ground test or flight test. The total mass airflow output from the compressor stage for various engine performance settings can then be calculated using the static pressure, total pressure and air temperature measurements.