METHOD FOR DIAGNOSIS OF TECHNICAL STATE aviation gas turbine engines

摘要

1. A method for diagnosing the technical condition of aircraft gas turbine engines, comprising a test to produce defect-free CCD resource them at steady state operation and variable modes of operation in time measurement fields gas dynamic flow conditions across the nozzle outlet area, the creation of a data bank as fields cartograms that correspond to defect-free elements of a flowing part TBG, calculation engine thrust and a bank of engine thrust data R, sequential introduction of specific defects in sensible elements of the hydraulic system and measurement fields of gas-dynamic flow parameters - P * total pressure, static pressure P and temperature T * flow across the nozzle exit area for the same engine operating conditions, the establishment of a data bank as fields cartograms that correspond to these defects and Bank data calculated values ​​of engine thrust R, metering fields gasdynamic flow parameters P *, P, T * newly diagnosed or in the process of operation of engines across the nozzle exit area and thrust calculation values ​​respectively motor, comparing them with the fields of gas-dynamic flow parameters and calculated values ​​of the thrust reference Engine respectively under the same operating conditions and therefore of-life, which is judged to reject the gas dynamic parameters of the flow and thrust of the diagnosed engine from the reference, if the deviation is compared field cartograms gasdynamic parameters flow and thrust of the engine with gas-dynamic parameters cartograms fields and traction motors defective, which define specific