Gas-Turbine Engine Testing TRIZ Cases

Replicates defects on a coated substrate to calibrate infrared thermography, resolving measurement precision versus device complexity.

A rotary table part measuring kit calculates calibration offsets using an artifact with known dimensions to correct measurement data.

A method determines turbine engine part service life by integrating average damage over time based on evolving wear and stress patterns.

An articulated multi-axis inspection scope automates camera positioning within gas turbines to capture internal component images without manual intervention.

Segmented probe struts attach to inlet cases without removing the engine, resolving installation complexity that reduces testing efficiency.

A real-time diagnostic system processes sensor data through a physics-based aero-thermal model to calculate engine parameters at non-instrumented locations.

Hub units condition analog sensor signals near the engine before transmitting digital data to remote processing units.

Deforming a swage collar on the turbocharger shaft eliminates assembly variability and unbalance migration under thermal loads.

A wireless engine monitoring system collects and transmits real-time aircraft engine performance data using onboard sensors and a local network.

A fuel injection system selects a metering unit channel based on flowmeter reliability to maintain stable operation.

A monitoring method processes thrust settings via a filtering function and transient-phase model to derive modeled thrust for real-time comparison.

Automated optical inspection scopes navigate pre-designed paths to reduce maintenance cycles and prevent internal component damage.

A model-based estimator uses biased engine speed to detect torque-related faults in gas turbine engines.

A geared turbine thrust measurement system uses force sensors on the annulus gear to determine fan torque and calculate thrust directly.

A rigid guide pipe orients a flexible borescope between turbine blades, enabling clear serial number identification without engine disassembly.

A non-contact magnetic excitation system uses movable magnets to apply precise forces to rotating test pieces without physical contact.

Segmented locks with transcowl sensors detect displacement to prevent unintended deployment during landing.

Pitot tubes measure gas stream pressure and temperature at multiple axial positions within an axial turbomachine.

Automated inspection system captures component images to determine material loss, preventing unnecessary scrapping of serviceable parts.

Gamma scintigraphy measures rotor kinematics through stators, reducing design conservatism and mass.

A turbine vane thermal barrier coating test system combines high-speed rotation with environmental simulation to detect real-time damage evolution.

Segmented annular regions in the turbine hub form a double pivot that isolates centrifugal deformation, preserving shaft clamping at high rotational speeds.

Computational modeling of shaft parameters determines precise balancing corrections to resolve manufacturing defects and tolerances in gas turbine engines.

A monitoring system builds efficiency maps to track component degradation using an adaptive tabulation algorithm.

A rotor balancing method uses influence runs to determine optimal weight placement on correction planes.

Fast Fourier Transform analysis of filtered dynamic pressure signals predicts compressor stall and surge, providing lead time for corrective control actions.

A gas turbine engine gearbox drives the fan at lower rotational speed than the core shaft to shift noise frequencies.

Wireless portable housing transmits real-time endoscope data to remote terminals, eliminating travel delays and enabling immediate expert diagnostics.

System computes inlet flow effective area and fouling rates to predict blockage before revenue losses occur.

RF tags on turbine rotor blades measure arrival time via signal time-of-flight, eliminating expensive mechanical probes and air cooling infrastructure.

A temperature compensation module adjusts signals from rotor-mounted wiring, enabling accurate dynamic pressure measurements despite extreme thermal conditions.

Sealing assemblies accommodate thermal growth between turbine structures, enabling accurate position detection despite relative movement.

Microphones acquire acoustic energy from gas turbine core paths to detect non-normal conditions via reference data comparison.

Segmented filtration with flow straighteners removes pollutants while maintaining stable airflow and minimizing pressure drop across the test bench.

A variance model qualifies gas turbine components using representative parameter profiles and Gaussian process regression.

A test facility generates steep thermal gradients across thin-walled components using high mass-flow fluid and internal impingement cooling.

Segmented sensors and a processor differentiate particulate types and sizes to detect accumulation, preventing performance degradation from ingested debris.

A gearbox decouples fan and core shaft speeds, reducing take-off EPNdB by 7-30 units while maintaining thrust.

Automated system correlates operational parameters across multiple rotary machines to identify potential causes of component conditions.

A controller adjusts proportional and integral gains using scheduling parameters to calculate null current values for position actuation systems.

A magnetic sensor system replaces frangible links with flux-based detection, eliminating false alarms from temperature variations and wear.

Segmented rails guide a maintenance head along the core air flowpath, eliminating skewed angle views and inconsistent documentation during inspections.

An integrated electrostatic sensor merges the amplifier within the housing to detect airborne particulates in engine environments.

Replacing time-consuming water and airflow checks, the sleeve detects temperature differences on a cover surface to verify cooling hole operation.

A ductility exhaustion module calculates remaining useful life for gas turbine components by combining fatigue and creep strain rates.

Pre-dressing unit uses integrated guide and lock mechanisms to connect instruments before engine entry, reducing test cell downtime.

Applying a resistance load to the core shaft replicates fan forces, enabling separate calibration of engine modules and eliminating full assembly requirements.

A gas turbine engine signal processing method uses current readings and previously calculated averages to remove sensor noise.