Gas-Turbine Engine Testing TRIZ Cases

A remote monitoring unit analyzes operating parameter snapshots from turbine engines to detect compressor surge events.

Digital part grading system standardizes wear assessment accuracy by replacing subjective manual inspection with automated image analysis protocols.

Virtual sensors on a digital twin replicate physical asset forces to enable real-time damage assessment without additional hardware.

A tip clearance measurement system uses shared RF circuitry to process microwave signals for turbine blade monitoring.

Underground cavern storage decouples test duration from facility footprint, eliminating the need for large compressors during operation.

An integrated thermoacoustic system uses acoustic pyrometry to monitor gas turbine combustor temperatures in real time.

A configurable controller segments sensor inputs to reduce false alarms in gas turbine engines while minimizing inspection time.

Data acquisition system calculates fatigue severity factors from operating parameters.

A wireless engine monitoring module collects and transmits real-time aircraft engine data using onboard processing.

Segmented sensors and a processor differentiate particulate types and sizes across engine zones to prevent component damage from accumulation.

A non-contact dynamic strain field measuring system reconstructs blade surface strains using tip timing sensors and finite element models.

A shroud surrounding a turbomachine creates an annular air flow to replicate flight aerodynamic conditions during ground testing.

Thermal imaging camera analyzes fluid exit patterns to identify misaligned or blocked cooling holes, resolving inspection complexity and time losses.

A turbine flow sensor employs a rubberlike stud contacting the inner wall to reduce vibratory issues and prevent damage during aerodynamic measurements.

Fiber optic sensors measure acceleration and strain at specific radial positions on wind turbine rotor blades to calculate stiffness values.

A combustion test rig housing features transparent windows for optical access to the internal combustor section.

An inspection apparatus uses an extendible shaft to guide sensors into gas turbine ports for automated remote operation.

Auxiliary turbine inlet directs compressor discharge air to drive the rotor, recovering stored energy without external propellant.

An automated maintenance system for gas turbine integrally bladed rotors uses reduced order vibration models to determine blade conditions.

A turbine engine shaft uses combined reference and measurement teeth to detect rotational speed and torque simultaneously via inductive sensors.

Processor-based turbine control system adjusts inlet guide vane gains to manage firing temperature during load path transitions.

Multiple circumferential sensors on a biased flexible sheet inspect round holes, eliminating complex single-sensor manipulation.

A laser probe assembly redirects a beam onto multiple targets on rotating parts to measure local maximum deflections.

A compliant layer mitigates thermo-mechanical forces between a conformal electronic device and a ceramic substrate.

Portable diagnostic unit automates electrical tests via a single cable interface, eliminating disassembly and reducing maintenance errors.