Gas-Turbine Engine Testing TRIZ Cases

Connector-stored sensor setup and calibration data let a lightweight recorder capture and wirelessly transfer vehicle monitoring signals with less hardware.

Reads sensor setup and calibration data from the connector to cut monitoring weight, fuel use, and deployment time.

A rotor-mounted laser and inclinometer measure fan blade tip clearance around the casing without removing blades or spinner cones.

Air-film and water-cooled housing keeps an eddy current sensor stable for accurate aircraft engine fatigue crack monitoring at 600°C.

A conductive layer and blade drain triboelectric charge from a pressure measuring rake, protecting sensor accuracy and data communication.

Fused steady and unsteady pressure sensors help a measuring rake track non-stationary aerodynamic variations in aircraft engines.

A handle-mounted grip secures the implement for single-handed use, reducing movement and helping capture clear images in confined spaces.

Pressure simulation and inlet sensors verify actual icing at a turbine engine intake, reducing false shut-downs during engine testing.

A handle-mounted grip mechanism secures the implement for one-handed use, improving stability and image clarity in confined inspections.

Computer-selected circumferential rotor positions create a bow-shaped mass layout that cuts vibration and improves acceptance test compliance.

A segmented bushing, flange, spacer, and locking screw stabilize blade tip clearance sensing under high heat, pressure, and vibration.

A sliding Inconel cooling sleeve and moving probe holder keep the BTT probe stable during casing thermal expansion and blade vibration monitoring.

Passive ducts and pre-swirl vanes shape inlet airflow to mimic flight conditions, reducing propeller stall during ground engine testing.

AI-based virtual sensors infer shock waves, Mach number, and pressure where physical sensors degrade, improving predictive maintenance.

A segmented bushing, washer, flange, and locking screw stabilize and cool the probe for reliable blade tip clearance sensing in turbines.

A sliding cooling sleeve keeps the BTT probe fixed to the vane carrier while absorbing casing thermal expansion and mechanical stress.

Integrated sensor electronics digitize aircraft engine measurements near the source, cutting cable complexity, disturbances, and bench assembly effort.

Pressure and temperature differences between upstream and downstream plenums reveal bleed offtake status without pipe-level sensors, cutting weight and maintenance.

A collinear light source, beam splitter, and sensor fit through one fan-case opening to inspect blade damage with minimal gas-flow disruption.

A shared-axis light source and sensor fit through one fan-case opening to detect blade damage while minimizing gas flow disturbance.

A monolithic tube-flange manifold uses a labyrinth path and heat exchange to stop hot-air leakage and protect pressure sensing accuracy.

Testing liquid is circulated through aircraft engine oil nozzles to measure flow resistance and detect coking blockages without disassembly.

Multiple images captured during rotor rotation flag suspect blades early, enabling targeted follow-up inspection and less wasted inspection time.

A combined field and optical probe measures blade tip clearance and time of arrival in one housing, improving accuracy without extra probes.

Multi-band wavelet networks denoise aeroengine signals across variable working conditions to improve anomaly detection accuracy and robustness.

A gaseous-coolant jacket and collar protect blade tip clearance probe leads from conductive heat, oxidation, and electrical failure.

Backscattered light and Doppler analysis detect contrail formation in engine exhaust, helping flight planning avoid persistent climate-warming trails.

Optical 3D scanning builds complete bladed rotor models for condition analysis, automated repair planning, and service life extension.