Engine Manufacture TRIZ Cases

Horizontal conduits near the silencer downstream end mix heated and ambient air in the inlet system.

Interwoven micro-channels direct cooling air through exhaust ports at shroud edges, reducing hot spots and erosion while lowering total air consumption.

Segmented rotor blades with higher outer crown airfoil counts increase peripheral solidity while reducing centrifugal stresses on the blade structure.

Pressure relief dimples on a gas turbine damper ring lower contact pressure to prevent frictional locking under centrifugal loads.

A turbine ring assembly uses an elastically deformable flange to hold ceramic matrix composite sectors in position.

An inverted track beam flange repositions attachment interfaces to increase noise cancellation surface area within aircraft nacelles.

A lifting bracket rigidly couples to a wind turbine generator transport frame to maintain precise alignment during the lifting operation.

Segmented Y-shaped ribs create distinct cooling channels that balance thermal stresses and reduce airfoil mass in gas turbine engines.

Varying the thickness-to-chord ratio along the vane span increases tangential stiffness and axial compactness while minimizing aerodynamic losses.

Radial channels in a reverse vortex ring reverse fluid pre-swirl to reduce vibrations and prevent rotordynamic instability.

Segmented shim cavity prevents radial wear during low-speed operation while easing assembly.

Variable coating thickness on a turbine tip prevents stress cracking while maintaining erosion resistance.

Axially oriented perforations minimize aerodynamic drag and skin friction while maintaining acoustic attenuation performance.

A flexible seal with a tapered fillet and rib section connects the vane to the liner through elastic crush.

A turbocharger adjusting device uses a two-part housing joined at multiple circumferential positions to reorient fluid and electrical connections.

Closed loop seal slots accommodate thermal expansion while internal cooling features manage heat in high temperature gas turbine environments.

Adjusting orbiting scroll rotation speed during radial spray nozzle movement to deposit uniform coating on spiral wrap side faces.

A quick release sling uncouples from a wind turbine rotor blade root end.

Tangential stacking offset curves minimize flow discontinuities and propulsive losses in gas turbine engines.

Transitional nozzle interfaces bridge angled and arcuate sidewalls, allowing individual segment replacement without damaging adjacent sections.

A turbomachine rotor blade root depression receives a protrusion with an elevation to narrow the gap.

A wind turbine blade leading edge fairing uses a projection received in a longitudinal channel to enable modular replacement of eroded sections.

A reverse core gas turbine engine configuration centers the core on a non-parallel axis to the fan for compact integration.

Clutch assembly in torque path decouples accessory drive from low speed spool to restore engine responsiveness.

Inclined strut portions guide combustion gas flow to minimize pressure loss, stabilizing fluid dynamics while reducing thermal stress on bearing supports.

Enlarged intermediate cooling hole sections accommodate thermal barrier coating deposition on gas turbine components.

Integrating fibrous straps into stacked carbon-fibre strips maintains alignment during resin infusion, reducing handling complexity for long blade components.

A rotatable blade cart provides adjustable support surfaces for wind turbine blades during post-molding operations.

Segmented bar arrangement with hinged extension beams resolves the contradiction between long reach distance and compact transport volume.

Corrugated longitudinal walls in a centrifugal degasser capture oil droplets while minimizing pressure losses caused by internal duct geometry.

Spaced inlet aperture extracts low-contaminant air via snorkel effect, reducing filter weight and maintenance costs.

Axial pile displacement on a buoyant platform simplifies installation, reducing equipment complexity and costs for deep-water foundations.

A laser alignment device projects beams between specific aids to set wind turbine rotor blade angles with high precision.

Iris mechanism occludes bypass duct airflow to redirect thrust, reducing weight and maintenance complexity of the thrust reverser system.

Longitudinal edge extensions modify wind turbine blade aerodynamics and provide rigidity, reducing costly leading edge maintenance.

Helical crossover passages connect internal airfoil cavities to enhance convective cooling while minimizing coolant pressure loss.

Merging deswirling struts with a wavy mixer reduces pressure losses while maintaining mixing efficiency.

Optimized tip rail surfaces and airfoil protrusions reduce aerodynamic losses and creep while managing mechanical loads.

Segmented additional webs in the spar enhance chord direction stiffness and adjust the center of elasticity to reduce vulnerability to chord forces.

A drilling method corrects hole position using measured wall thickness data.

Integrated core structure forms leading edge and tip cooling passages concurrently, resolving overheating without separate manufacturing steps.

Relocate the control cabinet to an uptower nacelle location during generator frame replacement, avoiding cable disconnection and reducing downtime.

Gear reduction system drives fan rotor at slower speeds while turbine rotors drive compressor stages.

External tower-mounted positioning elements guide wind turbine blades to align connection flanges, reducing crane requirements and assembly time.

Superposed sinusoidal waves on the aerofoil edge reduce broadband noise by canceling tone interference across wide frequencies.

A rotatable adjusting ring varies the overflow cross section between a volute and turbine wheel to control exhaust gas flow speed.

Recessed wear coats prevent high-temperature creep deflection and smearing on turbine blade tips.

Buoyancy chambers counteract hydraulic machine weight, enabling in-situ maintenance without dismantling heavy components from the water.

Disjointed internal walls reduce thermal gradients and stress in aviation turbine blades by enabling localized cooling zones.

Inclined discharge hole directs cooling air to turbine blade tip, resolving pressure loss and torque reduction trade-offs.