Blade Accessories TRIZ Cases

A milling assembly uses an electrode to remove ceramic coatings and machine metal substrates through electrochemical reactions.

A turbine rotor blade tip shroud features inclined surfaces and recessed contact blocks to distribute pressure.

A raised protuberance with a large cross-section rigidly secures upstream and downstream molding portions to form the blade trailing edge.

Orientable turbine blades allow external manual calibration, resolving inaccessibility issues and reducing manufacturing complexity.

A downhole transducer assembly converts drilling fluid kinetic energy into electrical power via radial flow through lateral sidewall turbines.

Local quality sleeves distribute high-speed fluid impact forces at shaft openings, reducing wear on turbine blades without adding significant weight.

A metal vapor infiltration method creates a concentration gradient within ceramic matrix composites.

Cantilevered lobes create low-pressure zones that produce thrust while eliminating slicing hazards for people and wildlife.

A guide blade design positions the axis of rotation along the profile chord to minimize vibration absorption.

A self-healing environmental barrier protects silicon carbide substrates using a rare earth silicate and manganese oxide coating.

A ceramic barrier layer with gettering particles limits oxidant exposure, extending gas turbine component longevity.

Replacing fiber fillers with ceramic particles creates pore networks that allow chemical vapor infiltration to reduce residual porosity.

Segmented elongated members in circumferential slots constrain gas turbine blade axial movement, reducing assembly friction and deformation risks.

A metallic leading edge shield covers composite fan blade airfoils and shanks to provide structural protection.

Optimizing upstream and downstream airfoil clocking relationships between 25% and 75% pitch reduces operational shaking and rocking stresses on target rows.

A holding ring and tactile measurement system centre turbine shafts relative to trunnions, avoiding hard contact risks during low-pressure module mounting.

Rare earth apatite phases prevent dopant leaching and maintain mechanical strength against CMAS erosion.

Segmented angular positioning enables precise repair of narrow recesses without removing stator blades, maintaining mechanical properties.

A gas turbine blade stalk uses a motion weld receiving surface to join the disk via friction welding.

Impact forging at high strain rates refines TiAl microstructure, reducing production time and cost while maintaining creep resistance.

Metallurgical bonding of a metallic retainer plate to a ceramic matrix composite vane enables reliable sealing against high temperatures, reducing air leakage.

Continuous fiber weaving eliminates stress concentration at joints while maintaining manufacturing flexibility and low production costs.

A nickel-based alloy composition with optimized chromium, cobalt, and aluminum content.

A turbine blade tip incorporates an abradable material bed to shield ceramic matrix composite airfoils from rubbing contact.

Alternating boron nitride and carbon layers deflect cracks and capture oxygen, preserving turbine component integrity under extreme heat.

A particle-infused binder coating method applied to specific turbomachine component areas.

Heat treatment method enhances low cycle fatigue strength of superalloy components through controlled solution treating and precipitation aging.

A grinding mechanism removes multi-layer coatings while a controller monitors vibration frequency to detect layer transitions.

A turbomachine rotor features a dovetail slot with a bulbous fillet region to reduce contact stresses during blade installation.

A C-shaped leaf spring holding device reduces plasticization and eliminates assembly asymmetry in turbomachine sealing systems.

Metallic liners pass through ceramic matrix composite turbine blades to convey ventilation air while matching thermal expansion coefficients.

A turbine blade tip shroud incorporates a pressure-side fillet with protrusions and locally reduced radial thickness regions to manage mechanical stress.

Hybrid CMC and monolithic ceramic sections resolve manufacturing complexity while raising gas turbine engine operating temperatures.

A segmented turbine bucket assembly uses a single-lobe joint to connect distinct airfoil segments made from different materials.

Segmenting the fan into multiple stages reduces total pressure loss and facilitates engine installation by increasing axial distance for flow redistribution.