Blade Accessories TRIZ Cases

Variable shroud extensions separate torsional frequencies in turbomachine blades, reducing fatigue failure risk from aeroelastic instability.

Metallic shroud cap on ceramic tip shroud maintains interlock load despite low thermal expansion of composite blades.

Shaftless magnetic turbine integrates electric control and ceramic components for hypersonic flight.

Machining internal cooling channels into a porous trailing edge structure to increase surface area for heat exchange.

Titanium-based braze alloys repair superalloys without boron or silicon, preventing ductility loss and carbide formation during structural repairs.

A nickel-based alloy with specific aluminum and tantalum levels forms a protective oxide scale.

Segmenting the lock body allows reducing circumferential groove width without compromising screw diameter, enabling lighter and shorter turbomachine wheels.

A variable inlet guide vane device uses a coaxial disc and annular member to mount pivotally adjustable vanes for turbomachines.

Static labyrinth seal channels inject secondary air between seal lips, reducing excessive cooling air extraction and improving turbine blade thermal management.

A pi-shaped insert anchors three-dimensional woven fiber reinforcement to resolve insufficient mechanical strength at the platform attachment points.

Multi-stage axial turbine applies partial admission across stages to reduce blade profile complexity and manufacturing costs.

Applying a MAXMET composite coating to aluminum fan guide vanes resolves the weight versus vibration resistance trade-off by dissipating mechanical energy.

Columnar silicon grains prevent oxygen penetration and delamination, enabling ceramic components to withstand higher operational temperatures.

A carbon-sink intermediate layer reacts with free carbon to form stable carbides within ceramic composite structures.

A self-biased lock lug system secures rotor blades within a gas turbine engine rim slot using an engagement mechanism that moves between assembly and engaged positions.

Low expansion ceramic matrix composites self-regulate dimensional changes in gas turbines, eliminating heavy active clearance control mechanisms.

Silicon carbide facecoat resists chemical reaction with molten titanium alloys during casting.

A lightweight leaf spring spacer prevents unwanted radial movement and tilting of fan blade roots during windmilling, reducing assembly complexity.

A sealing member fills gaps between adjacent rotor blades, preventing cooling air leakage and improving engine efficiency.

A ceramic composition uses a healing activator to accelerate oxidation diffusion of non-oxide agents for rapid crack repair.

Reducing exit guide vane stagger angles below 15 degrees minimizes shock losses while maintaining airflow control reliability.

Adaptive machining corrects dimensional deviations between scanned insert geometry and CAD data, restoring mechanical stability.

A segmented retainer ring axially retains turbine cover plates without modifying the rotor body.

Link plates join composite blade sections to reduce component count and simplify assembly.

Low-temperature ionic liquid electroplating prevents substrate embrittlement while maintaining oxidation resistance.

Segmenting the fan inlet case into a permanent backbone and replaceable shell members reduces erosion repair costs while maintaining structural integrity.

Segmenting the repair into a welded attachment zone and a weld-free shroud zone prevents thermal damage and brittleness during leading edge restoration.

A multi-shaft assembly employs an ablatable metallic alloy overlay with a radial air gap to mitigate rubbing-induced overheating in gas turbine engines.

Equilibrium partial pressure prevents solvent evaporation during slurry infiltration, reducing residual porosity in ceramic matrix composites.

Curved dovetail necks reduce stress concentrations without increasing weight, preventing premature failure in gas turbine engines.

Transition buckets with mixed lateral edge configurations slide into place, eliminating interference between adjacent covers during assembly.

Uneven axial chords in an integrated strut-vane nozzle prevent flow constriction and separation, reducing static pressure gradients and engine length.

A wax injection mould core assembly uses rod portions housed in slots to maintain precise relative positioning of multiple core elements.

Curved slot and dovetail ends reduce stress concentrations from centrifugal forces, improving mechanical integrity in gas turbine engines.

A composite coating layer combines rare-earth disilicate and monosilicate to protect ceramic matrix composites.

Inflatable bladders create retention surfaces for sealing material, resolving the contradiction between assembly speed and consistent joint quality.

Fugitive fiber oxidation creates matrix-rich regions that interrupt weak interfaces, boosting interlaminar strength and fracture toughness.

A specialized apparatus displaces turbine buckets from wheel slots using a linear actuator and engagement arm.

Segmented rotor assembly with axially offset disk and bladed ring reduces strain range on gas turbine components without extracting cooling airflow.

A rare earth disilicate environmental barrier coating incorporates specific molar proportions of a secondary rare earth oxide to enhance diffusion resistance.

A variable throat nozzle assembly adjusts flow capacity through selective fluid injection into exhaust holes.

A normalized chord distribution on a booster rotor blade manages endwall meridional velocity deficits to improve stability and efficiency.

A diffuser strut fairing injects compressed fluid through suction side openings to enhance boundary layer energy.

Electrical discharge machining with a replica tool restores worn blade tip pockets, reducing repair time and cost compared to welding.

Heating fibrous preforms above the sizing softening temperature enables flexible shaping without water lubrication.

Automated fiber placement layers prepreg plies on ceramic matrix composite mandrels while measuring intermediate weight to adjust material deposition.

Asymmetric scallop cuts on the partial back wall balance the mixed flow turbine wheel while preserving structural integrity against centrifugal stress.

Segmented seals with curved profiles engage airfoil bodies under pressure gradients, reducing secondary airflow leakage and improving turbomachinery efficiency.

Burnished compressive stress layer and composite wear covering prevent cracking in gas turbine fan blades.