Blade Accessories TRIZ Cases

Heat treatment and welding repair cracked gas turbine airfoils, restoring structural integrity while avoiding full component replacement costs.

Variable radius fillets in turbine blade growth pockets reduce stress concentrations and vibration interference, enabling accurate creep growth monitoring.

A composite airfoil spar tab embeds a surface pattern that mechanically locks to the ply structure during curing.

Dimensional constraints on the balance cut portion minimize crack formation in brittle titanium aluminide during rotational balance correction.

Central plies interweave around inserts to reinforce the narrowed neck region of ceramic matrix composite turbine blades.

Chemical vapor deposition creates thin, columnar silicon bond coatings that reduce mechanical stress and prevent failure in aggressive gas turbine environments.

A shroud relief area accommodates flowable attachment material to secure a gas turbine vane lug without obstructing the airfoil.

Electrolytic deposition coats airfoil internal passages with chromium and aluminum layers for high-temperature protection.

Plenum chamber directs cooling air through exit holes on the rear overhang portion, preventing thermal barrier coating shedding and blade failure.

Hooks engage attachment tabs to support an abradable ring on a CMC nozzle, accommodating thermal expansion without fastening.

Central channels supply cooling air through crossover holes to impinge against core channel walls.

Extracted seal teeth and notched fins reduce hoop stress while a separate base structure blocks crack propagation into the shaft.

Optimized rotor disk geometry and microstructure resolve the trade-off between power density and structural integrity at high temperatures.

A flow discourager redirects ingestion gas away from module joints to minimize wear.

A composite component uses a fracture inducing layer to create controlled failure zones within the structure.

Top and side plies on a ceramic matrix composite shank create an angel wing and skirt that inhibit hot gas ingestion while reducing weight.

A rotor blade design encloses a fiber composite part within a metallic shell to shield the material from media influences and mechanical impacts.

Additives stabilize beta-cristobalite in a silica matrix, reducing volumetric changes during thermal cycling to prevent microcrack formation.

Minimizing rotor assembly unbalance by calculating optimal stacking positions from measured concentricity and parallelism deviations.

Segmented fiber preforms with varied orientations mechanically attach to damaged areas, resolving the trade-off between repair ease and delamination resistance.

An abrasive coating on rotating blade tips reduces high-temperature leakage by abrading the stationary abradable layer.

A shaped rim cavity wing uses a geometric lower surface to control airflow separation and create re-circulation.

A reactor vessel generates swirling precursor gas flow around a central core region to enhance temperature uniformity and deposition homogeneity.

Orthogonal blocking wedges secure composite rotor blade roots, resolving axial retention challenges caused by differential thermal expansion.

An adjustable holding device supports the outer guide ring against warping during riveting, ensuring precise alignment of guide vanes to the inner ring.

Multi-stage vapor deposition resolves gas flow restrictions in thick-wall CMC structures to achieve high structural integrity.

A niobium-molybdenum-titanium alloy incorporates controlled nitrogen to enhance structural strength and ductility.

Integrating guide vanes with structural spokes eliminates inlet bifurcations, reducing axial length and device complexity.

Modular segmentation of gas turbine sections allows selective disassembly, reducing maintenance time and costs.

A turbine engine guide bearing forms a ball joint link to enable relative angular displacement between the power gear box shaft and turbine shaft.

Vane-mounted stationary seals compress against shroud segments to eliminate gas flowpath leakage and protect casing components from high temperatures.

A bi-layered electroless nickel-phosphorous coating protects turbocharger blades from water droplet erosion caused by exhaust gas recirculation systems.

A steam turbine rotor blade thinning management apparatus calculates past and future erosion levels based on measured data and operating conditions.

Mechanical tenon attachment prevents brazing cracks in turbine vane roots, maintaining cooling channel integrity while lowering manufacturing costs.

A wicking layer extracts boron and other impurities from ceramic matrix composites, improving oxidation resistance without adding complex diffusion barriers.

A platform mouth portion defined by inner and outer wings retains a segmented coverplate against the disc.

Cross-passages in turbomachine vanes heat leakage flows via convection, converting harmful gas loss into beneficial thermal energy for component protection.

A non-axisymmetric flow contour feature extends from gas path surfaces into turbomachine wheelspaces to alter local pressures and prevent hot gas ingestion.

Pre-formed edge plate grooves channel welding gas to prevent blow holes on the repaired turbine rotor disc surface.

Surface channels and ridges interlock with silica layers to inhibit creep displacement under high-temperature shear loading.

Segmented internal ribs accommodate thermal expansion in gas turbine airfoils, reducing structural stress while maintaining cooling efficiency.

Laser-assisted chemical vapor deposition repairs eroded ceramic composites by depositing matching matrix material, extending component lifespan.

Larger diameter pins and bores in pinned root fixings reduce peak stresses in disc fingers, mitigating stress corrosion cracking risks.

Adaptive machining compensates for core deformation during casting to produce precise cooled turbine airfoils.

A tool system positions masking plugs over surface features using a channel and rotational motion.

Nitriding silicon particles creates a diffusion barrier that prevents oxygen degradation in ceramic matrix composites.

Sealing strips in opposing grooves block gaps between rotor-side heat shields, preventing cooling air leakage and hot gas intrusion.

A turbomachine blade cover includes a gap between attachment surfaces to facilitate thermal expansion during welding and operation.

A turbine blade dimple initiates fracture at predetermined speeds to prevent rotor disk rupture during overspeed events.

A vane arc segment features axially-sloped circumferential mate faces and a projecting flange to transmit aerodynamic loads efficiently.