Blade Accessories TRIZ Cases

A steam turbine uses a speed-adjusting impulse stage and medium-pressure stages with optimized reaction degrees to improve energy utilization.

Segmenting the trailing edge into a rigid ceramic insert and wrapping CMC plies prevents fiber damage during manufacturing.

Segmented sealing elements accommodate differential thermal expansion between CMC blades and discs, reducing centrifugal load on platforms.

A turbine vane reconfiguration system applies controlled mechanical loads to straighten distorted airfoils at room temperature.

Cutting mechanisms sever turbine blades from the rotor disk upon disengagement, eliminating combustion gas driving force and preventing structural failure.

Controlled flow guides reduce wetness losses by 20% and enhance dry stage efficiency through optimized pitch-to-width ratios.

A dual-layer rare earth silicate coating protects ceramic matrix composite substrates through a segmented microstructure.

Blade leading edge foot alignment minimizes cross-passage secondary flow and reduces aerodynamic losses in gas turbine engines.

FeCrAlY alloy lining resists oxidation in turbomachine components, reducing manufacturing costs compared to ceramic coatings.

A turbine vane apex features curved pressure and suction walls to create a boundary layer that minimizes the gap between the vane and engine case.

Dual-sleeve vanes vary cooling air flow through differential thermal expansion, reducing compressor bleed air intake during low-temperature operations.

Stable porous oxide layers reduce recession rates by an order of magnitude, enabling operation above 1482°C.

A perforated rigid element balances injection pressure during slurry infusion, preventing macropore formation from uneven liquid withdrawal.

Variable thickness shroud walls enable customized blade-gap zones at the exducer, resolving adaptability versus manufacturing precision trade-offs.

Adjustable guide vanes and semi-axial inflow configurations minimize exhaust gas flow losses to improve low-speed power output.

Segmented inner band repair reduces joint count and complexity while maintaining load-carrying stability and fluid flow control.

A current-limiting power controller supplies electrical energy to resistance heating elements for localized gas turbine component treatment.

A dual-layer mask composition protects gas turbine chromide coatings during aluminizing processes.

Optimizing the solidity ratio of a first stage turbine nozzle improves durability against high thermal loads while maintaining energy extraction capability.

Intermediary seals bridge segmented shroud gaps to stop combustion gas leakage and maintain hot gas path integrity.

A compressor transition duct with a radially inward outlet reduces downstream rotor blade tip speed and mechanical stress.

Dissimilar cobalt and nickel hardcoatings on gas turbine blade shrouds prevent galling from vibration-induced deflections while maintaining wear resistance.

A thermoplastic covering element drapes over the trailing edge of a composite vane to eliminate square protrusions and reduce machining costs.

Austenitic stainless steel composition for turbocharger exhaust guide members provides high-temperature strength and oxidation resistance.

A sintering-aid free coating system with a composition gradient of rare earth disilicate and monosilicate layers.

Three-dimensional weaving of continuous fiber strips creates complex composite preforms densified by chemical vapor infiltration.

Integrated body bearing recesses eliminate separate panels to reduce manufacturing costs and prevent structural deformation during assembly.

Hydroxide-based chemical etching selectively dissolves barrier coatings on ceramic matrix composites, preventing substrate damage during maintenance.

A three-dimensional fibrous texture places aramid fibers in a reinforced zone to improve impact resistance against environmental damage.

Pyrolyzed organic binder residue reduces silica layers on SiC particles, enabling molten silicon infiltration into thick parts.

A cross-linkable coating composition cures at temperatures below 70°C using polyaldehyde and acrylic polycarbamate.

Sacrificial fibers define cooling channels within ceramic matrix composite filler packs, avoiding line-of-sight drilling damage.

Ceramic matrix composite casings reduce fuel consumption by replacing heavy metal components with lighter, segmented structures joined via brazing.

A two-layer thermal barrier coating system applies a porous pyrochlore reinforcement layer locally to turbine blade airfoils.

Recesses channel purge air away from leading edges to prevent pressure side horseshoe vortices, reducing mixing losses in gas turbine engines.

Dip-coated thermocouple layers on turbine blades mitigate thermal stress and prevent cracking, ensuring reliable temperature measurements.

Pyrolyzed surface coating on ceramic matrix composite fiber preforms creates a silicon carbide barrier layer.

Dual-layer spacers dissipate bird strike energy via elastic deformation, protecting fan blades while simplifying manufacturing complexity.

Metallic reinforcement spars transfer aerodynamic loads from ceramic airfoils, resolving thermal durability versus strength trade-offs.

Integrating an elastomeric flexible portion into the cover eliminates sliding seals, preventing cooling air leakage and condensation accumulation.

Keeper collar stand-off legs secure ceramic matrix composite blades, reducing cooling air usage and weight.

A hybrid ceramic matrix composite turbine blade combines chemical vapor infiltration and melt infiltration processes to form distinct component portions.

A dual alloy gas turbine blade uses a high chromium layer on the root and lower surface to prevent corrosion fatigue.

Polyoxyalkyleneamine-based curing compositions extend pot life and reduce exothermic heat release during wind turbine blade assembly.

A pump rotor deforms reversibly between compressed and expanded states using elastic recovery.

Blade shank deflector redirects hot gas flow over spacer surfaces to protect turbine wheel spaces from thermal damage.

A cool side coating on ceramic matrix composite substrates melts to seal through-orifice damage caused by water vapor recession in gas turbine engines.

Sintering process yields precise vanes without machining, eliminating post-processing costs.

Negative slope leading edges on low pressure compressor airfoils reduce downstream turbulence and losses in geared turbofan engines.