Blade Accessories TRIZ Cases

A reservoir design captures molten weld material to alleviate thermal stress and prevent deformation in welded shaft turbine wheel assemblies.

Differentiated curvature radii on rotor blades flatten the exit pressure ratio profile, reducing wake interactions and noise while maintaining fuel efficiency.

Isolation trenches segment flow paths to prevent coolant blow-off, maintaining uniform film coverage on turbine blade airfoils.

A temporary support pedestal positions turbine nozzles between rotor buckets during assembly.

Strategic unfinished airfoil regions trigger early turbulence, resolving laminar separation and pressure loss at shock interfaces.

Hybrid metallic frameworks stabilize low-strength ceramic vanes against twisting, reducing gas path leakage.

An intermediate coating containing hafnium disilicide reacts with thermally grown oxide layers to inhibit growth and reduce thermal stresses.

A slurry formulation delivers reactive element halides to turbine blade surfaces for controlled diffusion into aluminide layers.

A steam turbine rotating blade features a skewed axial entry dovetail and an angled tip cover with flat and depression sections.

A seal assembly flow-through tube directs conditioning airflow through an annular body to rotor assemblies, resolving temperature management trade-offs.

Sol-gel adhesion promoters bond directly to abraded substrates, eliminating complex surface preparation steps while maintaining reliable coating adhesion.

Angled tip rods cast through-holes in swept airfoil blade cores, resolving breakage from radial curvature constraints.

Segmented purge circuits direct opposing flows through a rotor wheel body, reducing temperature gradients and extending component life.

Optimized alloy composition balances high-temperature creep strength against density to enhance specific strength for gas turbine blades.

A directional solidification apparatus uses a baffle to separate heating and solidification chambers for air melt alloys.

Independent thermal applicators tailor creep resistance and fracture toughness across blade sections, resolving uniform treatment limitations.

A mullite/NOSC bondcoat protects ceramic substrates through controlled oxidation and gas venting mechanisms.

Integral metal fillets on stator vanes guide rubber potting to optimize shear loading, resolving inconsistent joint geometry and reducing assembly time.

Segmented abrasive water jet cutting removes bulk material to reduce manufacturing time and tool wear during blisk production.

Vent holes on the mandrel surface stabilize pressure between the support hole and rotating body.

Segmented inner casings isolate high-pressure and resuperheated steam flows, reducing outer casing loads while sealing elements prevent leakage.

A heat-resistant superalloy composition stabilizes the gamma-gamma prime microstructure through precise elemental ratios.

An indented insert tube reduces dead regions near the trailing edge, lowering surface temperatures by up to 300 degrees Fahrenheit.

A planar stiffening element extends beyond the feed bore to increase natural frequency.

Segmenting the platform into thick and thin subportions aligns the center of gravity with the airfoil to reduce stress while maintaining bearing forces.

A gas turbine rotor blade features a cooling cavity in the platform stiffener to manage thermal loads.

Elastic strut fixings manage differential thermal expansion between ceramic and metal components, eliminating cooling needs.

An injection mold design uses sealing O-rings between outer bells and mandrel plates to secure fiber reinforcement during composite manufacturing.

Segmented non-integral turbine blade platforms encircle rotor blades to isolate thermal gradients between components.

Continuous reinforcement fibers link the airfoil to the dovetail section, preventing shear failure under centrifugal forces.

A composite turbine blade uses a eutectic ceramic inner carrying structure and a ceramic matrix composite airfoil.

A ceramic matrix composite uses non-crimped fibers stitched with elastic thread to enhance tensile response and inter-laminar properties.

A contoured flow surface with a trough and bulge shifts radial streamlines around turbine airfoils.

Varying pin fin dimensions across regions balances metal temperature control with casting integrity.

A blade root incorporates a soft shoulder between flanks and fillets to modify the interface geometry.

Optimized propulsor blades reduce irreversible propulsive losses by managing flow discontinuities and turbulence in gas turbine engines.

Integrated dovetail cooling holes channel high-velocity air onto rotor wheel tangs, reducing hardware complexity and space requirements.

A conical heat shield separates the working fluid cavity to block hot gas ingress and protect stator components from erosion.

Enclosing the slurry with a covering composition traps coating vapors to ensure uniform penetration into narrow cracks and channels.

A low flash point coating on ceramic core rods ignites to create space, preventing cracking from rod expansion.

Resiliently yieldable laser welds connect turbine blades to support rings, enabling controlled radial displacement.

Sliding and rotating core elements reduce mechanical stress during lost-wax casting, preventing breakage.

A rotor disc sealing flange sector uses a foolproofing element in its groove to ensure correct annular strip mounting.

Enlarged head pins abut shell molds to maintain ceramic core position, preventing pin ejection under centrifugal force.

Extended fibers protrude from one preform component and embed into an adjacent ceramic matrix composite preform to increase shear and pull-out strength.

A segmented injection mold core uses dovetail joints to assemble distinct elements that maintain alignment during resin transfer molding.

SiAlON buffers thermal expansion mismatch between ceramic matrix composites and mullite, preventing interlayer defects while maintaining oxidation resistance.

A turbine wheel assembly uses a multi-piece disk with curvic coupling to secure ceramic matrix composite blades.

Water-based polyvinyl alcohol impregnation replaces toxic solvents while increasing breaking stress and Young's modulus of ceramic cores.