Blade Accessories TRIZ Cases

Aligning the rib with the aerodynamic load vector reduces bulge deflection while enabling larger sub-cavities for efficient cooling.

Local quality principles apply varying stress levels to concave and convex regions, enhancing component strength against tensile loads.

A slurry-based diffusion coating process applies a chromium-enriched layer to localized substrate areas without mechanical peening.

A grinding device machines rotor blade tips in situ using a screening apparatus and suction extraction to remove dust from the machining region.

Varying the seal rail axial thickness optimizes tip shroud balance and frequency tuning while reducing stress at the fillet region.

Segmented repair using pre-fabricated patches restores coatings on wing while reducing downtime.

Segmented casting joins distinct superalloys to create lightweight turbine rotors, mitigating material degradation at high operating temperatures.

A specialized jig stabilizes rotor blades during high-speed grinding to enable concurrent tip machining across multiple cascades.

A sealing assembly for rotary machines uses a protective member to shield stator labyrinth teeth from direct combustion gas contact.

A manifold with distribution channels delivers matrix material to ceramic composite plies, preventing porosity and silicon-rich zones in thick sections.

Centrifugal force drives a teardrop seal into a blade root gap to meter cooling fluid, reducing leakage losses that degrade engine efficiency.

A glass coating protects gas turbine components against hot corrosion.

Composite foam cooling passages transfer heat from airfoils to fluid, eliminating removable core support pins while maintaining structural integrity.

A ceramic matrix composite turbine blade features an abrasive tip bonded to its radially outward surface to prevent rub damage and reduce temperatures.

Pressurized inert gas fills internal blade cavities to prevent hot gas penetration and water vapor degradation after foreign object damage.

Grinding groove faces restores geometry while elastic foils resist wear from repeated blade impacts.

Tubular pre-forms with unconsolidated CMC fibers cut and reorient extraneous surfaces to create integrated flaps.

Segmented shroud mounts prevent turbine wheel contact during thermal deformation to maintain high efficiency.

A free-floating damper member inside an airfoil cavity reduces structural vibrations through frictional contact with sidewalls.

Segmented internal and external aluminum donors ensure uniform coating thickness within hollow turbomachine cavities.

Segmented porous molds resolve pressure gradients during slip injection, ensuring uniform particle distribution and low macroporosity.

A nickel-based casting superalloy composition strengthens grain boundaries and resists oxidation through precise elemental control.

Bent cross-section flexible seal accommodates thermal expansion at turbine diffuser parting line, reducing fluid flow across the gap.

A gas turbine guide vane inner platform uses a dovetail housing to secure the cover plate through mechanical interlocking.

A low diameter turbine rotor clamp assembly secures discs using a threaded sleeve and cylinder to apply axial force.

A hybrid blisk embeds a low-density insert within a metallic blade body to reduce rotor mass.

A turbine wheel assembly uses ceramic matrix composite blades mounted via slot and edge configurations to a metallic disc.

Amorphous silicon bond coating with crystalline grains prevents oxygen penetration to gas turbine substrates, eliminating blistering from low cohesive strength.

Carbide precipitation within austenitic matrix maintains dimensional stability at 1020°C while preventing oxidation and corrosion damage.

Sintering aids densify environmental barrier coatings via slurry deposition, preventing steam-induced volatilization at lower temperatures.

A seal plate restraint mechanism operates through a wide clearance between the blade platform and rotor disc outer surface to switch engagement states.

A laser transmission unit directs a beam to a target on opposing roller stands for precise shaft centerline alignment.

Segmenting the fan platform into independent upstream and downstream portions allows each section to pivot separately, managing large trailing edge clearances.

A damper seal integrates friction damping and air sealing within a single sheet metal assembly.

An isolation element in a turbine bucket dovetail reduces centrifugal and axial loading on adjacent buckets, extending component life.

An underlap seal extends past adjacent strip ends to distribute stress across the joint interface.

Sintered ceramic hollow microspheres reduce thermal conductivity while matching the substrate coefficient of thermal expansion to prevent spallation.

A separate bearing housing mounted with resilient elements moves relative to the main casing to isolate rotor vibrations for precise phase detection.

Ceramic coatings on aluminum expander blades resist corrosion and erosion, reducing production costs for low-temperature organic Rankine cycle systems.

Parallel stress paths through blade roots and shims reduce local shear forces, minimizing mass while preventing premature groove wear.

Inclined hub legs introduce radial clamping loads to reduce contact stress and vibration in turbomachine tie shafts by distributing torque transmission.

Annular flow mixing lobes guide high momentum exhaust toward the diffuser inner surface to form vortices.

A turbine blade design shapes the hub endwall flow path width to induce three-dimensional flow redistribution from the reference height toward the hub.

A temporary bridging ring stabilizes blisk blade preforms during abrasive water jet cutting to maintain structural integrity.

Sticky cleaning member removes dirt via shearing action, preventing mechanical damage to hybrid laminar flow control surfaces.

Flowing silicon and carbon precursors with hydrogen reduces residual porosity below four percent while maintaining mechanical properties.

Bias members secure a ceramic airfoil piece in a metal retention pocket, reducing compressor bleed cooling needs.

Resilient fingers on an assembly tool abut seal members against disc platforms, resolving alignment complexity during simultaneous installation.

Segmented outer rim with radial channels and seals relieves hoop stress in gas turbine integrally bladed rotors.

A multi-angle cold spray nozzle assembly deposits powder material onto component surfaces using varying impact angles.