Blade Accessories TRIZ Cases

A silicon bond coating incorporates a boron-doped refractory compound to stabilize the thermally grown oxide in an amorphous state.

Pre-shaped circular blanks eliminate dead zones and abnormal heating, ensuring fine grain structures in high-temperature ring rolling.

A nickel alloy with precise chromium and titanium ranges improves high-temperature creep rupture life.

Annular cooling channel and primary baffle deflect ingested hot gas, reducing sealing air consumption in gas turbine stator assemblies.

Calcium aluminosilicate additives equilibrate with molten deposits to prevent substrate recession and spallation in high-temperature environments.

Wire electric discharge machining creates hollow steam turbine blades as single pieces, eliminating complex mold assemblies and welding operations.

Closing compressor inlet guide vanes early prevents rotational stalls and vibrations while maintaining convective cooling of components.

Pressurization apertures in shroud walls create pressure differentials that prevent gas flow path fluid ingestion into internal pockets.

MCrAlX coating utilizes minor alloying elements to form a diffusion barrier that minimizes interdiffusion between the protective layer and superalloy substrate.

Pre-assembly optimization of gas turbine rotor components minimizes bending moments, eliminating vibration acceptance test failures.

Non-ply ceramic inserts replace small prepreg plies in composite manufacturing to form thin sections and small radii.

Localized anti-wear coating on rotor vane ridges prevents cavity formation and gas leaks while maintaining thermal dissipation.

Axially overlapping stator overhang and rotor projections block hot gas flow into the rim cavity, reducing purge air usage and engine performance loss.

Inner discharge channels guide cooling air to composite blade feet, resolving insufficient convection during deceleration and takeoff.

A method inserts a ceramic airfoil into a reused metal turbomachine blade shank to lower cooling demands.

Helical connections translate carriage motion into torque, reducing mechanical stress from fixed twist constraints.

A composite airfoil assembly with a woven core and exterior layer provides stiffness transition between the core and skin.

Optical detection replaces deformed tie-rod references to eliminate balancing errors during gas turbine assembly.

Analyzing feature-to-feature speed variation determines rotor imbalance amount and orientation without additional sensors, preventing engine outages.

A shrouded blade repair method measures post-operation geometric characteristics to determine hardface surface offsets for precise machining.

Apertures in rotor heat shields balance pressure against hot gas leakage while reducing cooling air waste.

A turbine locking piece features a thickened end portion to increase rigidity and prevent deformation under axial loads.

An active clearance control system manages airflow to an interdigitated turbine outer shroud based on engine conditions.

Rare earth oxide transition layers react with CMAS deposits to form viscous products, preventing pore infiltration and maintaining low thermal conductivity.

Elongate supports and detachable end stops align the trailing edge precisely, enabling efficient milling without obstructing tool access.

Merging the outlet guide vane with the structural support eliminates separate pylons, reducing flow non-uniformity and fan blade loading.

Segmented slurry infiltration deposits coarse and fine ceramic particles with diamond onto ceramic matrix composites to resist environmental degradation.

Composite spacer with circumferential ear enables hook insertion, eliminating threaded holes and allowing thinner designs.

Maple seed turbine blades lower cut-in speeds by optimizing mass distribution, enabling efficient hydrokinetic energy generation from low-flow water sources.

Variable camber ratios along the fan blade span optimize aerodynamic loading to resolve the trade-off between fuel burn reduction and flutter susceptibility.

A blade outer air seal assembly uses a heated control ring to expand carrier portions radially outward for precise gap management.

Magnetic particles in repair resin enable non-destructive detection of repaired areas within painted organic matrix composites.

Discrete height segments in the under-root spacer accommodate manufacturing tolerances, ensuring consistent load distribution across circumferential locations.

Slip-on extension tip sleeve adds structural ribs and fairing to wind turbine blades, resolving insufficient support for extended tips.

Alternating inward and outward centrifugal stages eliminate eddy currents and pressure losses by connecting discharge directly to the next inlet.

Increasing the hub diameter and reducing blade length lowers aspect ratio, which reduces bending moments on blades in turbulent flows.

Movable seal segments isolate individual turbine blade passages during airflow testing, eliminating manual probe handling and reducing cycle times.

Segmented sealing wiper with visual wear indicator eliminates complex measurement during maintenance, reducing inspection time and preventing friction damage.

Segmented platforms block radial hot gas movement in ceramic matrix composite turbine blades.

Three-dimensional weaving forms a one-piece hollow turbine vane, eliminating laminated structural weaknesses and reducing fabrication complexity.

Segmented locking blade hooks engage a rotor groove to distribute centrifugal loads, reducing stress concentrations at attachment points.

Variable curvature in the blade root attachment balances stress distribution, preventing structural failure while maintaining secure radial retention.

Intermediary fitting projection distributes load away from blade groove corners, preventing deformation and fracture during disk inversion.

A balancing tool uses a vertical rod and sleeve pivot to settle the rotor assembly level.

Axial partition divides inner platform chamber into radially separated regions to direct fluid flow paths within the rotor blade structure.

A hollow part span shroud reduces blade weight and vibratory stress, increasing turbomachine flow rate by minimizing windage losses.

A silicon source layer diffuses material to form a protective silica membrane on ceramic substrates.

Simultaneous aluminizing and chromizing slurry application on gas turbine components forms distinct protective layers in a single heat treatment cycle.

Asymmetrical scallops on a turbocharger turbine wheel hub reduce rotational inertia for faster acceleration.

Structural cells within a turbine airfoil use variable thickness braided fibers to tailor stiffness and shear capability against operational stresses.