Blade Accessories TRIZ Cases

Segmenting the core into a removable metal section and ceramic insert prevents deformation during wax injection, eliminating costly orifice plugging operations.

A composite casting core combines refractory metal and ceramic materials to form precise cooling passageways, reducing core fragility during investment casting.

Detachable arcuate seal segments on a cover plate accommodate short-shank blades by distributing sealing paths radially.

Interface plenum decelerates cooling fluid flow from the rotor bore exit to ensure uniform distribution across the blade inlet.

Dip coating a refractory metal oxide slurry onto gas turbine substrates forms dense protective layers that inhibit silicon volatilization.

Applying a ceramic precursor coating with metallic impregnation reduces surface roughness on CMC parts, avoiding costly chemical vapor infiltration.

Segregating high and low pressure compressor air streams via a partitioned nut prevents hot combustion gas entry, reducing turbine disc temperature.

Segmented blade design maintains throat area while reducing load, improving adiabatic efficiency without outlet interference.

Sequential alloy pouring controls metallurgical bonds and minimizes mixing gradients, ensuring microstructural stability in complex aerospace components.

Lateral extensions on a platform core create side openings during solidification, eliminating post-molding machining steps.

Mechanical cold working restores fatigue strength in gas turbine repair sections through distributed plastic deformation.

A second slurry coating fills valleys of a rough thermal barrier layer, reducing surface roughness without damaging the underlying coating integrity.

A low frequency RFID sensor system uses a ferromagnetic core to concentrate magnetic flux for wireless data transfer.

Parallel metal braids in a flat sheath allow controlled impregnation, preventing blade deformations during de-icing system manufacturing.

A turbine wall element uses inclined bottom flat parts to expand cooling channel thickness and attenuate sharp edges.

A clamped stabilization device with spring-elastic elements supports thin-walled workpieces during machining operations.

Optimized shroud geometry enables turbine blades to rise and couple at low speeds, resolving insufficient centrifugal force constraints.

Segmented cooling passages with intermediary inserts reduce heat transfer to coolant, lowering compressor bleed requirements and preserving engine efficiency.

Segmented cores replace wire suspension to control wall thickness while open tops simplify cooling hole drilling.

A modification patch attaches to an aerodynamic vein to define a new profile using stereolithographic resin.

Precise parameter control of chromium, cobalt, and refractory elements resolves the trade-off between turbine disc strength and manufacturing cost.

Precise compositional control in conventional casting produces high-strength turbine disk material without powder metallurgy costs.

A ceramic matrix composite airfoil segment uses box-shaped fiber geometry to define rectilinear bond lines for robust assembly.

Stationary spray nozzles apply uniform thermal barrier coatings while rotating the engine, eliminating disassembly downtime.

Asymmetric rail configuration with relief features reduces load slot depth, minimizing fatigue in the rail while ensuring secure blade mounting.

A turbine rotor device uses a prestressed fiber-wound layer to exert pre-loading force on the rotor body.

Chemical vapor infiltration densifies a preform with pore formers, achieving monomodal porosity and 15-35% fiber volume for high creep resistance.

A silicon metal bond coat deposits on ceramic matrix composite substrates to form a cohesive interface layer.

Centrifugal acceleration in ceramic rim-rotor turbomachinery reduces NOx emissions while maintaining material reliability at high cycle efficiency.

Welded hollow baffles prevent leakage and reduce manufacturing time.

Multi-layer sol-gel coatings prevent oxidation erosion and cation diffusion, raising operational temperature limits for turbine engine components.

A wind turbine blade uses varying design lift coefficients along its span to optimize aerodynamic performance.

Pre-assembled rotor units couple axially to a central tubular case, reducing assembly time and complexity while maintaining shaft support reliability.

A helical turbine device uses a transverse bar to stabilize operational angular position in flowing liquid.

An S-curved end wall on the downstream diaphragm outer ring prevents flow separation at enlarged passages, reducing exhaust loss while maintaining stability.

Splitting transverse filament pairs at the stiffener reduces mass while maintaining mechanical strength against centrifugal forces and impacts.

A casting mould uses a partition wall to separate the grain duct from the second volume, enabling controlled solidification fronts.

Gravity seats rotor blade attachments into slots via an axial support fixture, eliminating complex tooling for precise assembly.

Conical turbine wheel geometry reduces axial length and mass, mitigating thermal stress and lubricant degradation in high-speed turbochargers.

A pulse jet cryogenic cleaning system uses ultrasonic transducers to transform high-pressure fluid into pulsed slugs that remove coatings via sublimation.

Spherical bearing transmits torque between concentric swashplate components, eliminating redundant scissor assemblies to reduce assembly complexity.

A restoration slurry repairs damaged ceramic matrix composite coatings on gas turbine components through heat treatment.

Segmented ring members in circumferential slots minimize stress concentrations and enable blade installation without cutting notches.

Segmented fiber tow counts and thicknesses in the trailing edge resolve structural integrity challenges in high-temperature ceramic matrix composite airfoils.

Preventive maintenance blends, peens, and coats turbine disc dovetail cooling slots to mitigate stress concentrations and extend component service life.

Segmented manufacturing of composite airfoils allows independent curing of skins and cores, resolving co-molding limitations for improved quality control.

Tapered intermediary members align suspended rotors automatically, eliminating difficult manual crane operations.

Eliminating throat zones via converging walls prevents interrupted solidification and cold lap defects in turbine blade preforms.

Microchannels in turbine blade tips enhance heat transfer and durability while reducing coolant usage.

Segmented metal and silicone mandrels create precise cooling channels in high-temperature ceramic matrix composites.