Blade Accessories TRIZ Cases

Class-dependent mistake-proof features prevent mismatched assembly of varying airfoil geometries, enhancing gas turbine engine reliability.

A composite airfoil assembly uses a bulbous root and pin to attach blades to an interdigitated rotor structure.

Trochoidal grinding of rotor disc slots reduces thermal damage and residual tensile stress by alternating intermittent contact with lateral surfaces.

Precise control of chromium, cobalt, and tungsten content prevents brittle phase precipitation while maintaining oxidation resistance in turbine blades.

Entrained melt infiltration agent fills voids in thick ceramic matrix composite sections, achieving 90% densification without complex external delivery systems.

Segmented heat treatment reduces residual stress in steam turbine rotors, preventing hydrogen cracking in corrosive geothermal environments.

Thermal barrier coatings applied to radial slots shield high-temperature regions, reducing temperature differences and component slipping.

Remachining turbine disk slots eliminates M23C6 carbide dissolution layers, restoring fatigue strength and doubling dwell service life.

Segmented coupling sleeves eliminate notch stresses in turbine blades while reducing vibration amplitudes through friction-based energy dissipation.

Dispersed hard particles in a resin matrix absorb impact and resist scratching, maintaining weight reduction while improving erosion resistance.

Laser ablation forms peak and trough geometries in metallic substrates to resolve adhesion stability issues under high thermal loads.

Independent compaction blocks minimize fiber buckling and prevent delamination during turbomachine blade manufacturing.

Orthogonal composite plies reinforce fan platform sections against structural deformation.

Circumferential passages inject fluid onto rotor blades to eliminate rotating flow instabilities and vibrations during low volumetric flow conditions.

Turbine blade tip shrouds use defined surface profiles to reduce mass while maintaining aerodynamic efficiency.

Parameter optimization of the test bench support member resolves insufficient representativeness in turbomachine part lifespan predictions.

Flared blade tip geometry reduces flow leakage and pressure mixing to improve aerodynamic performance while maintaining mechanical feasibility.

A gas turbine rotor blade features a fillet cavity that expands laterally from internal conduits to reduce mass and enhance cooling.

A flexible fibrous blank deforms to engage a stiffened platform element for composite blade assembly.

A nitric acid and hydrogen peroxide mixture removes corrosion products from turbine blades, extending service life while avoiding toxic waste.

Axial milling of assembled nickel-based alloy discs eliminates fragile shaped cutters and reduces vibration during cavity contouring.

A thermal barrier coating protects the rim-rotor annular structure from hot combustion gases.

Extracting the containment function into a separate burst shield absorbs kinetic energy and reduces casing weight.

A turbine rotor damper uses a larger aft plate and projecting nub to regulate cooling air flow within the engine assembly.

Adaptor assembly accommodates mismatched ceramic blade roots in pre-existing rotor slots while providing dynamic sealing lips and vibration damping.

A composite aircraft fan blade integrates embedded piezoelectric elements and RFID transponders to measure internal deformations directly within the material structure.

A temporary protective coating composition uses aqueous soluble polymer matrix combined with compressible and non-compressible fillers.

Pre-sintered articles with contoured faces eliminate air-filled gaps at bond interfaces, enhancing cooling effectiveness and manufacturing yield.

Segmented wedge members mitigate tensile stress concentration at the narrow neck and fillet of gas turbine blades by applying localized compressive forces.

Centrifugal expansion of annular rotor elements closes radial clearances against fixed stator components, preventing working fluid leakage during operation.

Pyrolyzed formulations infiltrated with molten ceramics replicate original CMC properties, resolving mechanical stability versus repair time trade-offs.

Variable admission holes in the inlet disk adjust flow rates to maintain efficiency across varying loads in compact supercritical carbon dioxide turbines.

A turbine blade outer air seal attachment uses a sloped transition member to reduce thermal stress concentrations.

A wobble plate motor converts fluid energy into rotational motion using a bent shaft and inclined disc rolling on a flat base.

An integrated strut and turbine vane nozzle design merges radial components into unified airfoils to streamline gas turbine engine architecture.

Shaping a flexible reference system with encoded dots ensures complete point cloud data acquisition without obscuring workpiece features.

Film hole protrusions on ceramic cores fix positional relationships against wax dies, controlling airfoil wall thickness and preventing cooling fluid leakage.

Porous ceramic thermal barrier coatings on heat shields allow controlled blade tip abrasion to minimize radial clearance and boost turbine efficiency.

Axial non-linear cooling conduit in turbine nozzle fillet prevents ceramic spallation from shallow-angle drilling, enabling higher hot gas temperatures.

Embedding spinel-type colorant nanoparticles in a ceramic coating prevents thermal decomposition and color shifts during heat hardening up to 1000°C.

Integrate abradability into composite structural elements by molding filler materials that create porosity, eliminating separate layer application.

Segmented turbine wheel shrouds use machined contact areas for force transmission and cast gaps for flow guidance.

A dovetail slot heat shield intercepts cooling air flow to minimize thermal impact on the blade root.

Curved lugs extending from composite blade walls transmit aerodynamic forces while maintaining structural integrity.

Replacing mechanical feed devices with direct electrochemical reactions eliminates component aging, maintaining high cutting precision and yield.

A ceramic matrix composite turbine stator vane uses a clamping retainer to secure the blade and band interface.

Silicon monoxide vapor breaks the bond between ceramic-matrix composite substrates and environmental barrier coatings.

A woven composite wear pad and deep burnishing process create compressive residual stress in the gas turbine fan blade root, preventing crack initiation.

Laser build-up welding repairs damaged titanium alloy blisk blades by minimizing micropores and heat-affected zones that weaken mechanical properties.