Blade Accessories TRIZ Cases

A shaft-mounted hub moves trim balancing closer to the rotor, preserves corrections after coupling changes, and reduces field maintenance risk.

A Co-based coating with controlled Al diffusion forms protective Al and Cr oxides, preserving wear and oxidation resistance above 1000°C.

Separate hub, blade, and ring inspection enables defect detection before bonding, cutting scrap and supporting strong turbine rotor joints.

Heat treating removed titanium gas turbine components can annihilate dislocations, restore fatigue tolerance, and avoid mechanical repair.

Localized sidewall thickenings and a pressure-side depression cut secondary flows and flow losses in turbomachine blade passages.

Overlapping staggered riblets cut pressure and viscous drag, delay flow separation, and reduce heat transfer on fluid-exposed surfaces.

Localized curing of a sintering-additive slurry repairs spalled engine seal teeth in-module, restoring ceramic adhesion while avoiding teardown.

A rotor flange combines labyrinth seal fins and balancing counterweights to seal turbine cavities while reducing axial space and complexity.

A laser-drilled pilot hole guides waterjet machining to form turbine cooling apertures without ceramic coating spallation or oversized outlets.

Separate blades, ring, and hub are inspected before friction welding, reducing scrap from blade defects while preserving high-temperature rotor capability.

Angular layer deposition rebuilds damaged turbomachine overhung sections, enabling repair of flared tips that were previously replaced.

A deformation curbing member holds turbine vane shrouds in position during overlay welding, limiting distortion and residual stress in repair.

Repairs damaged high-temperature component surfaces with a base-material preform that diffusion-bonds below melting, avoiding brittle braze phases.

A machinable coating lets nonconforming CMC parts be reshaped or filled before final vapor infiltration, salvaging defective articles.

Targeted machining and austenitic stainless steel cladding rebuild worn diaphragm rails to nominal dimensions with less waste and longer service life.

Centered tool dies and a radial centering element improve gas turbine seal assembly precision while securely capturing the carbon seal.

A semicircular fabric sleeve with poles fits the turbine casing to catch dropped pins and prevent foreign object damage during maintenance.

Damaged flared tip blades are rebuilt by layered laser or CMT deposition to restore overhung sections and avoid full replacement.

A pivot-clamped deep rolling fixture controls contact stress on hollow fan blades to improve fatigue life, surface finish, and throughput.

A forged base body with a covered cavity routes hot air for de-icing while improving guide vane toughness against bird strikes.

Internal mixing and controlled spray delivery restore turbine engine coatings through small casing holes without disassembly or uneven coverage.

Chemical milling after lost-wax casting enables turbomachine blades to reach thinner trailing edges for better aerodynamic performance.

Plies in a brazed hollow vane cover tune vibration, stiffness, and stress distribution to better handle changing turbine operating conditions.

Controlled Fe, Mo, Si, and Cu additions help Ti-64 retain manufacturability while improving thick-section strength, fatigue resistance, and FOD response.

Automated EDM drilling analysis uses depth, velocity, and current key points to detect blocked or tapered holes faster and more reliably.

A brazed cover with damping plies lets hollow vane assemblies tune vibration and stiffness despite casting limits on cavity formation.

Pre-filling holes and slots in CMC turbomachine parts lets infiltration densify the repair and cut porosity, restoring strength and service life.

Chemical milling refines cast turbomachine blade trailing edges to 0.2-0.45 mm when lost-wax casting alone cannot reach the required fineness.

A protrusion preloaded by dipping transfers a fixed paste amount for faster, more consistent mini-core bonding on turbine cores.

Sintered replacement pieces and an attachment piece repair damaged gas turbine components while avoiding cracking, high porosity, and alloy degradation.

Sub-melting thermal cycles bond a base-material preform to damaged component surfaces, avoiding brittle brazing phases and extending service life.

Mechanically squeezed stops support turbine blade tip welding, preventing edge collapse, excessive penetration, and thermally affected zones.

Shaped consumable aluminum anodes control current density in ionic liquid plating, enabling tailored coatings on non-planar turbomachine surfaces.

Pre-modeled guide paths offset the wire bicycle effect in curved EDM cuts, improving aperture accuracy without slowing wire speed.

A recessed guide with contact portions and rollers trims wind turbine blade protective shell edges precisely while preventing blade surface damage.

A high-Tg polyimide matrix holds abrasive blade tip thickness and bond strength under turbine rubbing while reducing heat-driven delamination.

A foam airfoil core with an electroformed metal shell cuts fan blade weight while improving impact resistance and structural stability.

Pre-modeled guide paths offset wire drift in curved EDM cuts, keeping constant wire speed while improving aperture accuracy and cycle time.

A machinable coating fills dents and corrects CMC geometry before final infiltration, enabling repair where direct machining is unsuitable.

Cyclic hydraulic pressure drives turbine blades out of stacked rotor grooves in situ while reducing worker strain and scoring risk.

Non-contact gas-magnetic thrust and radial bearings stabilize high-speed gas turbine rotors by balancing center of gravity and reducing wear.

Mechanical vibration and combined axial-circumferential force help remove or install interlocked turbine blades without major turbomachine disassembly.

A variable-angle endoscopic tool reaches engine blade leading and trailing edges through a downstream access port without engine disassembly.

Gas tungsten arc welding plus solid-state joining rebuilds turbine blade tips with higher repair durability and longer engine service life.

Two overlay weld materials repair gas turbine blade cracks by balancing weldability and high-temperature strength to prevent crack recurrence.

Centered tool dies and a centering element improve gas turbine seal assembly precision while enabling efficient press-fit capture of the carbon seal.

Controlled heat treatment shifts β to γ phase in hot-forged TiAl alloy, improving forgeability, room-temperature ductility, and strength.

A pre-sintered recess insert rebuilds distressed cooling hole outlets in superalloy turbine parts without time-intensive welding or brazing.

Localized removal of damaged metal edge sections enables composite blade repair with adhesive rebonding, lower material waste, and less downtime.

A low-permeability barrier segment blocks silicon migration during CMC re-infiltration, preserving original segment strength and integrity.