Blade Accessories TRIZ Cases

Segmented turbine airfoils receive protective coatings before bonding, eliminating deposition blind spots between bonded components.

Continuous ceramic matrix composite plies form collar projections extending past platforms to reinforce gas turbine airfoils.

A platinum and chromium coating forms a single phase outer zone on turbine blade roots to enhance corrosion protection.

Radial blade biasers apply preliminary force to reduce stress range at attachment interfaces, extending low cycle fatigue life.

Segmented acid solutions remove protective metallic coatings from nickel turbine substrates while minimizing chemical etching damage.

Angel wing cavities extract bleed flow to prevent hot gas recirculation, reducing mechanical load and saving up to 9% mass.

A composite vane uses long fibers for stiffness and short fibers to fill shape gaps within a chemically compatible resin matrix.

Thickened attachment straps reduce stress concentrations in the support structure, improving durability against impact loads.

Localizing blade thickness at the trailing edge and inner span mitigates aerodynamic surging while constraining added weight.

Recessed tip leakage control channels redirect compressed gas flow to reduce aerodynamic losses from tip leakage vortices.

Angled stall fences redirect cross-flows along wind turbine blades, delaying flow separation and increasing lift force.

A rotating annulus mounted to the rotor disc defines the gas flow path boundary and provides interlocking sealing profiles.

Flexible mandrels create hollow cores in woven composite preforms, reducing mass while maintaining mechanical strength for turbomachine vanes.

Segmented blade outer air seal assembly uses a carrier with varying diameter pins and scalloped three-point contact for secure engagement.

Reactive magnesium oxide replaces mullite with spinel in alumina ceramics, preventing hot gas corrosion and reducing material ablation.

A rotor assembly uses a rim seal and pressure equalisation path to balance cavity pressures between stages.

Folding fiber blank segments forms integrated turbine engine platforms without separate filler elements.

Sacrificial fibers woven into ceramic matrix composites oxidize or melt to form cooling holes during densification.

Shim secondary channels route cooling air to the thermally stressed bulb top, reducing propulsion airflow demand.

A tapered dovetail sleeve distributes interlaminar tension across the interface, preventing lockup in high stress environments.

Pins pass through composite blade roots perpendicular to fiber layers, resolving fatigue deterioration from retaining forces.

A dual alloy turbine wheel joins a disk and unitary blade ring to prevent axial blade shift in auxiliary power units.

Integral CMC plies create robust damper retaining features, resolving integration complexity while maximizing temperature capability.

A nickel-based superalloy cast article uses specific chromium and cobalt ranges to deliver mechanical strength.

A boron-doped refractory compound maintains thermally grown oxide in an amorphous phase at elevated temperatures.

Conductive veil layer enables electroplating on uncured polymeric composite substrates, resolving low bond strength without thermal damage.

A turbine blade root scoop captures cooling air from a rim cavity and redirects it into internal diffusion channels.

A method forms ceramic matrix composite pre-forms with cavities using a meltable mandrel and durable tip cap.

Applying a nonstick coating to compressor aerodynamic surfaces prevents foreign material buildup, reducing wear and manual cleaning requirements.

Integrated metal core and fastener bases reduce assembly complexity while maintaining structural stiffness in composite vane designs.

Segmented interstage seal subsystems with radial coverplates eliminate spacer wheels and allow field maintenance without disassembling blade rows.

A contoured upstream platform edge with a recessed dimple reduces secondary flows and pressure losses in turbomachine blade channels.

A composite airfoil assembly with a dovetail portion uses a pitch snubber to distribute mechanical stresses across the mounting interface.

A thickness-modulated refractive film marker withstands extreme heat while maintaining optical readability.

Segmented turbine shroud design with circumferential seals blocks gas passage, reducing air leakage that lowers work extraction efficiency.

Rib extensions intersect flanges to form gussets that reinforce ceramic matrix composite airfoils against stress concentrations.

A gas turbine airfoil uses an equidistant camber line and optimized thickness ratio to maintain aerodynamic efficiency.

A thermal barrier coating system incorporates a reactive protective agent within its porous structure to form an immediate solid barrier against molten contaminants.

A ceramic matrix composite component uses a high-porosity fibrous core to enable uniform chemical vapor infiltration of the surrounding preform.

Internal routing in a rotor hub recess protects the wiring harness from aerodynamic drag and foreign object damage while accommodating blade motion.

A multi-mode Overjet engine directs hot fuel-rich gas onto turbine blades via a duplex guide vane to generate thrust.

Monolithic blade core integrates with shroud tip via hybrid three-dimensional fiber arrangement for structural integrity.

Segmented CMC plies with specific fiber orientations reduce manufacturing complexity while maintaining high-temperature strength.

Polygonal tows with a removable temporary matrix protect filaments from abrasion and ensure uniform ceramic infiltration.

Segmented ribs enhance tip shroud stiffness to weight ratio, enabling larger coverage for improved turbine efficiency.

A segmented cover assembly mounts to a turbine rotor using lips fitting into radial grooves and fasteners securing the segments.

Preheating the connecting nut to 130°C softens coked oils and enables differential expansion, preventing damage during disassembly.

Segmented scanners merge data to double point density, resolving the trade-off between device complexity and measurement precision.