Blade Accessories TRIZ Cases

Radial insertion grooves and fixing members secure the final bucket, eliminating Caruso keys to reduce centrifugal stress and assembly costs.

Segmented vent sectors control resin flow in horizontal composite cylinder molding.

A polymer composite coating blocks heat transfer from exhaust gases to a single-piece metal cylinder head and turbine, eliminating internal coolant passages.

Pivotable third pressing section bypasses trailing edge to allow unobstructed heating and balanced compression.

Recesses guide purge air away from leading edges, mitigating horseshoe vortices and reducing mixing losses in gas turbine engines.

Rope seals bridge gaps between shroud hangers and case structures, blocking cooling air leakage that reduces gas turbine engine efficiency.

Variable curvature bonding surfaces distribute radial stress across turbine wheel blade mounts, preventing structural failure at the rotor disk interface.

Increasing the pitch-to-chord ratio above 1.4 minimizes cooling air requirements and parasitic losses while maintaining high efficiency.

A replacement part for gas turbine blades features a U-shaped joining side to create precise welded connections.

Wavy side walls with airfoil ribs reduce secondary flow vortices and mixing losses caused by deflected flow layers near the wall.

Cross-key connection accommodates differential thermal expansion between ceramic runner and metallic carrier, preventing misalignment.

Segmented stage surface elevations control local pressure gradients to minimize secondary flow losses and eddy formation in turbomachines.

A silicon ceramic airfoil uses distinct suction and pressure side topcoats to resist volatilization and calcium-magnesium-aluminosilicate infiltration.

A bowed rotor blade with reduced middle width reduces profile losses and improves stage efficiency.

Axial disc lips on the rotor disc minimize air leakage passages at the blade interface, reducing heat transfer and improving engine efficiency.

Blade lugs engage disc notches to reduce stilt height, lowering mass and leakage.

An inclined metal body on the composite blade root prevents disk abrasion while distributing stress.

A turbine root spacer with a radial gap engages the blade root to support normal operation.

A ceramic matrix composite turbine bucket with a dovetail cavity receives an insert to reduce ply lay-up time and weight.

Segmented recesses and a supporting lever fix the seal strip, reducing weight while maintaining sealing reliability.

A nanocrystalline bainitic steel alloy maintains high strength and fatigue resistance across varying temperature ranges.

An axial locking device uses segmented wedges to secure a moving part on a turbine shaft while maintaining rotational freedom.

A protective surface layer with predetermined topography forms on a ceramic matrix composite via slurry deposition and heat-pressure consolidation.

Segmented cooling channels and a dedicated manifold manage high-pressure coolant flow to improve sealing effectiveness and reduce manufacturing costs.

Pack cementation deposits protective silicide layers on niobium alloys to overcome oxidation limits of nickel superalloys.

Slurry-based sintering creates a dense bond coat that blocks water vapor ingress and prevents rapid recession of silicon components.

Vacuum and pressurization drive filler slurry into thermal barrier coating cracks to eliminate remnant cavities.

Monolithic ceramic walls and a CMC liner with pedestals resolve the thinness-strength trade-off while enhancing convective heat transfer.

Radially inward suction side notch creates weaker local vortices to counteract tip vortex and minimize entropy generation losses.

A floating blade seal moves radially under centrifugal force to adjust blade length and maintain tight clearances against engine housing components.

Position markers and mold inserts control preform alignment, preventing resin clumps and scrap rates.

Segmented sealing rings engage turbine vanes via interlocking grooves to limit gas leakage and simplify assembly.

A cross-linkable coating composition cures at low temperatures using an acid catalyst and acrylic polycarbamate.

Transient liquid phase bonding joins gamma TiAl to nickel base superalloys, resolving low fracture toughness while increasing operating temperatures.

Automated laser deposition and CMM measurement restore damaged gas turbine airfoils, eliminating manual finishing to reduce material waste and processing time.

Recessed tip walls and parapet walls guide coolant through open and closed channel sections, maintaining cooling flow despite abrasion.

A composite vane manufacturing method injects resin during a specific temperature rise to control adhesive viscosity.

Segmented attachment geometry distributes stress concentrations in ceramic matrix composites, maintaining structural integrity without thermal issues.

A ceramic matrix composite turbine vane assembly uses stitched or tufted fiber reinforcements to interconnect the airfoil and end wall.

A turbine bucket airfoil features a tip pocket structure that generates controlled vortices to manage airflow near the blade tip.

A balance weight assembly clamps a rotor blade spar using a tray lip and cover to secure weights without fasteners.

Converging-diverging exit slots direct cooling fluid toward pressure and suction sides of an airfoil trailing edge.

Layered CMC fabric sheets create lightweight airfoils that withstand extreme temperatures and mechanical stresses without requiring extensive cooling fluids.

Reduced rhenium content lowers density while maintaining creep resistance, improving cyclic damage and oxidation performance.

Hanger heat shields reduce heat transfer to metallic mounts, eliminating dedicated cooling flows and improving specific fuel consumption.

Super abrasive machining quills machine complex airfoil geometries to resolve repair time constraints while maintaining surface finish quality.

Rare earth doped mullite and silica top coats prevent molten CMAS corrosion and delamination, enabling higher operating temperatures in gas turbines.

Continuous fibers in the composite airfoil piece transmit radial loads through a flange, managing thermal stress and manufacturing complexity.

A phosphate-based multilayer overlay system deposits metal oxide pigments onto superalloy substrates to form a stable protective coating.

Discrete pins engage slots in a movable lock ring to prevent rotation, resolving the trade-off between axial retention and assembly complexity.