Blade Accessories TRIZ Cases

Burying molds in ceramic powder manages thermal gradients to inhibit columnar grain growth and resolve non-uniform microstructure issues in large castings.

A segmented pin and slot mechanism secures rotating segments to a turbine rotor.

A gamma titanium aluminide alloy with specific aluminum and niobium ratios reduces density while maintaining high-temperature strength.

A bi-metallic containment ring combines high-strength Inconel with ductile stainless steel to absorb impact energy from separated disk fragments.

A stator vane platform with a non-zero scarf angle pivots to lock circumferentially, preventing axial locking and reducing manufacturing complexity.

Segmenting the exhaust chamber inlet-side member creates axial clearance, resolving interference between the inner diffuser and last-stage turbine blades.

A hybrid steam turbine blade uses a glass barrier layer between the metallic section and carbon fiber composite filler to mitigate interfacial stresses.

Segmented tool segments with interior grooves distribute precursor gas uniformly, preventing uneven material build-up during densification.

A flared platform shell neck region rotates toward the inner ply layer group to maintain structural integrity under centrifugal forces.

Alternating finger damper biases seal carrier against knife edges, reducing air leaks and extending abradable seal life in gas turbine engines.

Segmented compressor inlet delivers separate fresh air and oxygen-reduced gas streams to resolve pressure loss and incomplete combustion trade-offs.

Metal boride coating on gas turbine airfoil tips reduces gas leakage and prevents metal transfer during sliding contact.

A nickel-based alloy composition with controlled carbon and boron levels promotes carbide precipitation at grain boundaries for enhanced creep resistance.

Unitary engine case integrates fan, combustor, and turbine components through a single casting process.

An interface coating with a V-Cr-Ti layer prevents abrasive wear and elemental diffusion between ceramic matrix composites and metallic structures.

A turbine rotor lip directs compressor air through passages to form a pneumatic barrier against leakage gas.

Removable metal protection shields composite turbine blades from fretting and oxidation, preserving fatigue resistance while maintaining low engine mass.

Circumscribing rail microchannels extend around the inner surface of the tip cavity to reduce leakage and enhance cooling efficiency at the blade tip.

A hybrid airfoil combines metallic and ceramic matrix composite sections to manage thermal loads in gas turbine engines.

Segmented side rails with varying dimensions resolve mechanical stress and alignment precision trade-offs in gas turbine blade shrouds.

Optimized brazing position and refractory filler metal prevent diffusion between TiAl turbine wheel and carbon steel shaft at high exhaust gas temperatures.

Intentional gas path ingestion reduces thermal gradients in the CMC seal, mitigating thermal stress while maintaining high temperature resistance.

Segmented apertures in the rotary valve maintain mechanical strength while synchronizing multiple combustion chambers to reduce aerodynamic losses.

Electromagnets in a rotating housing attract magnetic particles within magnetorheological fluid to offset missing fan blade mass, reducing engine vibration.

Load distribution devices redistribute forces in composite fan cases, limiting damage propagation from blade out events without adding excessive mass.

Monolithic case projection restricts vane axial motion during engine surge conditions.

A sintered topcoat layer on environmental barrier coatings reduces surface roughness through slurry deposition and densification.

Machining extra casting stock creates a full constant radius trailing edge, eliminating the surface mismatch between coated and uncoated regions.

Angled and height-adjustable ribs distribute forces uniformly to reduce weight while maintaining rigidity in gas turbine blade shroud segments.

Localized heating fuses new composite material with existing structures while maintaining lower temperatures to prevent matrix liquification and stress cracks.

Segmented airfoil, root, and tip modules reduce thermal deformation and oscillations by enabling partial replacement instead of full reconditioning.

Offset radial retention surface on fan platform reduces hub ratio and minimizes disc tooth stress.

Segmented insert pins accommodate differential thermal expansion between metallic carriers and ceramic runners, preventing misalignment and stress.

Molten thermoplastic seals turbine blade cooling holes, replacing toxic UV materials with a reusable phase-change solution.

Segmenting the carrier ring circumferentially eliminates axial pushing constraints, allowing larger rotor blade diameters and simplified maintenance access.

Segmented vernier rings with inner and outer tabs secure turbine rotor nuts, avoiding shaft protrusion interference while preventing nut unwinding.

Segmented blade roots and intermediate pieces use standardized concave curvature to enhance gas flow stability while reducing manufacturing complexity.

Segmented annular plate with knife-edge seals limits gas leaks between impeller stages without increasing vane manufacturing complexity.

Extracting an oxidizable core from consolidated preforms eliminates thermal expansion mismatches and simplifies infiltration for precise hollow parts.

Optimized coating composition minimizes secondary reaction zone formation, preserving mechanical strength and oxidation resistance in turbine engine components.

Brazing a durable cobalt-based plug into a machined tip shroud pocket prevents premature wear from mechanical and thermal stresses.

A rotor blade uses tilted fiber alignment to absorb centrifugal forces and reduce shear stress on the matrix material.

Segmented ceramic airfoils reduce manufacturing complexity while maintaining high-temperature resistance in gas turbines.

Chemical etching with HCl/H3PO4 followed by NaOH desmutting eliminates substrate damage risks from aggressive grit blasting.

Transition zones with specific warp-weft arrangements reduce stress on yarns at non-interlinked zone ends during composite shaping.

A multi-layer coating system provides a smooth surface finish on ceramic matrix composite components.

Sintering aids in rare earth disilicate coatings reduce porosity to prevent steam degradation and oxidation in gas turbine engines.

A thermal-insulating coating system on the angel wing inhibits heat transfer from hot combustion gases.

Pressurized hot water immersion degrades thermal barrier coatings through phase change and internal stress.