Blade Accessories TRIZ Cases

A turbine blade tip trailing edge trench directs coolant flow from a squealer cavity to the blade tip rear.

Metallic annular rings and an elongated member accommodate differential thermal expansion in CMC vanes, preventing fatigue cracking from tensile stress.

Adjusting fan blade parameters reduces bypass thrust while enabling excess shaft power generation, cutting development time for aeroderivative conversion.

Crossing sub-channels embedded in wind turbine blades generate vortices to energize the boundary layer and prevent flow separation.

Precise alloying of rhenium, tantalum, and tungsten reduces density below 8.75 g/cm³ while maintaining creep resistance and microstructural stability.

Integrated hollow shaft splines eliminate bolted flanges, reducing assembly complexity and mass while maintaining torque transfer.

A turbine vane assembly combines a ceramic matrix composite airfoil body with a metallic support spar to direct gas flow efficiently.

A composite blade root uses three laminates with intersecting fiber orientations to distribute stress and maintain structural integrity.

Multilayer coating system with near-infrared absorber reduces cure temperatures and energy consumption while maintaining color accuracy.

An anti-swirl device alters cooling steam flow direction to enhance heat transfer from the rotor.

A ring and stack nut retain the bearing compartment position while the low-pressure turbine shaft unthreads for independent removal.

Preform rigidization positions core plies on a mandrel to define a tip cavity for subsequent densification.

Enhanced edge guards absorb impact energy and integrate heating conduits to prevent icing on turbine engine airfoils.

Segmented flowpath insert ducts with retention hooks reduce exhaust case weight and fluid leakage while maintaining aerodynamic efficiency.

A reinforcement plate bonded to a turbine mid-span shroud restores structural integrity through tack welding and high-temperature brazing.

Diverting compressor fluid through a bypass circuit heats turbine sections, restoring efficiency lost during part-load operations.

Targeted cooling passages protect vane segment edges from oxidation by mixing with combustion gas, avoiding performance degradation.

Angled contact faces in the multi-radial serration profile distribute centripetal stress to reduce wear at the rotor disk attachment root.

Curved blade post transitions distribute stress across turbine rotor disks, reducing fatigue at geometric discontinuities.

An integrated air seal combines hot gas containment with cooling airflow management, reducing structural complexity in gas turbine engines.

Adding vanadium to the Mo-Si-B system lowers density below 8 g/cm³, solving weight constraints in aerospace turbine applications.

Forward seal plate and selective damper restrict combustion gas ingress while permitting cooling air entry to maintain cavity pressure.

Interlocked fugitive inserts eliminate flash and dimensional variability in multi-wall airfoil cores, enabling precise internal cooling geometries.

An externally mounted actuator moves an air seal segment through a case wall aperture to adjust blade tip clearance in gas turbine engines.

Slurry deposition with sintering aids creates dense environmental barrier coatings that resist high temperature steam degradation.

A roller burnishing operation lengthens the radial extension of titanium compressor blade squealer tips through cold compaction.

A tip leakage control channel redirects airflow using internal vanes to manage momentum at the blade tip.

A multi-material vane uses a metallic-composite hybrid airfoil to manage flow direction and structural loads.

Variable spline thickness eliminates free edges to reduce stress concentration and extend service life in turbine compressor couplings.

Interleaved tapered wedges in a dovetail root section resolve weight versus durability trade-offs for composite gas turbine engine blades.

A hollow core energy harvester reduces magnetic braking effects to improve measurement accuracy and extend battery life in gas meters.

Variable stiffness springs counter thermal warpage during warm restarts, preventing hung-start rotor failure.

Ice-cream-cone-shaped pedestals eliminate dead zones behind trip strips in turbine airfoils, maintaining airflow attachment and improving heat transfer.

A compressor rotor assembly uses an integrally formed inner and outer backbone system to reduce structural weight.

Anisotropic thermal expansion in ceramic matrix composite turbine vanes reduces interlaminar tensile stress at the leading edge.

Small ceramic grains fill surface porosities in an abradable coating, reducing specific fuel consumption by 0.4% while maintaining temperature resistance.

An inverse conical stopper joins two interconnected shafts to create a self-centering mechanical lock.

Continuous ceramic fiber fabrics merge into a unitary body to eliminate weak interfaces and maintain connection strength in coupled turbine vanes.

Segmented floating wall sectors with clamp seals accommodate thermal expansion to prevent fluid leakage through axial joints.

A hybrid radial gas turbine bearing support combines Inconel 718 and Haynes 282 alloys to withstand high thermal loads.

Segmented chromium layers with a CrN diffusion barrier maintain thermodynamic stability at high temperatures while preserving vibration resistance.

Single cutting of pre-curved workpieces simplifies loop blade geometry, reducing manufacturing complexity and costs.

A blind assembly tool uses a driver to rotate shafts that pivot arms for precise retention element engagement.

Ceramic matrix composite aerofoils use localized reinforcement insets to resist impact damage from foreign objects.

Optimized single crystal alloys lower density without sacrificing creep strength, resolving the weight-strength tradeoff in high AN2 turbine blades.

Slurry deposition of rare earth hafnium tantalate creates dense refractory coatings on ceramic substrates.

A barrier layer seals internal passages in ceramic matrix composite blades, eliminating fragile multi-ply tip caps and reducing assembly labor.

Narrowing the nozzle guide vane outer ring accelerates hot combustion gases through a Venturi effect, reducing turboprop engine fuel consumption.

Alternating amorphous silica and silicon nitride layers prevent silicon diffusion and fretting in gas turbine engine disks.

Curved near-wall cooling channels direct air across turbine blade platforms, reducing leakage flow and stress concentrations that limit engine efficiency.