Blade Accessories TRIZ Cases

Radially inward threading on the positioner allows angular adjustment of rotor axial location, resolving clearance limits in gas turbine engines.

Segmented refractory metal cores stabilize thin ceramic inserts, reducing cooling air flow loss while preventing core breakage during casting.

Segmented bucket portions engage the blade tongue to maintain load-bearing capacity while enabling easy assembly.

Upstream radial walls integrated into rotor disc cells axially block blade roots, eliminating retaining rings that cause gas leaks under stress.

Decreasing cross-sectional area reduces vortices and pressure losses while maintaining effective cooling.

An inclined leading edge geometry guides working gas axially to reduce impact loss, maintaining turbine efficiency during variable nozzle throttling operations.

Fugitive inserts define complex cooling cavities in ceramic matrix composites, bypassing restrictive subtractive machining.

Replacing damaged outer bands and vanes preserves internal cooling passages, extending service life while maintaining engine performance.

Bosses extend from cantilevered core sections to constrain rib wall thickness and positioning during airfoil casting.

Pressure-side winglets block tip airflow leakage, reducing heat transfer and material degradation at the turbine blade tip region.

Interlocking non-planar abutment surfaces on a hinged turbine bucket resolve fatigue issues in bolted connections by accommodating centrifugal forces.

Abradable seal system directs 90% of volume loss to the softer matrix material, protecting the abrasive tip from damage during engine operation.

Shorter mid-span chords reduce secondary flow losses while maintaining structural support at the root and tip regions.

Gradient width distribution reduces turbulent flow wear on comminution parts while maintaining processing efficiency.

Locator blocks define a local datum to machine airfoil tips independent of root displacement, resolving setup complexity.

An automated machine transfers and stacks ceramic matrix composite plies using dried pre-impregnated tapes.

A turbine seal mechanism accommodates radial rotor expansion using ring members with differing thermal expansion coefficients.

Temporary bridging rings hold blade preforms during abrasive water jet cutting, preventing deformations and vibrations that increase tool wear.

Segmented strut conduits manage fluid flow to reduce lube system complexity in geared turbine sections.

Protective coating prevents oxidation of unalloyed chromium and aluminum matrix during high temperature operation, maintaining cutting performance.

Replacing glass fillers with polymer micro-balloons limits maximum rub temperature and reduces heat flux into turbine blades.

Integral embedded conductor paths eliminate post-production wire routing, preserving structural integrity while providing intrinsic electromagnetic shielding.

Non-axisymmetrical troughs between turbine airfoils increase flow passage volume to reduce frictional losses on the platform surface.

A circumferential seal portion divides the turbine wheel space to direct cooling air radially outward.

Chamfered plydrops eliminate resin-rich areas and stress concentrations in composite laminates.

A temporary bridging ring stabilizes blade preforms during abrasive water jet cutting, reducing vibrations and tool wear while enabling higher feed rates.

A film hole design with a metering portion and diffuser trench directs coolant flow along the airfoil surface.

Segmented braze tape casting resolves thermal spray volatility by enabling precise chemical control on complex geometries.

A method fabricating a ceramic matrix composite turbomachine blade by assembling separate consolidated fiber preforms and a central strand.

A non-axisymmetric platform elevation reduces energy losses by altering static pressure distribution and vortex formation near blade side walls.

Localized platform thickness variation enhances stress resistance at critical junctions without adding unnecessary weight to the stationary component.

A chromium-enriched diffused aluminide coating replaces aluminum with chromium to form a protective layer on gas turbine components.

Optimized chromium and cobalt levels maintain creep resistance above 900°C where conventional alloys fail.

Sintering aids lower processing temperatures to form dense environmental barrier coatings that prevent steam penetration in gas turbine engines.

Segmented labyrinth seals resist airflow through turbine dovetail gaps via pressure-driven vortices, enabling field repair without rotor disassembly.

Computer system calculates centerline deviations to determine optimal blade distribution for rotor assemblies.

Asymmetric rim flange extends intrados gas travel distance to increase flow velocity and reduce static pressure.

Flange arrangements create tortuous paths to stop hot gas ingestion and reduce thermal gradients on vanes.

Incorporating boron-doped refractory compounds into silicon bond coatings suppresses thermally grown oxide crystallization.

Double-flow axial flow expander cancels thrust forces while handling high pressure, eliminating gas leaks from division surfaces.

A turbine rotor blade with near wall cooling channels directs air through a collector cavity to cool the trailing edge region.

Metallic sleeve transmits force loads from ceramic matrix composite vanes to support structures, managing thermal expansion differences.

Optimized alloy composition suppresses element segregation during solidification, enabling large-sized gas turbine components with miniaturized crystal grains.

A ceramic matrix composite rotor disk integrates blades into the hub to distribute mechanical loads across the structure.

A tackifier bonds unidirectional fiber sections to enable precise stacking and alignment in ceramic matrix composites.

Angle-interlock weave in 3-D CMC turbine airfoils inhibits delamination and enables thin trailing edges without machining.

A blade assembly uses non-periodic sidewall contouring to customize transition areas between adjacent blades.

High-pressure jets create a fluid barrier that resists core-to-bypass leakage, maintaining engine efficiency at reduced power settings.

Rare-earth ions migrate from a metallic bond coat into a ceramic top coat to enable luminescence sensing at the thermally grown oxide layer.

Segmented inserts mediate retention forces to prevent permanent disk deformation, eliminating material damage and repair needs.