Blade Accessories TRIZ Cases

Flow features in retaining rings connect disk pockets to conditioning pathways, resolving thermal distribution bottlenecks.

Stacked airfoils with spanwise twist minimize airflow separation at low incidence angles, increasing downward air movement by 31%.

A suspension plasma sprayed outer layer absorbs impact energy, preventing crack initiation and chip formation in the underlying thermal barrier coating.

A turbine blade sealing groove repair method uses spark erosion to remove defective grooves and insert dovetail-shaped strips.

An oxygen sensor monitors a sealed tank and triggers argon replenishment, reducing gas consumption while preventing oxidation of coated components.

Embedded metal reinforcement in diverging CMC walls distributes loads and prevents root collapse under high temperature conditions.

A vane adjustment assembly uses shim plates and roller pins to position variable vanes within a gas turbine engine annular ring.

Segmented cores form serpentine paths that improve cooling while maintaining core strength.

Compliant layers on fan blade dovetails distribute contact loads to reduce stress concentrations and prevent premature wear at axial ends.

Metallic reinforcement platform transfers force loads from ceramic matrix composite turbine vanes to support struts.

A repair method for turbine engine inlet caps replaces damaged structural fiber layers with adhesive-bonded composite patches.

Offset shoulder abutments in segmented inner rings prevent thermal deformation gaps and simplify maintenance assembly.

Strip seal support inserts eliminate complex slot coatings in ceramic blade tracks, blocking combustion product leakage and reducing component degradation.

A turbine rotor blade design optimizes spanwise spacing to reduce fluid flow rates.

A nickel phosphorus alloy diffusion barrier layer separates the substrate from the composite material.

Rare earth metal oxides create a stable barrier preventing CMAS infiltration into porous structures above 1200°C.

Extended chord lengths at the single-tooth attachment reduce leading edge stress concentrations by 34%, enabling lighter, larger gas turbine engine designs.

Welded monoblock rotor design reduces assembly complexity and mass while maintaining structural integrity for gas turbine engines.

Segmented shroud and stiffener design mitigates edge creep curl while maintaining structural strength against high-speed rotation.

Bonded multi-down conductor carbon blade eliminates internal voltage differences between spaced conductors to prevent lightning flashover damage.

Borescope fixtures transmit port identification data to automatically associate inspection images with external access ports.

Fiber-free matrix plies interspersed in CMC stacks enable complete melt infiltration, resolving densification failures in thick gas turbine components.

Swelling solvents soften toughened epoxy primer for abrasion, preserving substrate integrity during gas turbine repair.

Segmented rigid master patterns enable precise cooling hole formation in turbine castings, avoiding ceramic shell disintegration during investment casting.

Localized heat curing at lower temperatures repairs ceramic-based top layers without dismantling the engine or damaging underlying nickel-aluminide bond coats.

A turbine vane assembly incorporates a floating ceramic matrix composite seal to block hot gas flow between the metallic base mount and inner platform.

Mechanical vibration breaks protrusion-groove engagement, reducing disassembly time while preventing part deformation.

Relief grooves in the rotor neck surface reduce stress concentration at the blade hook, preventing failure under steam bending and thermo-mechanical loads.

Serpentine cooling passages route coolant through the turbine bucket base core to manage high-temperature operating conditions.

Segmented plenums direct cooling medium to undercooled aft regions, resolving high temperatures without increasing overall system complexity.

A ceramic-matrix composite airfoil uses radially discontinuous ribs to interconnect stacked sections.

Mixed weave composite fan platforms eliminate machining complexity while enhancing impact resistance.

Gusset acts as heat sink between rail and shank, reducing thermal expansion and fatigue cracking.

A gas turbine shroud uses elastomeric gaps between abradable protrusions to manage rotor blade contact.

Slitted sheet stock wear pads accommodate blade root curvature, eliminating rumpling and reducing manufacturing complexity.

Segmenting the airfoil into separate wall sections reduces stress concentration while maintaining effective near-wall cooling.

A single-shaft radial gas expander design consolidates multiple impeller stages within one casing to reduce component count.

Shaft openings direct cooling air to the coupling area, reducing thermal coning at the bearing.

A Cr-modified maskant system enriches attachment regions during aluminizing to prevent dimensional growth.

A stator rim injects cooling air into a channel to form a fluidic dam between the rotor and stator.

Morphing nominal CAD models to match deformed gas turbine blades eliminates complex reverse engineering steps and reduces repair costs.

Directed laser heating deposits uniform coatings on non-line-of-sight turbine areas, resolving geometric masking issues.

Laser welding restores metallic component cavities with precision, eliminating residual stresses and avoiding post-weld heat treatment.

Discrete spars extend through vane cavities to transfer thermal loads, resolving structural strength limits in high-temperature gas turbines.

High-pressure jets inject momentum into the flow path to resist core-to-bypass leakage, reducing turbine loading at low power settings.

Non-structural materials modify centroid alignment to reduce eccentricity and out-of-plane stresses in modular blades with abrupt thickness changes.

Radially disposed ribs in an impeller baffle slow swirling air to increase backface pressure, preventing oil leakage from bearing cavities.

Quick couplers connect interchangeable heads to a hydraulic ram, reducing tool complexity in tight engine spaces.

Soft press block corrects thermal bulging in turbine vane cover plates, preserving structural integrity and sealing efficiency.