Blade Accessories TRIZ Cases

Casing heating steam releases hydrogen from installed turbine blades, eliminating large thermal processing devices and labor-intensive removal procedures.

Raised rim along squealer tip edges anchors abrasive coating particles, preventing particle loss and reducing aerodynamic losses from matrix overhang.

Segmented rotor blade design with a detachable tip reduces maintenance downtime and material waste by allowing independent replacement of the worn component.

Segmented CMC plies form a pressure vessel and split trailing edge to prevent debonding under thermal loads.

A split hub rotor design uses a moment inducing element to deflect blades radially inward, reducing tip clearance without adding weight.

A split damped outer shroud with spacer keys dampens stator vane vibrations through frictional movement and interference fit interfaces.

High shear strength bushings bear torque loads to reduce bolt weight and improve alignment efficiency.

A flexible lock ring absorbs axial impact forces through torsional deflection to retain rotor blades within the hub assembly.

Segmented abradable rings with grooves cooperate with turbine blade wipers to form labyrinth seals, reducing leakage without increasing assembly complexity.

Cooling the coated substrate prestresses the ceramic layer, while expansion slits accommodate thermal mismatch to prevent cracking.

Inclined blade edges on a mixed-length turbine wheel reduce incidence loss and clearance flow, enhancing efficiency at high engine speeds.

Eliminating vacuum requirements during pyrolysis prevents pump contamination and simplifies equipment maintenance for micro-channeled material fabrication.

A molding tool uses a sacrificial alignment member to position crossover holes and impingement jet receiving features within a ceramic core mold.

A rotor balancing method uses reference influence vectors to determine calibration weights for insensitive gas turbine rotors.

Optimized wall thickness and diverging angles balance structural strength against weight while enabling easy maintenance through separable flange design.

Porous ceramic coatings abrade against metallic blade tips to form sealing furrows, reducing turbulence and pressure drops in gas turbines.

A split ring with axial holes anchors balance weights to a grooved flange, securing rotational components within the engine assembly.

Blade channel inlets capture recirculating fluid near leading edges and redirect it through hub channels to reduce viscous losses from flow separation.

Shell protrusions contact blade surfaces to prevent dislodgment during tab rolling and maintain precise angles post-brazing.

Segmented clinch nut plate distributes clamping loads to prevent spool shaft damage during bolt replacement.

A composite platform assembly molded around a metallic lug head distributes operational loads across the gas turbine engine fan section.

Segmenting a ceramic matrix composite blade into short fiber functional preforms and woven structural preforms simplifies complex geometry fabrication.

Segmented outer shaft bores and nested flange gaps deliver sufficient cooling air while minimizing bearing weight and preventing gas leakage.

Segmented turbine blade root profile resolves stress trade-offs by distributing centrifugal, bending, and thermal loads across distinct lobes.

Applying a sacrificial hydrophobic film to fan blades prevents dirt buildup and eliminates abrasive cleaning damage.

Composite fixture and thermoplastic sheath reduce cumulative weight while maintaining structural strength.

An infrared detection system captures thermal images of multilayer coatings to generate precise subsurface defect maps.

Fold distal plies transverse to main layers and interleave additional prepreg to form complex geometries.

A ceramic matrix composite turbine blade uses distinct fiber-reinforcement plies to transfer radial loads directly to the root.

Grit blasting, chemical etching, and mechanical finishing remove the damaged laser remelt layer to restore damage tolerance in turbine engine parts.

A ceramic matrix composite overwrap fuses adjacent vane platforms, eliminating gas path leakage while maintaining structural integrity.

Splined interfaces in a CMC vane structure eliminate inter-segment leakage while accommodating thermal expansion.

Restrictor plates establish pressure differentials to distribute cooling air through metallic load shields, reducing thermal stress on gas turbine engine vanes.

Segmented super-abrasive quills form firtree slots in gas turbine engine discs, reducing mismatched surfaces and ridges at the bottom.

Adaptive cooling pathways use high-temperature compounds to open supplemental flow channels only when local temperatures exceed predetermined thresholds.

Metallic spars support ceramic matrix composite airfoils, reducing cooling air usage while minimizing chemical interaction between materials.

Twisted helical vanes stabilize torque and lift-to-drag ratio under omni-directional low-speed flow.

A peening device mounting surrounds unpeened component regions to block abrasive impact.

Homogenization annealing at 1100 to 1200°C eliminates chemical concentration gradients, reducing scrap rates from property inhomogeneity.

Segmenting the preform into sacrificial and useful zones isolates high-count yarns, enabling controlled fiber content and optimal matrix densification.

Slanted racetrack holes in gas turbine rotors bend cooling air to increase swirl ratio, reducing aerodynamic losses from conventional straight hole routing.

Thermal processing evaporates entrapped contaminants from titanium honeycomb structures to enable subsequent weld repair.

A reinforced bond layer with electrospark-deposited ceramic segments mitigates cracking and delamination at the substrate interface under thermal stress.

Axial transfer fixture aligns turbine bucket dovetails with rotor wheel slots, reducing assembly difficulty for complex interlocking shrouds.

An integrated damping device combines sealing and vibration control to reduce blade fatigue while simplifying installation.

Laser deposition creates near-net shape erosion shields, reducing machining time for complex turbine geometries.

Outlet plate tabs interact with shelf discouragers to restrict coolant leakage back into the cavity, enhancing heat transfer.

Through-thickness reinforcements in a ceramic matrix composite turbine blade block hot gas migration toward the root and minimize interlaminar shear forces.