Blade Accessories TRIZ Cases

Aluminide and MCrAIY coatings resist volatile bromide formation in low-oxygen, HBr-containing off-gas streams to maintain component durability.

Resin injection bonds anti-wear strips to composite blades, eliminating manual gluing defects and ensuring precise positioning.

Sacrificial protrusions enable precise rotor disc balancing while stress-relieving slots mitigate internal stresses and crack propagation risks.

A ceramic seal segment uses spaced passageways to fix support bars while allowing circumferential movement.

Localized infrared heating interdiffuses coating precursors on turbine vanes, eliminating costly disassembly and downtime while restoring substrate integrity.

Internal fluid channels in rotating fan blades generate pressure differences that improve fuel combustion completeness and propelling force.

Mold core nubs define blind opening geometry during casting, resolving the contradiction between manufacturing simplicity and cooling efficiency.

Austenitic stainless steel alloy with controlled chromium and nickel content forms durable turbocharger turbine housings.

A compressor stator vane features a chord length that decreases toward the tip and increases at the root to optimize airflow capture.

A bladed turbine stator uses distinct metal alloys for individual blades to match local stress profiles and reduce overall mass.

Optical measurement replaces manual verification of preform deformation, reducing manufacturing time while maintaining cutting precision.

Sol-gel oxide barrier coatings protect superalloy substrates against hot salt corrosion through sintering and oxidation processes.

Centrifugal force drives a recessable damper into engagement with adjacent platforms, resolving sealing and vibration trade-offs in gas turbines.

Nested mold shells enable precise metal shield positioning on turbine blade preforms, resolving complexity trade-offs in resin transfer molding.

Continuous sealing ring with slide connections and helical springs reduces residual leaks through labyrinth seals without ventilation constraints.

First projection on turbine blade cascade end wall reduces static pressure downstream of trailing edge.

A ceramic core method forms integral mold walls and internal cooling features for gas turbine airfoils.

Cellular gamma prime precipitates create tortuous grain boundary paths that improve fatigue crack growth resistance without slow cooling rates.

Generative manufacturing builds engine housings with porous structural parts for enhanced containment and thermal management.

Segmented dovetail slots and diskposts decouple rotor blade and platform components, eliminating integral construction stress and manufacturing costs.

Electroplating restores airfoil tip height without substrate welding.

Segmented inter-stage sealing member prevents hot gas ingestion into rotor structure, reducing cooling air purge requirements and improving turbine efficiency.

A nickel-based first layer and chromium-based second layer form a ductile coating system on gas turbine engine components.

A multilayered environmental barrier coating structure protects silicon carbide substrates through a gradient rare-earth silicate layer and an oxygen shielding mullite interface.

Film cooling holes extend through an airfoil exterior surface at precise Cartesian coordinates to establish a protective thermal barrier layer.

Friction-fit collars join ceramic matrix composite airfoils to metallic end walls, resolving thermal expansion mismatches between dissimilar materials.

Offset fin restricts vortices while hollow recess avoids casing contact, minimizing weight impact and stress.

Formed sheet metal retainers eliminate forging waste and ultrasound inspection needs while maintaining structural reliability.

A turbine rotor blade tip shroud features a composite coating structure with oxidation resistant and hard wear resistant layers on the contact block.

Plasma activation enables low-temperature deposition of uniform environmental barrier coatings without oxidizing the substrate.

An adaptor assembly couples ceramic turbine blade roots to rotor disk slots via radial insertion and matching lobe configurations.

An embedded metallic spar tab resists dislodging forces and moments by mechanically locking composite airfoil plies against recessed surfaces.

A superelastic leading edge sheet absorbs impact energy on turbomachine parts, maintaining aerodynamic profile stability against foreign body damage.

A partition wall isolates the bearing from hot exhaust gas, preventing lubricant carbonization and vibration.

A turbine blade cleaning reactor uses decentralized gas distribution structures to ensure uniform exposure of components to reactive halogen-containing gas.

Chemical decomposition of SiO2 impurities weakens micro-contacts, preventing delamination from thermal shock stresses.

Dove tail slots and shims adjust the inner ring segment position to control tip clearance without re-machining.

A semicircular fabric sleeve with attached poles prevents slipping under rotating components, ensuring maximum protection against foreign object damage.

Centrifugal forces actuate a shape memory alloy closure to regulate cooling air flow, eliminating external valve complexity and preventing engine damage.

A turbomachine rotor blade heel features a bowl-shaped portion to receive anti-wear material deposits.

A ceramic matrix composite rotor disk features a rail integrated with the hub that tapers to an inner bore.

Strategic substrate steps and undercuts prevent coating bridging while the topcoat structure dissipates thermal stresses to extend component lifespan.

Convex and concave endwall profiles direct fluid flow to reduce boundary layer separation and eliminate horseshoe vortex losses in gas turbine engines.

Flat trays and side gas injection reduce donor consumption and tooling weight during superalloy coating.

Curved trailing edge portions in cast shroud slots accelerate leakage flow alignment while maintaining structural attachment integrity.

A plasma formation system heats the annular flow guide surface of a turbomachine separation nozzle to prevent frost accumulation.

A ceramic matrix composite component uses a three-dimensional braided fibrous core to enhance radial and torsional stiffness.

Three-dimensional woven ceramic overwrap eliminates filler material to strengthen joints between the vane core tube and platform insert.

A turbine blade shroud integrates a cutting tooth to create a sealing gap with the casing.