Blade Accessories TRIZ Cases

A silicon carbide junction gate field-effect transistor voltage regulator maintains stable DC output using a constant current source and source follower stage.

Segmented shroud design featuring parallel fins and converging ribs reduces bending stress and weight while minimizing tip leakage loss in gas turbine engines.

A seal plate inserted into a thermal stress prevention slot on the carrier hook portion prevents compressed air leakage and distributes thermal loads.

Optimized rotor component stacking positions minimize static unbalance forces during gas turbine engine assembly.

Segmenting the rotor allows localized high temperature materials while lowering production costs.

A detachable fan blade platform uses elastomeric seals and a pin system to slide replacements into place, bypassing adhesive curing delays.

Segmented heating modules counteract differential expansion to prevent casing bending and rotor blocking during shutdown.

Phase-controlled signal routing reduces channel complexity while maintaining vibration measurement precision across all rotor blades.

A ceramic matrix composite vane uses a rotatable baffle to adjust orientation within the central chamber.

Nested retaining grooves in a mid mount sleeve reduce bearing stresses and weight while solving packaging complexity in high speed gas turbine engines.

Composite annulus fillers with flexible braces absorb blade movement, reducing fretting fatigue and debris generation in gas turbine engines.

A mounting tool pivots turbine vane heels radially to align roots for axial socket insertion.

Segmenting the fan into a single unit mounted on a tie shaft eliminates complex individual bolting and surrounding component removal during maintenance.

Compressed fabric bushings restore bolt hole integrity in gas turbine nose cones without replacing entire components or using inadequate epoxy fillers.

Sacrificial metal particles within a cobalt-based coating act as anodes to prevent galvanic corrosion on martensitic stainless steel compressor blades.

Porous fan nacelle inlets weaken shock waves and minimize flow separation, reducing aerodynamic drag without increasing nacelle weight.

Strategic reliefs on dovetail contact surfaces shift natural frequencies away from driving forces to reduce vibration-induced fatigue.

Segmented thermal processing creates thick hermetic coatings, reducing cycle time compared to conventional slurry deposition methods.

Optimized austenitic stainless steel alloy reduces nickel dependency while maintaining oxidation resistance and machinability for turbocharger turbines.

Vortex generators on fan blade leading edges create a fluidic barrier to resist core pressure leakage, maintaining engine efficiency at reduced power settings.

Segmented notch filter damper reduces rotor frequency vibrations while maintaining rigidity against atmospheric pressure differences.

Segmented unidirectional CMC plies increase tensile strength twice over woven materials, resolving stress concentration limits in gas turbine blade seals.

Repositioning the drive arm between the shaft and first rotor ensures failure detection via speed measurement, preventing uncontrolled acceleration.

A woven fiber structure uses surface yarn withdrawal and replacement to maintain continuous threads over decreasing thickness portions.

Segmented CMC disks use interlocking features to balance hoop stresses, preventing airfoil roll without traditional bolts.

Three-dimensional weaving of central and lateral fibrous strips creates a bulbous turbine blade root, eliminating insert positioning complexity.

Segmented CMC nozzle sectors on a metal shroud absorb thermal stress and pressure loads via independent deformation.

Optimized Ni-based alloy composition reduces elemental segregation during solidification.

Bonded stiffening portions prevent disbonding or inversion in gas turbine engine seals, maintaining aerodynamic efficiency.

Segmented heel design resolves double-layer fibrous texture complexity by using single-layer textures for sealing and aerodynamic roles.

A photography system uses a sensor to detect cyclic variations in detection values and acquire images at predetermined positions.

Alternating porous and dense layers in abradable tracks reduce turbine clearance while managing erosion resistance and thermal stress.

Asymmetric blade lock features guide specific rotor blades into designated slots, preventing misalignment during gas turbine assembly.

Internal slots in the rotor disk direct cooling air to reduce thermo-mechanical fatigue and lower component weight.

Closed pores within the ceramic matrix resist sintering and spalling, maintaining coating integrity at elevated temperatures.

Positioning members adjust seal arc segment placement to minimize gas flow leakage through clearance gaps, enhancing turbine efficiency.

Optimizing gas turbine rotor assembly stacking positions and mass corrections to minimize static unbalance forces.

A method reworks ceramic structures by injecting bonding material into drilled holes and curing it to restore structural integrity.

Attach registration blocks to salvageable airfoil segments for precise machining and reassembly.

Geopolymeric resin matrix replaces titanium ducts to reduce weight while maintaining mechanical reliability above 500°C.

Segmented tape-deposited coatings protect blade tips from steam penetration and wear.

Partial vacuum expands air bubbles in molten epoxy to prevent laser penetration damage.

Centrifugal forces drive resin through internal channels to reload the abradable layer, eliminating engine disassembly and reducing maintenance downtime.

Positioning a damper off the blade-to-blade centerline creates an unequal load split that reduces vibratory stress without adding engine weight.

Multi-piece fan spacer design with solid lugs and laminate platforms improves durability by distributing stress effectively.

A composition-gradient bonding sub-layer transitions from pure silicon to stoichiometric mullite between the substrate and anti-corrosion protection layer.

A diffuser section creates a stop surface that stabilizes the drilling element at low angles, preventing tool slippage during cooling channel fabrication.

Segmented shroud bodies with coupling spars mitigate resonance and dynamic stress by distributing radial loads while enabling retrofitting.