Blade Accessories TRIZ Cases

Automated helical braiding of nested tubular preforms eliminates core requirements and enables variable thickness geometries.

A pre-formed inter-blade profile plug system ensures correct orientation during turbine runner assembly.

Segmenting the blade tip into a durable insert prevents seal damage and cracking without increasing overall rotor weight.

Blade grid platform depressions reduce secondary flows and pressure losses by optimizing local geometry to minimize vortex formation.

Ceramic matrix composite shroud blocks withstand elevated hot gas temperatures from eliminated first stage nozzles.

A turbine shaft with a secondary tubular segment breaks at a weak point under excessive tangential stress to trigger mechanical protection.

Auxiliary openings in the single rotor disc enable intermediate pressure injection, avoiding axial lengthening and vibration issues of axial expanders.

Multi-blade platform with stiffeners retains blades axially, eliminating air recirculation risks and simplifying assembly.

Aft seal plate secures blades without forward locking, eliminating casing disassembly during maintenance.

A Hans bell housing seals a balloon envelope while an internal impeller moves air to adjust altitude.

A laser melts rotor blade material to form wear indicators while a plug collects the molten substance.

A gas turbine blade uses two independent cooling channels to regulate fluid flow and manage thermal loads.

A turbine blade incorporates a variable radius fillet within the pocket between buttresses to distribute mechanical loads.

Annular sealing end plate isolates ceramic matrix composite blades from metal parts, preventing fiber twisting during fabrication.

Segmented blade supports with central portions and wing elements distribute loads to improve structural integrity while maintaining manufacturing simplicity.

Bimodal porous ceramic particles in aqueous slurry create non-collapsing closed porosity, preventing thermal conductivity degradation at high temperatures.

A hollow ceramic matrix composite article applies a ply-wrap layer with a single turning point curve to eliminate ply fraying at sharp angles.

Segmented pockets in a rotor blade tip plate channel cooling media to remove heat, reducing tip cap temperature without disrupting turbine efficiency.

Merging bearing assemblies into one structure reduces axial length and weight, enabling interdigitated turbine sections.

Segmented fan track liner moves independently against detached blades while maintaining rigidity for ice impact resistance through dynamic fastener failure.

A jet engine rotor blade burnishing tool aligns its carrier spindle axis through the rolling contact point to simplify multi-axis programming.

A repair tool removes material from high-stress regions of turbine components to reduce fatigue.

A roller joint enables radial movement between ceramic airfoils and metallic carriers to accommodate thermal expansion differences.

Slurry deposition with binder and plasticizer creates a machinable surface layer on ceramic matrix composites.

Recessing the tip outer wall creates an open trailing edge slot that directs internal cooling air radially to lower blade temperatures.

Segmented bond coats with graded aluminum layers prevent interdiffusion between the substrate and coating, extending turbine component service life.

Cantilever trailing edge section reduces stress concentrations and notch effects at the airfoil-platform transition.

A closing element bridges the assembly space between adjacent cover elements in a gas turbine rotor disk to maintain structural integrity.

Cold spray deposits oxide-free bond coats onto turbine airfoils via supersonic impact, avoiding vacuum chambers and reducing cycle times.

Asymmetric aerofoil edge profiles shift camber lines to mitigate efficiency losses from manufacturing tolerances and wear.

Automated imaging captures transient thermal responses to identify coating defects, replacing manual inspection and reducing unnecessary recoating expenses.

Segmenting the fin into a solid cutting edge and hollow sidewalls aligns centrifugal forces with the neutral axis, reducing radial loads on the rotor.

Protrusions on the turbine blade suction side mitigate boundary layer detachment near the trailing edge, reducing vortex disturbances and aerodynamic losses.

Bending the stationary blade tip section in the rotor direction aligns stagnation lines, reducing secondary flow loss caused by combustion gas leakage.

Thermal vaporization extracts support material from metal recesses, eliminating acidic corrosion risks and process complexity.

A power turbine controller adjusts electrical generator torque to maintain constant spool speed during transient load changes.

A diode grounds aluminum fan blades to titanium rotors, dissipating static charges while blocking reverse current to prevent galvanic corrosion.

Embedded wear indication layers in composite gaspath walls enable visual detection of erosion, preventing maintenance delays.

A single wedge secures a closure bucket within a rotor groove, eliminating stress concentrations and remachining during reassembly.

Compressed gas projects breakaway shell carriers to deposit environmental barrier patches, eliminating turbine disassembly for in-situ repair.

Staged nozzle and blade assemblies enable selective submerged or colliding turbine operation within a single axial turbine structure.

Segmented meta-structures and isogrids resolve weight-strength trade-offs in gas turbine airfoils.

Varying the throat angle along the vane span improves airflow distribution and reduces vortexing at inner and outer duct diameters.

A casting process directs molten metals into specific mold zones to form tailored grain structures in a single step.

A continuous support ring with through-holes secures vane spar flanges, eliminating inter-segment joints to reduce leak paths and manufacturing complexity.

Protrusions upstream and downstream of lacing wire holes reduce stress concentrations without disrupting gas stream flow.

A steam turbine rotor blade features a leading edge protrusion that releases water droplets via centrifugal force.

A machinable coating applied to ceramic matrix composite articles enables precise geometric correction through subsequent machining operations.

A turbine rotor wheel uses insertion grooves and radial catching features to secure second buckets without separate keys.

Three-dimensional weaving creates single-piece composite turbine blades with integrated airfoils and platforms for enhanced structural integrity.