Blade Accessories TRIZ Cases

A casting mold uses a weakening layer to release TiAl alloy cast products.

Segmented rotor hub with radial flanges manages centrifugal stresses in oxidizing environments using ceramic matrix composite materials.

A probe with a location signal receiver detects transmitter signals to determine its position within a gas turbine engine.

Multilayer weaving creates a fiber blank for composite turbine vanes, enabling hollow airfoils and solid platforms to reduce manufacturing complexity.

Radial tabs on a hollow airfoil collar transfer loads while minimizing heat conduction from ceramic matrix composite to metallic spar.

An aft switchback and forward arc in the main plenum direct coolant to pressure side ports, preventing hot gas ingestion.

Segmenting the propulsor into independent rotating components reduces nacelle weight and drag penalties while maintaining high fuel efficiency.

Atomic layer deposition coats gas turbine engine disks with uniform protective barrier films that resist salt-induced hot corrosion.

Electrophoretic deposition restores damaged ceramic thermal barrier coatings on electrically conductive turbine components.

Pyrolyzing a ceramic precursor slurry creates a bond coat that resists spalling and delamination in thermal barrier systems.

Axially stacked ceramic matrix composite segments eliminate porosity in thick gas turbine blades by allowing separate manufacturing of thinner sections.

Segmenting the blade into ceramic and metallic zones simplifies manufacturing intricate features while maintaining high-temperature resistance.

A ceramic matrix composite airfoil uses woven reinforcing fibers suspended in a ceramic matrix to form a hollow core structure.

Composite rare earth silicate coatings resist calcium-magnesium-aluminum-silicon-oxide infiltration and mechanical wear in gas turbine engines.

Radial recompression fins reduce pressure differences between turbine recesses, preventing fluid leaks that degrade engine efficiency.

TIG welding eliminates insert complexity and premature failure risks in gas turbine blade sealing.

A physical vapor deposited multi-element coating protects superalloy disks from oxidation and hot corrosion without degrading mechanical fatigue capability.

Axial assembly of segmented abradable sectors creates a labyrinth seal that reduces leakage and simplifies installation.

An asymmetric hollow portion in the rotor blade fillet reduces weight by varying wall thickness, resolving the strength versus weight trade-off.

An asymmetric abutment guides the feather seal into correct alignment within the blade pocket, preventing misinstallation and reducing air leakage.

Double vacuum arc remelting casting combined with hot isostatic pressing and isothermal forging produces gamma TiAl turbine blades.

Reducing the central thickness of a turbomachine rotor blade cleat lowers rotating mass without compromising rotational locking reliability.

Asymmetric mateface design compensates for manufacturing variability, reducing waterfall and damming effects that disrupt gas turbine performance.

Circumferential pockets amplify strain to increase locking force above centrifugal loads, preventing friction-induced damper lock at high speeds.

A machinable coating mediates the interface between ceramic matrix composite blades and metal disks, preventing chemical reactions at high temperatures.

A gas turbine engine shaft bearing configuration positions a low pressure compressor hub between bearings to support rotating shafts.

Segmented keys eliminate plastic deformation by engaging circumferential and platform grooves, ensuring reliable axial restraint for steam turbine rotors.

Profiled endwall regions mitigate secondary losses from horseshoe vortices by reducing structural strength of flow patterns.

Segmented bearing assemblies support interdigitated turbine rotors within a gas turbine engine frame to reduce seal interface clearances.

Molten silicon infiltration restores stiffness and oxidation resistance in cracked melt-infiltrated ceramic matrix composites without degrading fibers.

Segmented inner and outer surface cooling holes reduce thermal stress and oxidation damage on gas turbine blade tips.

Circumferential swirl breaks redirect steam flow to enhance vortex formation, reducing sealing excitation forces that cause rotor oscillation.

Alternating flanges and overhang lips mate between adjacent rotor blade platforms, minimizing gaps that cause air losses in gas turbine engines.

A steam turbine control device estimates thrust force using an operating point map to regulate balance piston pressure through segmented valves.

A segmented root spacer with a radial groove fractures to absorb shock loads during foreign object impact.

Mounting a shim in a disc notch reduces heat transmission and thermal stresses, enhancing mechanical strength and operational lifespan of turbine blades.

Multi-piece mounting segment inserts radially into a rotor slot and expands to secure blades, eliminating assembly gates that cause stress concentrations.

Segmented diffuser zones with varying angles reduce pressure losses and boundary layer separation.

Wave springs and soft metal foils reduce thermal stress at tab interfaces, maintaining concentricity while minimizing energy loss from tip clearance.

Segmented arcs in a compound fillet distribute stress at the airfoil-platform junction, preventing cracks caused by space-constrained designs.

Curved bore transitions distribute stress in a turbine disk, reducing fatigue at geometric discontinuities while minimizing weight increases.

Axial shoulders on disk teeth and blade roots create a cylindrical surface that secures an annular seal, preventing air leaks between blades and disc.

Segmented mateface gaps align with and cross streamlines to minimize stagnation and secondary vortices, reducing pressure losses in gas turbine engines.

Flexible silicone molds create twisted rib voids that align ribs with airfoil geometry, reducing weight and improving cooling efficiency.

A nickel-based superalloy with optimized composition forms a high gamma prime phase content.

Segmented outer diameter shroud design with integral brackets resists radial forces to maintain fan exit stator positioning.

Predetermined slot geometries remove defects while preserving structural integrity, ensuring reproducible repairs across different operators.

Differential thermal expansion between the control ring and carrier dynamically adjusts radial position to minimize leakage from large tip clearances.

A unitary ceramic matrix composite rotor module integrates airfoils directly onto a common drum structure.