Blade Accessories TRIZ Cases

Applying a sinterable slurry reduces environmental barrier coating roughness below 5.08 micrometers for improved aerodynamic turbine performance.

Segmented fiber layers reinforce double-thickness platforms to withstand centrifugal forces while maintaining gas flow path integrity.

A rotor blade uses a compound lean contour to increase local bending stiffness and shift natural frequencies.

Segmented aluminide-alumina bond coats and hermetic barrier layers prevent CMAS deposition and material loss in high-temperature gas turbine engines.

A turbine bypass passage redirects leakage fluid around stationary vanes to minimize re-entry into the main flow.

A steam turbine casing support unit incorporates heating elements to actively manage thermal expansion during operation.

An intermediary connector with extruded rivets joins the inertia ring to the turbine shell, eliminating MIG weld protrusions that require costly post-machining.

An abradable lip minimizes axial gaps between turbine blades and vanes to improve sealing performance.

Segmenting the duct with splitter blades mitigates boundary layer separation and reduces pressure losses.

A spring-loaded seal assembly bridges counter-rotating turbine rotors to maintain tight radial clearance during operation.

Adding a machinable stock layer before melt infiltration protects ceramic fibers from exposure, eliminating costly environmental barrier coatings.

A valve regulates pressure in the expansion machine valve chamber to maintain shaft seal contact.

Variable amplitude and wavelength in sinusoidal heating strands increase specific surface heating power to resolve insufficient tip heating effectiveness.

A frame-mounted containment chamber enables ultrasonic peening of assembled turbine rotors, preventing shot media contamination and ensuring operational safety.

Segmenting the cavity with ribs resolves uneven temperature distribution caused by internal pressure differentials.

Segmented spinner and rear flange assemblies eliminate exposed fasteners to resolve aerodynamic disruption while enabling composite material construction.

Metallurgically bonded low-density tip sections reduce pull forces while high-density roots maintain structural integrity.

Movable vane segments rotate between fixed airfoil members to alter aerodynamic properties in gas turbine engines.

Separated fiber plies form void pockets that reduce interlaminar stresses and thermal gradients in ceramic matrix composite airfoils.

A turbine shroud seal uses a damping coil to maintain strip seal engagement during radial misalignment, preventing gas leakage between segments.

Integrating the blade with a divided shaft eliminates separate frames and bolts, reducing part count and assembly time.

Integrating a composite annular ring into a metallic bore expands the self-sustaining radius, reducing weight while maintaining structural integrity.

A rotor vane casting method uses a transverse machining allowance on the downstream lip to enable longitudinal mould removal.

Adhesion promoter material restores turbine blade platform dimensions through deposition and machining, preserving superalloy microstructure integrity.

Sodium silicate slurry consolidates into a solid coating on porous ceramic substrates, reducing wear rates by two orders of magnitude.

Laser cladding deposits abrasive layers on turbine blade tips to reduce leakage losses from rotor-housing movement while maintaining ceramic coating integrity.

Embedding aluminum macroparticles into cathodic arc coatings via controlled arc parameters.

A turbine rotor calibration device uses fusible materials to alter fluid flow rates based on temperature thresholds.

A turbine blade substrate features a sigma-phase intermetallic diffusion barrier layer positioned between the bond coat and the metal coating.

Segmented rails on the turbine blade tip create shelf regions that reduce leakage flow, lowering heat transfer by 65% while improving aerodynamic efficiency.

A 3D woven fiber preform creates a single-piece vane module with integrated platforms.

A spring-loaded clamping jaw maintains position without continuous energy supply.

An inverted turbine structure rotates the housing instead of a central shaft, allowing solid debris to pass through without jamming the mechanism.

Segmented vane ring joints support the shroud housing to minimize structural path length and reduce bending-induced looseness in gas turbine engines.

Pivotable retaining structures on a mounting block equalize coining forces to prevent airfoil stress and deformation.

A porous rare earth monosilicate thermal barrier layer infiltrated with metal oxides prevents cation migration and reduces erosion in gas turbine engines.

Segmenting the downstream face via a deep transverse channel enables precise +/−0.05 mm tolerance on large radial dimensions.

Continuous three-dimensional braiding covers composite airfoil cores and dovetail roots to create integral high-strength attachment features.

Interdigitally woven fibers encapsulate radially inward blade roots within a ceramic matrix, increasing tensile load capacity and self-sustaining radius.

Varying second moment of area reduces rub loads and thermal energy generation at the airfoil tip.

Clamping members support tie-bolts within cooling air flow paths to enhance vibration absorption in gas turbine rotor assemblies.

Normalizes blade passing signals to extract static deflections, enabling real-time crack detection without adding complex mechanical sensors.

A turbine airfoil tip leakage control channel redirects flow from the pressure side to the suction side.

A minidisk flange and bumper enable tool engagement for rotor manipulation.

A CMAS-resistant barrier coating layer uses secondary oxides to reduce diffusion gradients and maintain thermal insulation.

An undercut rim design isolates the airfoil from tie shaft preload forces in gas turbine rotor assemblies.

Internal stiffeners between the core and skin enhance torsional stiffness against extreme loading.

Carbide forming elements like zirconium or tantalum reduce intergranular corrosion attack and pitting in forged precipitation-hardened stainless steel alloys.

A stator fin creates a converging flow channel that accelerates gas flow, reducing corner separation and aerodynamic blocking at high incidence angles.