Blade Accessories TRIZ Cases

A boron-doped refractory compound integrates into silicon compositions to form durable bond coatings.

Composite rotor segments bond to a metal crown via serrated inserts, resolving heterogeneous weight distribution and reducing manufacturing complexity.

Secondary contact surfaces engage only after primary surface failure, preventing airfoil detachment while maintaining engine stability.

A thermal distribution layer on an engine shaft prevents asymmetric cooling distortion, enabling tighter clearances and improved fuel efficiency.

Segmented foaming agent maintains internal pressure throughout the entire curing cycle, preventing shaping defects and ply separation in composite blades.

A noble metal barrier layer on a molybdenum-based alloy substrate prevents oxygen infiltration through electroplating and thermal treatment.

Roughening the inner surface of a steel tube through cold working disperses thermal stress, preventing scale exfoliation during steam oxidation cycles.

A mold with a porous bottom and deformable diaphragm forces slip through fiber textures to form preforms.

Flush ceramic inserts in metal alloy BOAS bodies reduce cooling flow requirements while maintaining structural strength.

Varying the trailing edge wall thickness reduces stress peaks and flow losses in gas turbomachines by smoothing material transitions.

A lock assembly secures compressor blades to a rotor disk using dovetail interference and slider seals.

Replacing damaged partitions with pre-manufactured coupons eliminates time-consuming manual contouring and welding in the steam flow path.

An automatic balancing system displaces a weight via a motor to counteract rotor vibration, eliminating manual maintenance downtime.

A replacement cap with an opening provides direct access to a turbine blade internal cavity for secure structural welding.

Angled serration profile on turbine airfoil roots distributes centripetal loads to reduce wear and extend functional life.

Asymmetric damper plates restrict combustion gas ingress while reducing windage heating in turbine rotors.

An annular cut in the retaining ring shifts radial force direction, balancing axial thrust and preventing tilting of the rotor disc flange.

A reaction turbine harnesses condensation heat through curved channels and shock waves to generate thrust from ejected vapor droplets.

Segmented composite disk with radial plies absorbs hoop stress, reducing weight while maintaining structural integrity under centrifugal forces.

Segmented seal ring couples to turbine vanes using centering features, reducing hot gas bypass leakage.

Three-dimensional weaving creates a one-piece fiber preform for composite turbomachine blades and vanes.

Offsetting the lay-up profile accommodates preform bulk to prevent localized ply displacement and wrinkling during composite forming.

A vitreous glass monocoating seals ceramic matrix composite turbine substrates directly without metallic bond coats.

Reducing the propulsor blade stagger angle below 15 degrees directs particulate matter into the bypass flow, protecting core engine components from damage.

Integrating anti-rotation locking into the mounting sleeve eliminates complex separate elements, reducing rotorcraft weight and gearbox casing thickness.

An active tip clearance control system uses an ejector to amplify high pressure air flow for effective turbine cooling.

Segmenting the welding operation into vertical and horizontal stages reduces facility size requirements while maintaining high-quality seam formation.

Segmented shroud walls with circumferential expansion joints reduce thermally-induced strain from differing inner and outer wall expansion rates.

An intermediary chamber flushes with gas mass flow to maintain pressure above exhaust levels, preventing leakage during low-power operation.

Stress-relieving openings in layered pre-forms enable hot creep forming of inflated aerofoils without shape distortion.

Wider rib cap joins offset cavity inserts to prevent incorrect installation and ensure correct cooling performance.

An intermediate layer between a gas turbine blade platform and root reduces stress concentrations and prevents crack propagation.

A hybrid rotor disk assembly combines metal hubs and ceramic matrix composite platforms to balance hoop stresses.

A bladed disc assembly joins dissimilar workpieces using sequential diffusion bonding and friction welding processes.

Precise Cr, Co, Al, Ti, Ta, W, Mo, Nb, C, and B ranges maintain tissue stability while delivering balanced creep strength and corrosion resistance.

Coverplate lock engages coverplate tabs to secure rotor stages, reducing assembly complexity while maintaining sealing effectiveness.

A wishbone-shaped fiber layer structure merges into a flange to form an integrated attachment on composite airfoil fairings.

Nested inner and outer seals prevent cooling air leakage through pressure differentials.

Form platform depressions to attach replacement airfoils, avoiding full assembly retirement.

A rotatable support mounts multiple aerofoil blades in an array to enable simultaneous computed tomography scanning within an energy beam.

Metallic spar system transfers loads from ceramic matrix composite turbine vanes to prevent structural twisting.

Interleaving cut composite plies between secondary platform layers reinforces joints, reducing stress concentration and shortening manufacturing time.

Merges blades with the shell via stamping to lower inertia, improving launch performance while cutting assembly complexity.

Optimized nickel-base superalloy composition with specific tantalum and molybdenum levels.

Radially oriented through-holes allow direct airfoil insertion and removal, eliminating the need to lift the upper casing for maintenance.

A gas turbine output correction method calculates adjustment coefficients using distinct degradation ratios from different time periods to adjust control outputs accurately.

A turbine nozzle airfoil features a flow groove extending from the leading edge to the trailing edge on the suction side.

Dynamic actuators adjust blade outer air seal positions to minimize tip leakage losses while preventing blade contact.

MAX phase ceramic composite lowers specific density to reduce centrifugal forces, enabling larger gas turbines without sacrificing mechanical strength.