Blade Accessories TRIZ Cases

Real-time coupling of laser and ultrasonic shock waves overcomes velocity mismatch, increasing residual compressive stress.

Inverting the seal to the interior prevents dust from damaging ceramic coatings, while local shielding extends component service life.

Magnesium oxide stop-off materials contain brazing filler during heating and remove easily via air pressure to prevent substrate contamination.

An integral composite blading member eliminates gaps between the airfoil and platform to stop uncontrolled leakage in gas turbine engines.

A resistive band coupled to laminated plies provides local compression loading to maintain structural integrity under mechanical stress.

A nickel-base superalloy composition balances high chromium with restricted molybdenum to maintain phase stability and weldability.

Helical rotor blades attach at the axis root to remove central hub flow disturbance and enable self-starting.

Digital sector models enable precise virtual assembly and optimal arrangement selection for turbomachine distributors.

Composite coatings on fan blade stilts prevent wear from oscillation during autorotation, extending component lifespan.

Ribs in hollow turbine vanes create counter-rotating circulations that limit heat exchange, reducing wall temperature while maintaining low blade weight.

Suction holds a capping panel against a pocketed aerofoil body, enabling accurate welding that reduces material wastage and component weight.

A composite turbomachine blade uses three-dimensional weaving to create complementary asymmetrical geometry for integrated platform functions.

Segmented turbomachine blade parts butt-welded to reduce machining time while maintaining mechanical strength.

Asymmetric groove geometry reduces hoop stress concentrations and prevents wire seal migration without increasing material usage.

A composite woven outlet guide vane uses a removable core and resin transfer molding to form a hollow airfoil structure.

A cooling module uses interconnected flow sections to facilitate radial, longitudinal, and circumferential fluid movement for uniform heat transfer.

An aluminoborosilicate glass layer from a MoSiB coating resists sand infiltration and oxygen diffusion in extreme environments.

Segmented shroud inserts replace worn vane location slots via adhesive bonding, eliminating costly full assembly replacement.

Segmented vane nozzles attach to an integrated strut using dovetail joints, eliminating interface mismatch and bolt seizing in hot gas turbine environments.

Wedge-shaped spars in a mid-span shroud assembly provide clamping force to alter turbine blade natural frequencies.

Segmented guide vanes use internal channels to distribute loads, reducing stress concentrations while maintaining weight savings.

A hollow vane uses a nested cover design to create a smooth external face without welding.

Co-diffusing chromium, hafnium, and yttrium via pack cementation resolves the contradiction between multi-element protection and process complexity.

A mask protects critical features during ceramic matrix composite repair processes.

Intersecting ribs transition airfoil geometry to attachment section, segregating cooling flows and managing thermal expansion differences.

Discontinuous gaps in a blade ring energize the boundary layer via periodic flow injection, preventing separation and improving pressure recovery.

Angel wings seal second steam flow in blade roots, reducing thermal stress and extending service life.

Interleaved fingered plies reinforce ceramic matrix composite turbine nozzle joints, reducing stress cracking and cooling air requirements.

Gettering particles in a silicon dioxide matrix react with oxidants to protect substrates from thermal degradation.

The attachment member alters the load path by transitioning from radial biasing to outer ring contact as temperature rises, reducing stress in the nozzle dovetail and outer ring.

Applying a corrosion-inhibiting primer and filled epoxy paste restores eroded aluminum fan blades without full recoating.

Metal fibres reinforce the wind turbine blade root, balancing aerodynamic efficiency gains against required mechanical strength.

A contoured endwall on a composite platform anchors gas turbine airfoils while shaping internal flow paths.

A ceramic-based liner mechanically interfaces with a movable nacelle to accommodate thermally-induced dimensional changes in gas turbine engines.

A blade outer air seal uses a reverse retention hook to constrain the abradable seal within a trough for secure positioning.

Fluid circulation through the transmission shaft bore stabilizes temperature, correcting measurement errors caused by thermal variations in turbine engines.

Radial cavity in dovetail joint reduces mounting segment weight, alleviating stress on components caused by high centrifugal loads during operation.

Co-infiltration joins porous tip preforms to airfoil preforms, eliminating thermal-mechanical stress at material interfaces.

Twisted slots in the rotor web align with flow paths to reduce stress peaking and increase fatigue capability.

Adjusting the aluminum to titanium ratio minimizes eta phase formation during solidification, preventing micro-shrinkages and improving manufacturing yield.

A gas turbine fan blade features a variable leading edge thickness profile along the span to optimize structural integrity.

Segmented balance weight pins allow targeted rebalancing of gas turbine rotors, reducing vibration and maintenance time.

Segmented head cap guides airflow through circular grooves, reducing turbulence and increasing torque for dental handpieces.

An integral rotation controlling feature limits dovetail twist to prevent rotor body gouging and ensure proper assembly.

A radial turbine rotor combines ceramic matrix composite blades with a metallic hub to resist high temperatures.

Endwall throat decambering and pitchline throat overcambering in adjacent nozzles reduce secondary flows that degrade stage efficiency.

Variable slope angles in the inlet case flowpath minimize flow separation and improve pressure ratio, resolving performance drops from fewer compressor stages.

Segmented trailing edge plies prevent bulging under differential pressure while maintaining aerodynamic efficiency.

Segmented blade retention slots block air leakage across the rotor disk while maintaining blade retention, improving turbine engine efficiency.

Outwardly biased blocks align a guide bushing aperture with the blade root for precise punch insertion.