Engine Manufacture TRIZ Cases

A resilient member connects a floating vessel to a pile, allowing relative motion during installation.

A fiber-reinforced component uses a braided sleeve to form integral cooling channels within gas turbine engine structures.

Curved platform groove increases friction contact with damping elements to absorb vibration energy in gas turbine guide vanes.

Aircraft acoustic liner uses aerogel layer to attenuate lower frequencies, reducing panel thickness and weight while maintaining noise reduction.

Crisscrossing internal cooling channels reduce thermal stress and maintain structural strength in high-temperature turbine blades.

Segmented stator wind turbine generator attaches power conversion assemblies to stator segments, reducing nacelle size and maintenance complexity.

Segmented rotating frames allow the work platform to pass through immovable supports, resolving stability versus movement freedom.

Variable shear strength in vertical joints reduces mortar leakage and formwork complexity during assembly.

A reduction gearbox transfers power laterally through transversely extending gear axes to achieve speed reduction.

Cam-actuated rotating blades redirect bypass flow without obstructing the duct, reducing reversal door mass.

Amphiphilic block copolymers maintain low viscosity during infusion, eliminating the need for reactive diluents that degrade mechanical properties.

A steam turbine blade injects high-pressure steam through internal flow paths to suppress boundary layer development on the negative-pressure surface.

Positioning a supply vessel beneath the hull allows direct cargo transfer without port returns, resolving downtime and weather-related reliability issues.

Composite material tubes and grooved surfaces enhance heat dissipation while reducing weight in aeronautic engine stators.

A rub button with a defined head profile enables tip clearance measurement via borescope imaging, eliminating costly disassembly.

Segmented cascade structures match total flow areas across lateral sectors, minimizing secondary fluid flows and leakage paths that reduce landing performance.

Porous lattice structures absorb fan blade impact energy, reducing casing weight and fuel consumption compared to solid metal designs.

Oblique flange orientation aligns high static pressure with the throat location, maintaining positive backflow margin despite space limitations.

Segmented tanks separate gravity drainage from accessible emptying, reducing fire risk while maintaining efficient fluid removal.

Replacing rigid reversing gates with flexible sails reduces engine mass while maintaining thrust reversal effectiveness.

Adjustable counteracting forces compensate for vessel heave, pitch, and roll to safely pull wind turbine assemblies onto seabed support structures.

Triangular serpentine circuits increase up-pass density to cool high-temperature pressure sides without complex manufacturing.

Acute angle film cooling holes reduce cooling air momentum, preventing film blow-off and eliminating complex electro-discharge machining requirements.

A thermostructural composite envelope attaches externally to a rocket combustion chamber, containing radial deformations through an integrated reinforcing casing.

Acute angled cooling holes disperse air for film cooling on turbine blade tips, reducing engine efficiency penalties from coolant pressurization.

Dynamic piezoelectric grooves adapt shape to reduce erosion and fouling while facilitating ice detachment on aircraft propulsion systems.

Strategic placement of six distinct cooling hole sets optimizes heat dissipation while preserving structural strength against high thermal loads.

Staggered filmrow cooling holes direct air across transition zones to improve convective heat transfer on turbine airfoils.

Integrated attachment devices allow horizontal blade servicing, eliminating expensive lifting equipment while preserving aerodynamic properties.

Rotating calibration plate orifices direct cooling air radially onto the outer drum, eliminating shear losses from counter-rotation.

Smaller sub-fins cancel separation-promoting vortices from main fins, improving aerodynamic performance at wind turbine blade ends.

Parabolic fin profiles reduce head losses by expanding airflow cross-sections while maintaining heat exchange surface area.

Segmented cooling channels direct airflow through airfoil platforms to enhance heat transfer coefficients while minimizing pressure drop across the system.

Projection plates eliminate welding residual stress to improve fatigue performance and shear capacity in grouted mono-pile connections.

Foundation terraces support modular units to reduce construction costs while maintaining bow wave effects for efficient energy extraction.

Segmented protrusions bend the mixed layer to reduce shear forces, suppressing noise without the thrust loss caused by traditional mixers.

A stream diverter uses movable doors to redirect airflow between ducts, enabling precise fan operating line management in gas turbine engines.

Blade outer air seal cooling holes defined by normalized Cartesian coordinates enhance heat transfer.

Segmented ribs and interlocking tabs reduce thermal stress accumulation in ceramic matrix composite airfoils.

A metal motor housing connects to a plastic pump housing using segmented connecting pieces and axial projections for efficient caulking.

Spring-loaded adjusting means displace reinforcement parts to compensate for assembly inaccuracies, ensuring precise alignment and structural integrity.

A particle extraction duct removes debris from the primary flowpath before the compressor.

A blade damper body features identical first and second damping surfaces on opposite sides to provide full functionality in both flipped and unflipped orientations.

Segmented divergent wall contours suppress internal shocks and prevent flow separation, maximizing specific vacuum impulse for rocket engines.

A guide pin engages a converging entry slot to orient turbine shaft splines before axial assembly.

Diverging outer wall portions direct air away from the drain to prevent windage interference, ensuring efficient lubricant scavenging and component longevity.

Oversized compressor stages generate excess airflow that mixes with exhaust gas, eliminating bulky external blowers while maintaining SCR catalyst protection.

Opposed undulations generate rotating vortices within hollow turbine blade passages to enhance coolant mixing and heat transfer.

Angular sector with converging threading axes positions balancing weights simultaneously, eliminating tedious nut crimping and reducing manufacturing time.