Engine Manufacture TRIZ Cases

Elastic spring elements guide heavy rotor blades during assembly, reducing alignment time and impulsive movements at elevated heights.

Internal airfoil cooling combines impingement from crossover passages with convection from a trailing edge pin array to reduce thermal stress.

A tapered connection piece bridges spar caps with different cross-sectional shapes and materials in wind turbine blades.

Interlocking edges on pultruded spar caps align components, reducing defects and improving stiffness control.

Ceramic matrix composite turbine ring sectors with radial clearance fit over metal support tabs to accommodate differential thermal expansion.

Oblique polyhedral cellular structures attenuate sound waves across various frequencies, reducing liner weight and complexity compared to uniform deep cells.

A serpentine cooling passage with radially aligned segments shields internal cavities in gas turbine flow path components.

Segmented evaporator and condenser modules recover water vapor from turbine exhaust, recycling steam into the combustor to improve thermal efficiency.

Clamp blocks transfer centrifugal forces from ceramic blades to the disk, resolving attachment reliability issues under high heat.

Chord-wise joint design with span-wise offset profiles connects wind turbine blade segments through overlapping engagement.

A turbomachine blade uses a trailing edge cooling circuit to redirect heat transfer fluid back into the body for reuse.

A pinned connector links an airfoil shell to a spar, enabling axial thermal growth between the components.

Intermediate carriers with flanges manage thermal expansion differences between ceramic matrix composite tracks and metallic carriers in gas turbine engines.

A chevron ring with a hollow portion modifies nozzle surface area to attenuate acoustic noise in gas turbine engines.

Defining a turbine arm profile with precise curvature radii resolves the contradiction between aerodynamic efficiency and manufacturing complexity.

A Z-notch edge profile on turbine blade tip shrouds reduces operational stresses through segmented geometric optimization.

A wind turbine nacelle crane boom rests against a dedicated support structure in its stowed position, reducing dynamic loads and wear from continuous vibration.

Splicing resonant cells overlap to form splice joints while fastening elements couple the segments for secure mechanical assembly.

Interpenetrated ceramic matrix composite and foam layers create thicker seals that resist shear failure while reducing purge air usage.

An automated drive unit rotates inner and outer rims to control heavy suspended loads, eliminating manual tag line handling risks.

Segmented isolator channels split supersonic airflow to minimize shock wave propagation, reducing viscous losses and weight penalties.

Segmented mold assemblies replace dedicated tooling for each blade size, reducing storage space and production lead times while maintaining shape precision.

A ceramic matrix composite discourager spans adjacent gas turbine components to prevent hot combustion gas ingestion into buffer cavities.

Turbine airfoil cooling holes use specific Cartesian coordinates to optimize fluid distribution, resolving design complexity from non-linear flow analyses.

Prefabricated fairing with elastomer layers bonds to wind turbine blades, preventing leading-edge erosion damage while maintaining aerodynamic profile accuracy.

Radial concrete ribs extend from a central pedestal to reduce material volume, improving heat dissipation during curing.

A reverse flow gas turbine core routes exhaust through radial mixing lobes to blend combustion products with bypass air.

Spacer elements in composite blade shells define controlled adhesive cavities, reducing material usage while strengthening glue joints.

Hydraulic arms compress tower segments to join structures, eliminating large crane costs and transport risks.

Segmented meandering flow paths eliminate cantilevered core protrusions, increasing rigidity while maintaining cooling performance.

Segmented ply lengths eliminate vacuum bag bridging and delamination risks while preserving structural strength in wind turbine rotor blades.

An intermediary bushing with elastically compressible elements transfers loads away from the sandwich structure, preventing creep-induced loosening.

Pivotable stays fold during insertion to bypass flange constraints, eliminating segmented manufacturing and complex inclination equipment.

Splitter blades with vortex generating structures manage airflow within gas turbine inter-turbine ducts.

Segmented three-dimensional cooling passages deliver targeted airflow to high-temperature zones, reducing thermal stress and improving structural stability.

Impulse bodies in guide vane cavities detune natural frequencies, reducing resonant vibrations that existing frictional methods fail to mitigate.

A turbojet nacelle deployment system coordinates cowl translation and flap rotation using slide bars and connecting rods.

Radial strut support for the connecting element eliminates thick cladding and gas flow blockages while distributing forces effectively.

Segmented geometry reduces profile and secondary losses while maintaining thermal resilience at high aspect ratios.

Rotating metering ring aligns apertures to control fluid flow, resolving uniformity defects in gas turbine engine bleed systems.

Segmented ribs form continuous L, T, or l-shaped cooling channels that distribute airflow to reduce thermal stress while maintaining structural integrity.

Controlled pre-stressing and shear pins direct radial and tangential forces into the wheel disk, reducing dynamic loading on screws.

Radial wall creates transverse obstacle reducing gas leakage and improving pressure drop.

A turbomachine scoop merges with the secondary flow path wall to extract cooling air without disrupting the primary airflow.

Segmented inflatable bags replace rigid cores to eliminate difficult core removal, enabling efficient production of complex hollow wind turbine blade profiles.

Serpentine cooling passages integrate airfoil and platform regions, reducing backflow and pressure losses while maintaining favorable pressure ratios.

Incompressible mounting spacers maintain repeatable seal compression, preventing air leaks and material damage from overcompression.

Removing pin fins from merging and outflow passages prevents machining damage while maintaining suction side wall strength.

Bendable support band with suction channels adapts to blade curvature, preventing water ingress during maintenance.