Engine Manufacture TRIZ Cases

Internal bypass flow channels cool turbine blade fillets via pressure-driven convection, eliminating surface holes that cause fatigue cracks.

Cantilevered rotor blade attachments integrate directly into segmented disk structures to reduce weight and simplify cooling passages.

Temporary slings wrap around rotor blades to lift and orient the assembly, eliminating fixed lifting lugs that complicate setup.

A locally extended portion in the cooling hole directs cooling air to impinge upon the leading edge, reducing cross-flow and heat load.

A travelling car features a movable deck portion that carries and positions wind turbine components vertically along the tower structure.

A ceramic matrix composite turbine flowpath uses a centering spring and radial pins to maintain position.

A circular collar maintains blade root geometry during mounting to align bushings with hub apertures, preventing stay bolt failure from ovalisation.

Floating platform integrates pump and buoyant structure to generate pressurized fluid on-site, eliminating high-pressure pipeline costs.

Segmented CMC turbine shroud sectors mount on a modular spacer and flange support structure to reduce part count and manage cooling airflow.

Segmented nozzle orientation directs high-pressure jets at specific wall zones, eliminating manual intervention needs.

A nested coverplate creates a winding cooling passage in the turbine rotor blade platform, improving heat removal while reducing manufacturing complexity.

Optimized turbine blade profile defined by specific Cartesian coordinates enhances aerodynamic efficiency and reduces turbulence.

A compressor turbine blade airfoil profile defined by specific Cartesian coordinates to optimize aerodynamic and structural performance.

Adjustable spacing between clustered cycloidal wave energy converters cancels reactive forces, reducing mooring complexity in deep ocean environments.

Elastic deformation compresses wind turbine tower sections to reduce vertical height, avoiding legal transport limits and minimizing sectioning costs.

Segmented platform with radial lips limits axial dimension while preventing intrados to extrados air recirculation.

A monolithic heat exchanger core transfers heat between compressed air and turbine exhaust using spiral parting plates.

Curved radial channels in support platforms distribute thermal and aerodynamic loads to reduce stress concentrations in ceramic matrix composite airfoils.

Anti-rotation pegs and adjustable retention pegs secure gas turbine disks, correcting rotor imbalance while simplifying assembly.

Elevator carriage raises nacelle along tower and pivots rotor horizontally, replacing expensive lattice boom cranes.

A deployable fairing pivots away from the central axis to create space for thrust reverser doors.

Inclined bottomed recess walls align ejection holes with the blade contour to reduce combustion gas separation and aerodynamic loss.

Segmented rollers replace sliding plates to eliminate thermal deflection and hysteresis, maintaining precise cooling air flow control.

Segmented tower segments and balanced weight distribution stabilize the lifting assembly against high winds, reducing downtime.

A sliding seal body accommodates thermal growth between rotating components, preventing wear and leakage in gas turbine engines.

Laser-machined microchannels in turbine bucket tip shroud rails dissipate heat from high-temperature zones, preventing rail failure.

Segmented first and serpentine passages in the leading edge cooling channel direct cooling fluid radially inward to reduce blade outer air seal temperature.

Center body with de-swirl vanes expands exhaust gas mean diameter to reduce tangential velocity.

Double polymerization followed by post-cure perforation reduces panel weight and manufacturing costs while maintaining gas turbine noise attenuation.

Axial cooling channels with film cooling distribute fluid through turbine airfoil trailing edges to maintain uniform temperature and extend lifespan.

Segmented vane airfoil profile with optimized trailing edge cutback reduces secondary flow losses and improves thermal management.

Radially staggered heat transfer protrusions on the inner surface of a cast turbine nozzle enhance cooling effectiveness in narrow airfoils.

Segmented assembly traverse reduces crane dependency and safety risks during tendon installation.

Segmented thick and thin flow structures in a variable width channel redistribute mass flow to resolve boundary layer convergence issues.

A climbing device uses a swivel joint and telescopic assembly to lift wind turbine components along the tower structure.

Relocating the cold source heat-exchanger to a movable thrust reverser surface eliminates aerodynamic disturbances from fixed scoops, reducing fuel consumption.

Repositioning the bleed inlet downstream of the combustor reduces turbine pressure ratio, enhancing thrust recovery while maintaining surge stability.

A perforated baffle uses a vaporizable sound absorbing material to reduce noise while preventing CMAS deposits from forming on hot gas path components.

Segmented drive train housings enable direct technician access to elastic couplings, reducing maintenance time and improving gearbox reliability.

ACME threads on shaft flanges allow hydraulic tools to apply pulling force for room temperature disassembly, eliminating machining recesses.

Separating the turbine housing from a cover member simplifies the core shape, reducing production costs while maintaining pressure equilibrium through a gap.

Resistive welding of thermoplastic shear clips resolves misalignment issues and reduces bond line failure risks in wind turbine rotor blades.

Circular heatsink integrates emissive surface area to conduct heat away from components, eliminating complex liquid cooling systems.

Offset gas generating cores enable a larger fan shaft diameter in this gas turbine engine design.

Segmented spoiler design separates base mounting from aerodynamic attachment, enabling post-construction drag reduction without complex manufacturing.

Streamwise airfoil grooves guide cracks to prevent uncontained fragment release in gas turbine engines.

Segmented wedge and spline seals utilize centrifugal force to block fuel gas leakage while maintaining efficient rotor blade fixation.

Inclined ridge patterns on abradable surfaces redirect blade tip leakage airflow, reducing energy loss while managing wear through progressive zone adaptation.

Offsetting the grinding centerline creates an eccentric blade outer air seal that reduces gas leakage by maintaining consistent contact with rotating blades.