Engine Manufacture TRIZ Cases

Flexible tripod anchoring cables stabilize a buoyant turbine assembly, resolving overturning moments from drag forces to enable maintenance access.

Wavy camber line ribs partition turbine blade chambers into stacked flow passages, reducing thermal expansion stress concentrations.

Stack preformed metal rings on a mandrel and apply hot isostatic compression to join them, enabling non-circular sections without intermediate bearings.

Segmented rotatable doors regulate bleed air flow to prevent booster stall and supply cooling air despite reduced pressure differentials.

A movable secondary nozzle flap dynamically adjusts the bypass duct exit area to reduce flow separation at the divergent region and improve thrust efficiency.

Segmenting the engine into independent cores decouples fan and core efficiencies, resolving critical speed limitations while maintaining torque transmission.

Offsetting the cowl interface circumferentially from the top apex prevents interference with wing slats during deployment.

Displaced foundation connection faces resolve instability between main foundations and rear frames, improving torque transfer during assembly.

A non-axisymmetric stator vane endwall contour modifies radial deviations to reduce secondary flow effects in gas turbine engines.

Rotatable blades replace heavy reversing doors to reduce system mass while maintaining effective thrust reversal.

A self-lifting exchange device couples to lifting ropes fixed to a wind turbine hub to handle stator segments directly at the nacelle location.

Side-by-side heat recovery steam generator layout lowers center of gravity to maintain stability on water-surface facilities.

Segmented ceramic and refractory metal cores create convoluted cooling passageways that reduce heat loading in the turbine blade tip region.

A nozzle ring with a groove connecting bores dissipates pressure pulses along the main body to reduce rotor blade excitations.

Splash ribs extend beyond flow turbulators to reassert fluid influence within the passage.

Chemical bonding between a polyurethane film and resin eliminates micropores and mold release agents, improving rotor blade durability.

Relief voids in circumferential flanges accommodate thermal expansion, reducing deflection and stress on adjacent components during gas turbine operation.

Merging the sound attenuation outer skin directly with connecting flanges eliminates intermediate closing components, reducing mass and manufacturing costs.

Curved valve body adjusts flow path width to reduce pressure loss from fluid separation in high-temperature rotary machines.

Changeable pigment gel coats enable defect inspection during wind turbine rotor blade manufacturing by shifting from transparent to colored finishes.

Segmented core assembly isolates impingement openings, eliminating cross-flow issues that degrade heat transfer efficiency.

Bolted overlapping annular rings replace welding to eliminate fatigue risks, lower assembly time, and minimize water penetration in wind turbine towers.

Angled vertical flanges with protruding connection elements eliminate welding distortion and reduce assembly time for wind turbine steel towers.

Segmented dual bearings constrain the shaft under axial and radial loads while accommodating engine growth through independent support portions.

Rocket ignition establishes supersonic flow conditions for efficient combustion, resolving overheating constraints while enabling autonomous hypersonic flight.

Chamfered stator vane rail edges redirect cooling airflow to reduce recirculation in gas turbine engines.

A stator vane segment shifts its trailing edge circumferentially near the hub to reduce suction surface stress without adding weight.

Segmented erosion-resistant coatings on gas turbine airfoils reduce flow separation and turbulence caused by leading edge blunting.

Helical strakes attach to wind turbine towers via adjustable support guides on longitudinal rods.

A partially coated gas turbine blade design applies thermal barrier coating selectively to pressure side and leading edge regions.

Integrated flange tabs on wind turbine blade bulkheads enable precise movement device placement without temporary steel plates.

A turbine blade root groove disperses torsional stress by overlapping contact surfaces to enhance rotor disk durability.

Stacking glass and carbon fiber plates creates a continuous spar cap that resolves insufficient structural integrity in cost-effective wind turbine blades.

Banked helical channel decelerates high-speed oil films to prevent pooling and leakage, resolving directional capture contradictions.

Axial lobe mixer integrates with turbine discharge to enhance total-to-static pressure ratio through secondary flow mixing.

Heated thermoplastic adhesive prevents resin flow that blocks perforations, maintaining noise attenuation.

Roughened mating surfaces reduce contact area to minimize heat transfer between metal parts.

Impingement cooling on the divergent flap reduces required airflow, resolving the contradiction between mechanical endurance and propulsion performance.

A wind turbine blade support structure uses seesaw elements to automatically equalize load distribution across belt elements.

Curved perforated intermediate walls yield to thermal expansion, reducing thermomechanical stresses on turbine blade leading edges.

Flexible fuel-cooled tubes maintain thermal contact with a thermoelectric device via a coil spring, reducing weight and complexity in hypersonic vehicles.

Integrated winches lift a circumferential carrier to eliminate external crane costs and logistical challenges during erection.

Segmented airfoils rotate on cables to adjust angles automatically, eliminating complex pitch control systems.

Segmented coverplate bends condition coolant distribution across high-temperature zones, reducing material mass while maintaining thermal performance.

Electroforming a sculpted metal edge shell over a composite airfoil body resolves the weight-reliability trade-off while reducing fan noise.

Strategic cooling hole coordinates direct coolant air to the turbine blade exterior surface for effective film cooling.

Segmented splined weights adjust mass distribution without disassembly, eliminating labor-intensive reassembly steps.

An annular one-piece acoustic insulation panel mounts inside a turbomachine casing wall using dismountable projecting members.