Engine Manufacture TRIZ Cases

Thermoplastic edge welding joins composite blade elements without metal fasteners or adhesive curing, cutting weight and simplifying assembly.

Fuel routed through vane, strut, and shaft passages cools the aft bearing while supplying heated fuel to combustion with fewer parts.

Adjustable lifting support holds post-moulding wind turbine blades securely, improving access while reducing crane hazards and scaffold time.

A two-piece nozzle ring forms the needed flow contour for low-blade-height radial turbines without weakening core gap stability in casting.

Inlay beams through mounting insert holes reinforce the blade root, improving load transfer and service life under high stress.

Cooling holes vary by load zone in a gas turbine web to cut stress concentrations while preserving cooling performance and manufacturability.

Segmented feed and axial flow channels guide cooler air through a turbine vane to limit inner diameter heat-up and protect metal temperature.

Layered structural and impact-absorbing casing sections redistribute blade impact energy to contain failures with lower force, weight, and drag.

Tapered damper bodies in rotor blade pockets dissipate vibration through friction, cutting HCF stress in integrally bladed rotors.

Integrated splice recesses and pads replace flexible honeycomb parts in aircraft nacelles, cutting cost and simplifying installation.

Discrete stilt projections engage turbine disc teeth to limit blade inward drop at կանգstill while reducing mass, stress, and root complexity.

Using inlet airflow to cool heat exchanger vanes upstream of the fan avoids bypass-air off-takes, preserving thrust, surge margin, and compactness.

Guiding elements and tensioned connection lines synchronize wind turbine components during lifting, reducing relative movement for stabler assembly.

Spherical articulation lets nacelle sliders rotate in the track, cutting edge contact stress, wear, and damage in thrust reversers.

Chamfered stepped pins create a controlled interference fit between CMC parts and metal hangers, reducing edge chipping and assembly damage.

Direct flange-to-flange sector joints with elastomer seals improve mold rigidity and cut bolt handling time in composite fan casing manufacture.

Angled woven fibers with honeycomb or foam layers absorb blade-out energy, reduce peak forces, and limit bulge in gas turbine containment.

A recessed stator vane creates a gas leakage path that cuts back pressure and reduces wake and bow wave interference in turbine flowpaths.

A sealed drain path guides rainwater away from the blade work zone, keeping wind turbine repairs dry in bad weather.

A decoupled outer ring with honeycomb and foam layers redistributes blade-out forces in gas turbines while limiting drag and structural weight.

A contoured hollow spool shaft shifts thread load away from the highly loaded end, reducing fatigue initiation without added mass or complexity.

Trailing-edge slots and a baffle insert cool turbine nozzle vanes to manage thermal gradients, cut local stress, and improve durability.

A dual-adhesive fan blade bond uses flexible tip and durable root regions to resist impact, moisture, and disbond growth.

A nested structure link and door link cut bypass flowpath drag while preserving blocker door deployment in aircraft thrust reversers.

A pitching system rotates a lifted rotor blade to counter wind-induced tilting, improving stability and extending installation windows offshore.

Composite fan blades paired with a reduction gearbox enable larger turbine fans with lower speed, lower pressure ratio, and improved thrust efficiency.

Intermediate flanges and a lower-supported lift stack wind turbine tower sections with smaller cranes, cutting installation time and cost.

A decoupled outer ring with honeycomb or foam redistributes blade-out forces, cutting containment weight and keep-out zone needs.

A movable inner body opens or closes inner and outer inlet passages to match aircraft engine mass flow across subsonic and supersonic flight.

A movable splitter leading edge adjusts core and bypass airflow split, improving turbofan performance across changing operating conditions.

Angled fiber layers with honeycomb or foam improve blade containment by absorbing impact energy and limiting bulging in gas turbine casings.

Metering holes lower coolant pressure before impingement, cooling turbine CMC parts while reducing thermal gradients and damage.

Separately moulded leading- and trailing-edge spar parts avoid rigid mandrel removal, cutting defects, cost, and assembly complexity.

A slanted septum and perforated face split each honeycomb cell into resonant chambers, cutting turbine exhaust noise with simpler manufacturing.

Notched porous blade tip coating wears away on housing contact to control radial gap losses while limiting damage and debris.

Operating history from original turbines provides site-specific meteorological estimates for more precise replacement-turbine placement.

A layered gas turbine casing separates structural and impact-absorbing materials to dissipate blade energy and reduce casing weight.

Overlapping laminated blunting plates with honeycomb volumes address concentrated blade-impact forces and soft-wall bulging while absorbing energy.

Axial hairpin features absorb dislodged-blade impact energy and redistribute forces, balancing peak loads and casing deformation in gas turbine containment.

Lateral drive pads and one gear shaft let a gas turbine accessory gearbox drive two accessories in less space.

Curved sealing tongues and matching slots help produce CMC turbomachine assemblies with fewer defects and less tool wear.

Foam or honeycomb within a gas turbine containment ring absorbs blade-impact energy and redistributes forces to reduce peak stresses.

A frustoconical wedge centers coaxial turbine-engine shafts while reducing vibration and simplifying assembly and disassembly.

Conductive fibres can heat under lightning strikes; a bendable mesh connector routes current to a grounded down conductor while easing blade handling.

Trailing-edge cooling uses radial turn passages, obstructions, and coolant reuse to reduce flow demand while supporting sharper blade edges.

Outwardly extending plenum projections alter resonant frequencies, limiting pressure waves and noise while protecting the compressor.

Segmented main and auxiliary nacelle units support separate transport and site assembly, helping accommodate larger components without one oversized shipment.

High-temperature turbine rubbing can wear abradable coatings; vertical cracks in segmented FSZ improve toughness and protect underlying metal.