Engine Manufacture TRIZ Cases

Particle separation slots divert cooling air through a rotating component to remove contaminant particles.

Segmented rotor blade portions align on a fixture system and weld via heated thermoplastic resin, eliminating bond line failures from adhesive curing.

An angled on-board injector locates a metering throat inward relative to the engine centerline to direct cooling airflow.

Lateral connecting flanges with frustoconical surfaces assemble ring sections to reduce blade angle dispersion and prevent ovalization.

A contra-rotating turbine engine positions bearings downstream from the turbine and upstream from the reduction gear to guide shafts.

Horizontal sliding rails move the main shaft out of the nacelle, eliminating factory transport and reducing repair downtime.

A damped turbine blade assembly positions a damper within asymmetric slots to reduce high cycle fatigue and prevent resonance in gas turbine engines.

Cooling slots on the rotor wheel direct fluid through guide grooves to enhance heat transfer while reducing maintenance workload.

Fluid channels and turbulators in the turbine casing dynamically adjust clearances, reducing thermal stress and improving efficiency.

A turbine blade tip shroud uses a variable fillet on the seal rail to increase contact area, reducing interface wear and bending stress.

A turbine casing alignment system calculates prediction offset values from reference point measurements to adjust component support positions.

Helical threads enable axial translation of a movable cowl portion, preventing misalignment and improving gas turbine engine reliability.

A control line guides the blade root for precise alignment while a crane lifts the heavy component to the rotor flange.

A bond paste cap with biased legs defines a dam at the blade edge to control bond width.

Tapered mounting elements join wind turbine rotor blade segments using non-linear contact surfaces to distribute mechanical loads.

Optimizing the diffuser case attachment position reduces bleed air pathway length while maintaining structural support for outer flowpath components.

A turbine airfoil uses radially non-uniform ceramic matrix composite wall thickness to manage local thermal stresses.

An airfoil leading edge uses non-continuous curvature distribution to tailor local heat transfer properties across the surface.

Embedding lightning protection conductors within blade shells using recessed connectors eliminates surface protrusions that degrade aerodynamic efficiency.

A tubular turbine shaft with a screwing portion and nut enables blind assembly of counter-rotating components.

Foam spacer material fills the bond gap between a tapered beam structure and blade shell in segmented wind turbine rotors.

Segmented shafts transmit torque via spherical bearings, preventing radial binding under heavy loads while mitigating fluid leakage.

Angled fins and cooling holes in an impingement insert redirect coolant flow within a turbine airfoil cavity, eliminating crossflow inefficiencies.

Optimized throat distribution reduces aerodynamic losses in gas turbine nozzles by managing secondary flows and resonant frequencies.

A turbine nozzle airfoil profile defined by specific Cartesian coordinate values creates smooth continuous arcs connecting discrete sections along the span.

Segmented core units with guide structures prevent breakage during mold separation while forming complex cooling passages.

A measurement device emits signals through a wind turbine blade spar wall to determine thickness using a reflective element.

Circumferentially diverging ramp in airfoil transition region prevents axial cooling slot displacement and plugging during investment casting.

Curved members in the segmented seal prevent core airflow recirculation between rotor and stator assemblies.

Non-uniform fin thickness improves heat exchange efficiency while reducing pressure loss and weight.

Radial fibre reinforcement distributes stress around apertures, preventing fractures in wind turbine blades.

Aircraft engine exhaust mixer with a radially mounted damper ring attenuates peripheral wall vibrations.

Relocating a skirt hole opening to a low-stress end surface resolves manufacturing stress while enabling efficient cooling air flow through internal channels.

Flatracks provide stable assembly surfaces for wind turbine components, reducing transport costs and logistical complexity.

Segmented aft bearings increase spool critical speed to resolve instability in high length-to-diameter gas turbine engines.

Asymmetric connector placement on stacked tubular tower elements resolves buckling risks while simplifying transport and reducing assembly time.

An extended nozzle plug body aligns exhaust plumes with free stream air to diminish cowl shocks and reduce sonic boom strength.

A gas turbine airfoil platform replaces sharp corners with a contoured surface to reduce stress concentration and improve sealing efficiency.

A pulley arrangement with a polyester receptacle lifts and lowers wind turbine blades using mechanical advantage.

A hydraulic turbine applies a water-repellent coating layer to running water surfaces, reducing friction loss from viscosity resistance.

A conduit bracket system couples a gas turbine fluid line to static structure using a damped intermediary mount that prevents fretting damage from vibration.

Segmented acoustic chambers with baffles attenuate low-frequency noise while bulkheads maintain structural integrity of the tapered inner skin.

Axially movable support pin and spherical bearing reduce attachment stresses on heavy land-based gearboxes.

Laser module measures distances around the turbine shell to generate an eccentricity plot, resolving restricted spacing in double-wall gas turbines.

Spanwise weft yarns interweave with chordwise warp yarns to resolve weight versus ductility trade-offs in gas turbine fan blades.

Universal movable hoisting lugs eliminate specialized tool requirements by extending through tower walls for versatile lifting.

A variable displacement pump driven by an anticipatory corrector eliminates excess fuel recirculation and associated heat dissipation during cruise flight.

Concave transitions and convex internal surfaces eliminate recirculation zones, reducing thermal stress on gas turbine vanes.

Segmented external cavities in the non-flow path region of fan blades reduce weight without requiring covers, preserving strength against bird strikes.