Engine Manufacture TRIZ Cases

Tapered inclined surfaces abut to seal the annular member support interface, suppressing high-temperature oxidation reactions.

Pivotable cooling panels in a wind turbine cooler increase heat transfer surface area, reducing transport volume and assembly complexity.

A turbine blade airfoil profile uses specific Cartesian coordinates to define a flattened intermediate section that controls tip vortices.

A single unducted rotor engine operates at an advance ratio above 3.8 to achieve net efficiency of at least 0.8.

Flow-forming a blank over a mandrel forms a near net-shape annular support structure, reducing material wastage from extensive machining.

Asymmetric lattice ribs create cancelling vortex flows that prevent high-temperature gas mixing and enhance rear edge cooling.

Segmented chevrons mix high velocity core exhaust with ambient air, reducing supersonic jet noise without aerodynamic losses.

Angled wall and varying diameter funnel redirect cooling gas flow, reducing debris bonding on turbine blades while maintaining thermal protection.

Nested ceramic matrix composite shields and co-processing bonds protect vane units from thermal damage while managing structural complexity.

Outer and inner insert pins accommodate radial growth differences between turbine shroud components.

Varying thickness profile at the trailing edge adjusts pitching moment while minimizing drag and vibration from airflow separation.

A turbine vane airfoil profile defined by specific Cartesian coordinates optimizes gaspath geometry to minimize aerodynamic losses.

Mounting the crane on the tower before transport allows pre-site certification, reducing installation delays from weather.

A gas turbine transition duct uses a curved geometric profile to minimize stress concentrations.

Chamfering the suction-side platform edge directs reused cooling air to the transition region, resolving thermal fatigue and energy loss trade-offs.

Depressed portions on the diaphragm inner ring modify steam flow paths to reduce circumferential pressure differences in axial flow turbines.

Asymmetric nozzle vane design adjusts position under exhaust pressure to narrow the gap between the vane and turbine housing side wall.

Hybrid support ring with high and low CTE members manages radial expansion for gas turbine blade stages.

A tailored composite core integrates structural functions into a rotor blade airfoil using reticulated adhesive bonding.

Upstream fairing attachment reduces thermal stress from temperature gradients while maintaining aerodynamic continuity.

Factory milling of a resin leveling layer on precast concrete tower segments eliminates weather-dependent on-site leveling and reduces construction time.

A fiber-reinforced polymeric shell assembly modifies turbine stay vane geometry through injected polymer casting.

A centering plate replaces complex dovetail joints with longitudinal and radial screws, reducing assembly complexity while ensuring precise blade positioning.

A locking nut provides mechanical interlocking to prevent loosening while allowing reversible maintenance of the rotor blade connection.

A tip shelf discourager creates a pocket separating cooling air from high-pressure gas flow, preventing premature mixing and maintaining thermal durability.

Radial concrete ribs and post-tensioning reduce thermal cracking risk by improving heat dissipation during construction.

A composite joint uses tapered ends with modified material properties to reduce stress concentrations at the thin end.

Nested lateral cavities and conduits distribute cooling air across the blade, reducing thermal stresses while managing device complexity.

Metal plates clamp the composite blade root using a screw and nut, distributing centrifugal loads across the contact surface to prevent stress concentration.

V-shaped grooves channel cooling air through the seal to lower component temperatures and prevent overheating near the core flow path.

Cutting recycled wind turbine spars into uniform boards and connecting them with rings yields a high tensile strength mat that adapts to landscape contours.

A satellite gear drives a secondary fan within a compact power transmission module, reducing size and mass while maintaining rotational speed transformation.

Segmented airfoils orient bleed airflow into the bypass passage, reducing pressure losses and flow disturbances.

A seal assembly uses a dovetail interface and overwrap to secure components within gas turbine engines.

Calculating offset amounts for a center guide pin eliminates temporary assembly iterations, reducing steam turbine alignment time.

A collapsible fan track liner assembly uses a honeycomb core and mechanical fasteners to secure the structure without adhesive bonding.

A multi-wall blade cooling circuit directs radial air flow through dedicated pressure, suction, and leading edge cavities.

A rotatable support arch transfers torque between high and low pressure spools to a stationary frame.

Stator flange groove creates recirculating flow to restrict gas leakage between rotor and stator components.

Adjustable elastic mechanism provides precise clamping force for safe wind turbine blade storage without friction variability.

Dead-end cavity stiffener ring reduces vibrations and thermal stress in gas turbine exhaust mixers.

Segmented movable vanes reduce shear layer velocity gradients to prevent rotating stall cells that cause asynchronous high cycle fatigue on turbine blades.

Three-dimensional spiral and Z-shaped cooling passageways route airflow through curved paths to increase effective heat dissipation area.

Segmented damper pins conform to complex platform shapes, resolving inconsistent damping and resonance risks in turbomachine blades.

Curved turbine airfoil passages use centrifugal force to separate particulates, preventing flow disruption and thermal stress on components.

Overlapping blunting plates absorb impact energy, preventing blade penetration and reducing casing complexity.

Separate manufacturing of swivel ring and integral collar reduces costs while maintaining extraction pressure control precision through accurate alignment.

A turbine bucket airfoil platform intersection features a contoured cooling conduit turn that mitigates thermal stress concentrations.

Concentric turbine housings with hermetic sealing reduce leakage and assembly complexity while maintaining axial mobility.

Series-connected internal cavities in a turbine blade homogenize temperature distribution, reducing thermal stresses caused by high combustion gas temperatures.