Engine Manufacture TRIZ Cases

Segmented central tie rod enables independent tensioning of compressor and turbine areas, resolving strength trade-offs in divided housings.

Elongated pin holes absorb radial thermal expansion differences between nozzle rings, suppressing deformation to maintain parallelism and reduce leakage flow.

Segmented inner shell directs fan blade out damage circumferentially, preventing back sheet failure and maintaining engine reliability.

Segmented annular rings prevent oxidant infiltration by eliminating capillary paths.

Oval discharge slots at airfoil edges direct cooling airflow to manage thermal stresses in gas turbine engines.

Stamping recessed patterns into thin sheet metal increases buckling capacity and structural integrity, eliminating the need for heavy ribs.

Part-span connectors at 40-70% radial span segment the airfoil, resolving inadequate fluid flow management in high-heat environments.

Bonding a CMC sensor bracket to a turbine wall eliminates adhesive failure from thermal expansion mismatch.

Controller applies bias values to second actuator position demands, resolving positional mismatches between independent airfoil arrays.

Pin structures in airfoil cavities enhance convective cooling, reducing oxidation risks at high turbine inlet temperatures.

Intersegment seals bridge flow guide gaps to reduce gas leakage and accommodate thermal expansion differences in ceramic matrix composite blade outer air seals.

Segmented cover and airfoil sections use external turning cavities to redirect cooling flow, reducing pressure losses in gas turbine engines.

Segmented ventilation cavities in a turbomachine blade utilize Coriolis force to press cooling air against internal walls for targeted heat exchange.

Extending a 3D woven fiber core through intersecting walls reinforces the deltoid region, resolving fiber deficiency and improving mechanical properties.

An asymmetric diffuser with an oval-ended bearing cone eliminates backflow regions to reduce pressure loss and improve steam turbine efficiency.

Variable-radius securing plate increases contact area on groove walls, reducing surface pressure and preventing damage from vibratory loads.

A gimbal table isolates vessel roll and pitch motions from a spar buoy, reducing mating loads without large cranes.

Segmented cooling channels direct coolant to the trailing edge while outer layers thermally isolate the middle channel, preventing upstream heat degradation.

Scarfed cooling holes recess into suction walls to direct cooling air through angled channels, preventing hot gas path air from washing out the coolant.

A zip line guides electric cables through a horizontal wind turbine tower section, distributing weight to prevent damage during installation.

A rivet and washer assembly with nested countersinks maintains aerodynamic smoothness while applying continuous radial holding force.

Strategic turbine clustering converts aerodynamic interference into enhanced power output by exploiting local flow variations.

Segmented airfoil cooling circuit uses oxbow transitions to eliminate dead spots and reduce thermal stress.

S-shaped cooling passages interconnect interior channels and exterior surfaces using ceramic cores.

A blade insert couples between rotor segments to extend span length while maintaining aerodynamic profiles.

Radial serpentine circuits shield tip areas from high heat loads, preventing component failure.

Integrating a metering device with variable orifices reduces parasitic energy losses from excessive cooling air while maintaining vane temperatures.

A hollow truncated cone sealing element fully encompasses a connecting element guided through a conical passage aperture in the housing.

Incremental tower assembly via a rail-mounted carriage reduces crane lifting capacity requirements, lowering installation costs for large wind turbines.

An external platform assembly mounts to the nacelle front, providing a secure working surface for maintenance personnel.

An asymmetric lobe cross-over offset eliminates axial area variation in gas turbine exhaust mixers, reducing core stream losses and enabling weight reduction.

An asymmetric locking ring offsets its mass to counterbalance radial fingers, preventing vibration in high-speed turbomachines.

Inclined end walls on gas turbine blade segments align sealing air with the primary flow to reduce leakage and improve efficiency.

A recessed casing guides steam backflow along radial and axial walls to suppress separation at the bearing cone.

Leading edge concavities on gas turbine recuperator plates improve sheet positioning precision while maintaining structural stability under thermal loads.

Machining honeycomb blocks before rigid panel assembly simplifies manufacturing support panels for turbine engine casings.

Film cooling holes positioned by Cartesian coordinates create a protective boundary layer on blade outer air seals.

An angled nozzle with a curved conduit bend transition area minimizes turbulence and pressure losses by redirecting cooling air flow direction.

Segmented cooling pins with fillets eliminate dust stagnation zones, maintaining thermal efficiency in gas turbines.

Arcuate peaks and troughs stiffen ceramic matrix composite hangers to withstand operational stresses without altering material composition.

Locking sprocket engages crenelated shaft rims to prevent relative rotation, reducing bulk and assembly complexity of gas turbine engine couplings.

Enclosing metallic lugs within ceramic sectors reduces cooling gas needs and manages differential expansion stresses.

Ridges on a turbine component create cooling passages that shift inlet positions via a moving seal, reducing heat ingestion.

A fuel metering unit uses a movable element to obstruct a narrow flow section, preventing ice buildup in the metering slot.

Spherical fusing structure connects cone arms via diffusion bonding to absorb fan blade out unbalanced loads and prevent casing damage.

A bent main trailing edge cooling channel displaces flow off the camber line to reduce thermal stress and improve aerodynamic efficiency.

Turning vanes mediate airflow turning to reduce separation risk and shorten axial length between compressors.

A spray bar tip bushing with a support strut stabilizes the air gap to prevent non-uniform airflow caused by thermal growth and vibration.

Identical curved wall parts across tapered wind turbine masts eliminate multiple molds, reducing production costs while maintaining structural stability.

A rocket motor employs a fragmenting nozzle system to switch between boost and sustain modes, overcoming limitations in rapid mode adaptation.