Engine Manufacture TRIZ Cases

A turbine blade airfoil uses a segmented metallic spar and ceramic heat shield to manage thermal loads.

Coupling pins distribute centrifugal loads across segmented connection points, preventing slip between rotor disks while enabling center of gravity balancing.

A conical flange bolted joint design secures rotating gas turbine wheels without through-holes in the rotor structure.

Rotating the yaw bearing ring redistributes load on wind turbine teeth, avoiding costly nacelle lowering for repair.

Concealed discharge devices with comb-shaped contact plates divert lightning currents to the hub, avoiding bearing electrical loads and surface defects.

Nested containment structures capture detached fan blades to prevent downstream damage while reducing engine weight and drag penalties.

Laser-textured silicon carbide barriers prevent impurity migration and maintain amorphous thermally grown oxide phases, extending gas turbine component life.

Z-shaped closeout membrane accommodates thermal expansion between movable liners, preventing combustion gas leakage at segment interfaces.

A remote robotic repair system uses virtual reality equipment to control manipulators inside wind turbine nacelles.

Shaft vents deliver airflow from the nosecone inlet duct to heat exchangers, managing thermal loads within constrained packaging space.

Laterally inclined duct axes and asymmetric diffusers merge cooling filaments to form a gapless film, reducing hot-gas damage.

Hinged moveable panel absorbs roll and torque loads through coupling portions, reducing structural displacement and propulsor weight.

Lateral carbon fibre layers on pultrusion plates ensure electrical conductivity through the spar cap thickness.

Standardized connectors join pre-assembled polyhedron panels into buoyant floaters, reducing manufacturing complexity and assembly time.

Internal 3D printed organic vibration stiffeners shift compressor blade natural frequencies without altering external aerodynamic contours.

Thin flexible adhesive supports join curved acoustic honeycomb sections, preserving sound properties while maintaining strong bonds.

Sliding damper contacts inner wall to attenuate vibration while avoiding vent holes to prevent clogging.

Replacing heavy fixed platforms with a dynamic mobile guide reduces tower weight and improves fatigue strength while enabling efficient component hoisting.

Porous lattice structures permeated with lubricant mitigate heat buildup and reduce wear in turbomachine seals.

Inflatable pneumatic chamber surrounds wind turbine blade to immobilize it without direct contact, preventing surface damage during lifting operations.

Radially offset outward and return legs in a multi-wall blade redirect coolant flow to reuse air, maximizing heat capacity while managing system complexity.

A coupling uses a non-circular connection profile to transmit torque through mechanical engagement.

Web head reduces flow cross-section upstream of deflector to accelerate coolant and minimize separation in turbine blade cooling channels.

A gas turbine airfoil core assembly uses purge slot protrusions to form cavity extensions for enhanced cooling.

Multiple inlets feed a serpentine cavity to cool turbine vanes, resolving insufficient heat transfer from single-inlet designs.

Flexible ring gear mounts accommodate misalignment without adding weight to the static structure.

Radial accessory gearbox placement resolves thermal exposure and driveshaft length trade-offs while maintaining compact packaging.

A gyroscopic stabilization device counters wind-induced vibrations to enable precise component placement without manual worker intervention.

Protuberances on the casting core hold the insert in place and form communication holes directly, eliminating post-casting drilling operations.

Distinct guide dynamics detune blade vibrations across multiple resonant frequencies while balancing centrifugal loads.

A segmented upstream cover minimizes fluid turbulence and head losses in turbomachines, preserving engine efficiency.

Defined turbine blade profile using specific Cartesian coordinates to reduce turbulence and mechanical stress for improved engine reliability.

Segmented turn cap design merges separate suction and pressure side air streams, reducing turbulence and pressure loss in gas turbine airfoil cooling passages.

Fins distributed over 180 degrees of the casing act as an expansion chamber to reduce noise up to 20 kHz while maintaining thermal dissipation.

Counter vortexes collide with harmful interaction vortexes to relieve flow instability and enhance cooling film formation on gas turbine blades.

Local quality principles shape asymmetric arms and compensating surfaces to eliminate heterogeneous cross sections, reducing pressure losses.

Active clearance control system uses debris-laden air from an inlet particle separator to cool the turbine case and maintain tip clearance.

Non-concentric spool assemblies with turning ducts enable higher operating pressure ratios while maintaining manufacturing tolerances in compact engine cores.

Internal cooling air passages in bearing races provide convective heat transfer to isolate components from hot exhaust gases and prevent thermal damage.

A turbine rotor blade airfoil shape defined by specific Cartesian coordinates to enhance aerodynamic efficiency.

Airfoil-shaped mesh members in aircraft fuel screens eliminate recirculation zones, preventing deposit accumulation and pressure drops at high temperatures.

Segmented nozzle geometry with a monotonic expanding cross section enables independent control of mass flow and exit velocity while minimizing pressure loss.

Segmented metal hook resolves attachment strength issues in composite fan cases, while graded honeycomb liner directs debris for secure retention.

Extracting folded gates into external housing eliminates pressure losses and drag caused by inactive gate placement.

Segmented transition duct joints allow relative movement along multiple axes, preventing stress buildup from thermal expansion.

Adaptable gas turbine disassembly methods reduce maintenance time and cost by enabling selective component removal instead of full teardown.

A reverse core engine design uses pivoting doors to block bypass and core exhaust flows for thrust reversal.

Mechanical deformation secures delaminated mesh without adhesive curing, eliminating engine downtime and preventing mesh occlusion.

Relocating actuation rods outside the fluid conduit eliminates flow disturbances and improves propulsion efficiency.

A removable winch hoisted by permanent nacelle power lifts heavy components without oversized cranes.