Engine Manufacture TRIZ Cases

Compressed flanges on pultruded layers bond spar caps, reducing weight and manufacturing re-work.

Compressible PET spacers ensure uniform adhesive thickness in wind turbine blade shear web bonding, preventing dis-bonds caused by thermal expansion or gravity.

Pre-formed flanges on a continuous structural component eliminate bond-line failures and reduce manufacturing cycle time.

A gas turbine fastener uses a deformable bellows outer wall to dampen pipe movement and maintain seal integrity.

Angled radial fins on an annular support hold oil-laden air tubes while accommodating thermal expansion and reducing weight compared to prior art.

An impact chamber containing a single impulse body with a specific clearance range effectively damps self-excited vibrations in aircraft engine gas turbines.

Securement retainers prevent radially outward translation of fan cowl panels, reducing pressure build-up and air leakage at the nacelle interface.

Chamfered grooves distribute stress along the surface to prevent crack initiation while ensuring complete void filling via negative pressure infusion.

Dual curvatures in the stator vane profile compensate for non-uniform thermal expansion, preventing distortions and leakages at operating temperatures.

Tapered pedestals create a throat in gas turbine airfoil cooling passages, accelerating flow to reduce mixing losses and manage heat loads.

Segmented seal baffles divide internal cavities to redirect cooling flows, reducing thermal gradients and mechanical stress on turbine components.

Segmented serration profiles reduce peak compressive stress concentrations in turbine airfoil attachment roots under centrifugal loads.

Optimized perforation pattern minimizes aerodynamic drag while maintaining broadband noise attenuation across engine operating conditions.

Segmented nacelle sections slide on rails to access core externals, using a guide pin and locking mechanism to secure the structure against aerodynamic drag.

Movable connecting members link a support frame to a wind turbine nacelle, eliminating time-consuming hole cutting in the outer housing.

Serial flow gas turbine auxiliary power units with non-parallel shafts reduce overall length and pressure drop while maintaining peak generator capacity.

Viscoelastic composite spacer accommodates centrifugal loading to prevent breakage while metallic conduit enables safe removal from rotor disk slot.

A lifting arrangement uses movable pulley arrangements interconnected by a rope to rotate wind turbine tower segments during hoisting.

Compressed heat conducting matrix between vane walls resolves fabrication complexity while improving thermal efficiency.

An augmentor flow splitter duct directs fan bypass air into an annular liner cooling path to manage thermal loads.

A sandwich composite airfoil uses a cellular core between ceramic fiber ply skins to enable complete densification of the preform.

A nacelle maintenance system uses a movable trolley and winch to transport components through an access door.

Segmented flow media with dedicated feed lines guide resin through composite laminate layers, reducing fill time by 38% and preventing defects.

A turbine seal slot retains spline seals while removing excess material to lower component weight.

Angled retention hooks on the blade outer air seal allow radial inboard movement during thermal growth, maintaining tight clearance with the blade tip.

Excluding outlier temperature measurements from the averaging process prevents measurement errors that increase NOx emissions and reduce operational efficiency.

Removing the obstructing hub nut allows blades to converge at the centerline, increasing horsepower by 75 percent without enlarging the frame.

Parallel connectors form a parallelogram mechanism that maintains sub-platform orientation, resolving the trade-off between adaptability and stability.

Axial tool device moves wind turbine bearing components to enable housing-free replacement without drive train disassembly.

An integrated ring maintains elevated cooling air pressure between turbine disks, reducing wear and stress.

Nesting the leading edge protector inside the hollow blade space eliminates surface projections that cause erosion damage and aerodynamic drag.

Etched grooves define micro-channel cooling passages to resolve manufacturing complexity and non-uniform temperature profiles.

Extracting stationary systems into a mobile unit reduces structural complexity while enabling internal thermal and ultrasonic de-icing.

A movably mounted impact cooling device deflects cooling air onto a rotor blade surface to manage thermal loads.

A front center body support assembly integrates a frustro-conical interface section to unify load paths and reduce part count.

Heavier overlapping shrouds increase sliding contact area to suppress blade vibration without complex pin structures.

Aft-curved bypass fairing expands flow path area to reduce pressure loss and improve fuel efficiency in low bypass ratio turbofans.

A turbomachine furrow channels fluid upstream of fixed blades to optimize the angle of attack.

Rotary blades pivot within the duct to divert thrust, eliminating obstruction from traditional doors.

Flexible parachute catchers minimize aerodynamic drag during rotation, resolving efficiency losses from rigid support frames.

Electromechanical actuators replace pneumatic systems to reduce weight and cost while optimizing engine efficiency through precise airflow control.

An external threaded stud on an airfoil tenon secures a shroud with a nut, reducing vortex bursting in smaller turbomachines.

Dual coolant circuits dissipate heat from rocket engine combustion chamber walls.

Convolution retainer arms secure turbine shrouds radially and circumferentially.

Countersink recesses hold turbine blade dampers, eliminating adhesive residue that reduces service life.

Segmented vacuum outlets in the root end assembly evacuate air pockets to ensure complete fibre impregnation and reduce manufacturing cycle times.

A seal assembly uses a carrier and tab to secure a rotational valve within a gas turbine casing.