Engine Manufacture TRIZ Cases

Cruciate protrusions on a gas turbine stator shroud increase surface area for enhanced heat exchange.

Inclined protrusions and recesses guide powertrain housing contact, preventing surface treatment damage.

Deflectors in the airfoil assembly redirect tangential airflow to reduce windage losses and increase power output.

Modified trailing edge contour on turbine transition ducts reshapes hot gas flow paths through optimized pressure and suction sides.

Curved ribs and canted turbulators enhance coolant flow to reduce thermal expansion stress in turbine blades.

An undercut around radial cooling holes prevents plugging from tip rubbing, maintaining reliability.

Elastomeric seals bridge gaps between adjacent fan nozzle petals, preventing radial air leakage that degrades engine performance and fuel efficiency.

Radial tabs on an annular spring maintain clamping force on a variable turbine guide device despite high exhaust gas temperatures.

Actuated blade flaps generate damping forces to reduce tower base loads without overloading pitch systems.

A modular nacelle design segments the structure into auxiliary units to enable individual assembly and encapsulation during transport.

A gas turbine airfoil cooling passage network uses oblique impingement surfaces to deflect and distribute cooling air through the wall structure.

A liner assembly uses a perforated core to attenuate sound waves while maintaining a smooth facesheet.

A supercritical carbon dioxide gas turbine engine uses independent shafts to drive separate compressor and fan assemblies.

Segmented planetary carrier halves and integrated bearing caps enable radial axle insertion for wind turbine gear trains.

A clamper plate secures a wind turbine tower flange to a pedestal using embedded bolts and additional fasteners.

Dynamic blocking devices connect the nozzle to movable cowls, reducing cylinder length and stress while avoiding turbine bursting risks.

Curved flow director blades eliminate dead bands and prevent static lockup, enabling accurate low flow rate measurement down to 0.015 L/s.

Helical elements in turbine vane intakes swirl cooling air to boost heat transfer efficiency and reduce energy loss from reinjected gas.

A machinable coating applied to seal slots provides a smooth surface finish ready for precision machining.

Hydraulic actuators adjust rotor position to reduce blade tip gaps, raising combustion gas temperatures and improving partial load efficiency.

Segmented float units detach from the center float when wave forces exceed thresholds, protecting generators from mechanical damage.

Sliding elements in the strut connection allow radial movement to compensate for differential thermal expansion, reducing structural stress on the nozzle wall.

Inlets use fins to mix boundary layer flow, reducing system complexity and volume while maintaining performance.

Welded titanium strips join acoustic cover and structural layers to prevent debonding and galvanic corrosion in gas turbine applications.

Segmented carrier and selective drive units move nacelle components parallel to the rotor axis, resolving poor adaptability in existing handling systems.

An axially translating forward structure adjusts the inlet area to manage mass flow across supersonic and subsonic flight regimes.

Internal walls divide the web foot into chambers to spread loads, preventing adhesive bond line failure in wind turbine blades.

Inclined flow splitter slots split propellant into fine jets, increasing contact area and combustion efficiency in compact rocket engines.

An S-shaped nozzle vane cross section increases the opening moment to reduce hysteresis and improve control stability at low speeds.

Pre-positioned clips align shear web inserts before paste injection, eliminating manual adjustment delays during wind turbine blade assembly.

Kerfed solid membranes conform to curved surfaces, solving application limits on polymer composites.

A scroll compressor spiral end region features a conical cut design that reduces wear and friction between interleaving spirals.

Nested translating and rotating members in the hinge assembly reduce weight and complexity while enabling deployment.

Asymmetric diffusion geometry controls vortex formation and improves film coverage on gas turbine airfoils despite uncertain stagnation lines.

Surface irregularities on a turbine rotor shaft increase the heat exchange area, reducing thermal response time differences with the casing.

Segmenting cooling supply into platform and direct sources balances heat loads across airfoil bodies while maintaining precise exit temperature control.

Offset carrier gaps and overlapping track segments create a tortuous gas path that reduces cooling air leakage into combustion products.

Turbine blade airfoil conforms to scaled Cartesian coordinates, resolving design complexity while enhancing stress resistance and performance predictability.

Integrating an annular combustion chamber eliminates inclined nozzles, preventing ejection engines from falling and reducing thermal detectability.

Central submerged inlet ensures reliable oil delivery across all flight orientations, eliminating complex peripheral outlet configurations.

Hinged connections between tower segments enable transport of oversized components within standard road limits.

Reduced rigidity at shroud contact ends enables elastic deformation that compensates for assembly variations, ensuring uniform contact reactive forces.

Pre-formed blade wall sockets eliminate complex drilling operations, reducing installation labor while securing lightning receptors.

Ground-level preassembly of modular supply modules containing climbing devices and power lines eliminates hazardous high-altitude installation work.

A sealing surface member bridges the axial seal and forward hook of a blade outer air seal.

A modular mounting system with a moveable coupling enables rotation of underwater power generation apparatus about a mounting axis.

Thermoplastic resin components fuse via thermal welding to replace fatigue-prone adhesive bonds, reducing manufacturing time and costs.

An inlet duct lip integrates an exhaust conduit routing turbine gases around the perimeter, resolving bulkiness constraints in aircraft nacelle integration.

A blade outer air seal uses a non-uniform abradable coating that achieves uniform thickness during service to reduce thermal gradients.