Engine Manufacture TRIZ Cases

Parallel upper stages divide mass flow to maintain stable low-pressure compressor operation at partial load.

A gas turbine engine mounts a propulsion unit and core engine on non-parallel axes to simplify maintenance access.

Longitudinal translation of the secondary cowl adapts the ejection section to engine speeds, reducing drag and acoustic emissions.

A transverse accessory gearbox arrangement reduces nacelle volume by positioning gears perpendicular to the drive shaft.

Segmented cooling holes use flag regions to form vortices that increase heat removal without reducing wall thickness or compromising structural integrity.

Advanced transition duct accelerates combustion gases using internal geometry to eliminate stationary vanes, reducing engine complexity and length.

Recesses in the outer wall direct cooling fluid closer to the exterior surface, mitigating thermal barrier coating spalling and extending operational lifetime.

A rectifying structural body integrates a metal plate with vacuum thermal insulation to manage airflow and heat transfer.

Separating partition with sliding connection increases surface area for acoustic panels in compact thrust reversers.

Defined aerodynamic profile reduces turbulence and mechanical stress while maintaining manufacturing precision for low-pressure turbines.

Strut strips form corner and streamwise vortices that suppress separated flow, reducing pressure loss in gas turbine exhaust diffusers.

Segmented translating inlet uses slider beam to manage airflow efficiency while reducing structural complexity.

Grooved platform structure directs cooling air to feather seals, preventing overheating in high-temperature gas turbine core flow paths.

A handling arrangement protects wind turbine rotor blade add-ons using shaped covers and non-compressible load-bearing material.

Floating bearing connection with axially displaceable sleeves simplifies large blade assembly while reducing bending loads and connection gaps.

Transversely oriented guide surfaces constrain shear web displacement during mould closure, ensuring accurate bonding to the leeward shell.

A turbine vane uses specific cooling hole coordinates to deliver coolant flow to critical surfaces.

An elliptical trailing edge reduces velocity distribution defects and total pressure loss while maintaining mechanical strength without increasing weight.

Sectorial equipotential bonding via copper or aluminium meshes prevents electric arc jumps across thick, infused composite stacks.

A stator device uses a pre-curved rearward connecting surface to ensure full contact with the turbine casing receiving surface.

Axially offset distributors integrate heat exchangers into turbine inter-blanket platforms, resolving space constraints in secondary duct cooling.

A floating vertical axis wind turbine uses a releasable mechanical coupling to detach the energy converter for modular replacement.

A floating installation vessel uses a dedicated nacelle support structure and blade moving system to connect blades to the hub before lifting the assembly.

Movable backing sheets adjust cavity depth in acoustic liners, resolving the trade-off between multi-frequency noise suppression and increased liner weight.

A rotor blade tip incorporates a convex-walled squealer pocket to divert leakage airflow, reducing vortex induced losses without increasing rotor mass.

Internal channels enable hybrid cooling to resolve insufficient thermal discharge in geared fan engines.

Recessed vane tips absorb elastic stress and prevent direct contact, ensuring consistent leakage across turbocharger units.

Dividing the shroud edge passage into three or more sub-passages reduces pressure loss and improves cooling air efficiency for the first stage stator vane.

Orthogonal cross-flow paths cool hot compressed air, preventing thermal stress on engine components during high-pressure operation.

A nacelle design featuring a fixed and mobile cowl with a reverser flap that translates and rotates, coordinated by a drive mechanism.

Alternating chevron and indentation rings interlock on turbojet nozzle doors to reduce jet noise while preserving exhaust roundness.

Low hub-to-tip ratio axial turbine reduces thrust loads, resolving bearing energy loss at high expansion ratios.

A flow diverter redirects air from a closed bleed duct inlet to suppress dynamic pressure oscillations in gas turbine engines.

End wall contoured pedestals stabilize cooling airflow within gas turbine airfoils by matching curved end wall geometry.

Convex nozzle parts point-support thrust bearing pads to enable free tilting, reducing metal temperature at high pressures.

A rigid template aligns rotor blade surface features using fixed base and marker tail connections, eliminating soft template wrinkles that cause misalignment.

Bobbin-type transfer tubes route compressor bleed air through spherical seals to cool turbine shrouds, preventing pinch points during hot running conditions.

A polymer damper between spring coils and a pivot pin absorbs motion through friction, preventing pawl bouncing during windmilling.

Segmented turbine shrouds block gas leakage through combustion exhaust by using ceramic blade tracks and nested retainer blocks to secure components.

A serpentine airfoil uses a flow control feature to direct cooling air and prevent resupply backflow.

Grooves channel cooling air from the pocket to the chamfer, stabilizing the film against hot gas leakage.

Automated spring-loaded locking prevents accidental separation during installation, eliminating personnel exposure to heavy moving loads.

Porous inserts in turbine airfoils create tortuous paths that raise pressure drop and heat transfer while preventing blockages.

A portable solar water pump uses tight interference fits to join components without tools.

Segmented autoclave curing processes ceramic matrix composite plies to form gas turbine engine rotor blades with optimized compaction.

Adhesive bonding and covering strips attach toothed trailing edges, simplifying retrofitting while enhancing stability.

U-shaped channels guide the floating seal to accommodate thermal expansion while cooling passages reduce wear at the sealing interface.

A projection device aligns with the rotor blade longitudinal axis to mark precise sensor attachment points on the inner surface.

Serpentine shelf wall and nested cooling passages reduce thermal transient strains while maintaining structural strength.