Engine Manufacture TRIZ Cases

Curved separating portions in a circumferential particle separator remove sand and dust from inlet airflow, protecting engine components from damage.

A three-dimensional digital model of a turbomachine nozzle sector aligns reference blades to determine precise cross-sectional areas.

Segmented chambers separated by internal cross-ribs distribute thermal and mechanical loads to reduce stress levels in gas turbine engine components.

Angled viscoelastic partitions in a stacked honeycomb structure reduce panel thickness and engine weight without compromising acoustic treatment effectiveness.

A non-axisymmetric secondary duct design modifies the outer wall distance to reduce flow velocity at outlet guide vanes.

Radial pin segmentation and bypass conduits eliminate flow dead zones that create hot spots and degrade gas turbine performance.

Internal lifting lines route through rotor blade sections to enable section alignment and coupling, reducing reliance on large ground cranes during servicing.

Foam adhesive strips bond wind turbine blade tip extensions via a separated trailing edge, eliminating hazardous curing and structural damage risks.

An actuated metering ring modulates compressed airflow through a heat exchanger, reducing unnecessary energy consumption during variable engine operation.

A lifting structure with retractable rods grips tower blocks for vertical assembly without cranes.

Chevron pin banks increase turbulence to boost heat transfer coefficients by 45% for high temperature turbine components.

A turbine housing tongue tip geometry positions the lateral centreline relative to the passage offset line.

Segmented conducting receptors and an insulated conductor inside the tip add-on confine strikes to predetermined points, protecting the airfoil from damage.

A segmented jib crane uses interchangeable pillar and arm modules to move heavy components inside a wind turbine nacelle.

Flared cylinder portions expand the exhaust passage before tubular struts, reducing pressure loss while maintaining structural strength.

Faceted structural coating reduces groove gaps, enabling micro-channel formation that improves heat transfer rates and engine efficiency.

A wind turbine blade features a sharp corner at the pressure side transition to expand aerodynamic surface area.

A nozzle airfoil with a trailing edge deviating 0.1 to 5 degrees from the axial plane reduces aerodynamic loss and improves loading.

Modular fittings with curved tubes tune natural frequency to manage thermal stress and vibration without complex geometry.

Segmented wedging bodies transform axial loads into radial expansion forces, reducing disc weight and machining time while enhancing vibrational damping.

An inclined tip shroud prevents main flow collision and separation vortices, maintaining turbine performance while reducing centrifugal loads on rotor blades.

Segmented stator blades with variable tilt reduce noise while minimizing friction losses and pressure gradients in turbofan compressor stages.

Forward attachment flanges create cavities for captured nuts, securing acoustic panels without penetrating the inner body to maintain noise attenuation.

Segmented cooling air circulation ducts transfer heat from internal flaps to reduce propulsive performance losses caused by excessive cooling air extraction.

Interior protrusions in the airfoil passage intercept dirt particles, preventing plugging of film cooling holes and maintaining uninterrupted coolant flow.

A turbine vane corner part uses a curved surface design to distribute stress, preventing cracks at high temperatures.

A movable bypass door diverts boundary layer air away from the fan rotor inlet to reduce mechanical stress on rotating components.

A blade outer air seal incorporates a relief gap to accommodate thermal expansion of the radially inward side.

A hydrochloric acid stripping solution uses iron ions to facilitate selective coating removal via redox reactions.

Triangular divots fill gaps between stowed blocker doors to restore smooth airflow and reduce aerodynamic performance losses in the thrust reverser system.

Mixed cooling nubs with varied geometries enhance convective heat transfer while accommodating casting constraints near edges.

Porous acoustic material fills the space between inner and outer layers, reducing aerodynamic drag while maintaining structural strength.

Segmented baffle insert minimizes cooling air pressure losses while maintaining outflow margin to prevent hot air backflow.

Grooved guide vanes prevent exhaust gas leakage and swirling by disturbing edge flow and channeling surface flow through the variable turbine geometry.

Radial relief channels in rotor discs remove condensation and debris from spindle bolt holes, preventing fretting fatigue fractures.

A hydraulic power generation device uses segmented water passage units to drive turbines independently during maintenance.

Partial tip flag directs cooling air through serpentine channels to mitigate ambient pressure variations that disrupt internal flow paths.

Offset gas core and concentric electric motor reduce engine size while providing supplemental take-off thrust.

Spherical washers distribute stress across ceramic matrix composite liner flanges, preventing damage from flat washer connections.

Curved vane shroud positioning shifts collision points away from the casing, suppressing secondary flow generation and reducing pressure loss.

Lock assembly secures turbine rotor cover plate via interference fit, maintaining reliability under thermal stress.

A bifurcation panel inlet directs control air onto the turbine casing to manage thermal expansion and contraction.

An oversized cavity and wedge system replace damaged outer bases without full disassembly, maintaining precise vane positioning.

Varying spar cap chord-wise width expands the bonded joint area to maintain structural integrity without adding blade weight.

Segmented Inconel 718 wings and a hollow bullet constrain the turbine wheel, reducing weight while preventing radial ejection.

Angled chamfer pockets remove material from turbine shrouds to lower weight while maintaining feather seal retention and airflow sealing.

Interior recesses in dual-wall components capture drilling burrs at hole exits, preventing flow restriction and improving gas turbine cooling efficiency.

A converging plenum increases circumferential velocity, directing particles radially outward for efficient removal from turbine engine airflows.

Tapered scarf joints with recesses integrate modular wind turbine blade sections, resolving joint durability and weight trade-offs.