Efficient Propulsion Technologies TRIZ Cases

Relocating the front flange upstream creates a cavity within the nacelle assembly to house engine accessories.

Diffuser nozzle geometry expands gas cross-section to lower exit velocity, improving hot bleed air mixing and eliminating inlet lip hot spots.

A fuel flow control assembly uses a dynamic metering valve to restrict parasitic pump output loss at low speeds while ensuring adequate lubrication pressure.

A tool assembly forms and compacts composite stringers directly onto aircraft skins for co-curing.

Composite microparticles prevent chemical ingress and swelling, achieving high abrasion resistance without compromising durability.

Differential thermal expansion between metal and CMC increases clamping load at elevated operating temperatures.

A translating cowl and pivotally coupled cascade system divert bypass air for thrust reversal without blocker doors.

Localized barrel thickness variations direct cracks toward low-stress areas, preventing secondary damage from fan blade off debris without adding weight.

Segmented doors and flaps adjust the bypass ratio to optimize thrust augmentation while managing device complexity.

Layout matrices group zones by ply orientation to reduce computational complexity while satisfying local stacking rules.

A fibrous preform assembly method for ceramic matrix composite flow mixers using connection lines extending in the gas flow direction.

Nested cascades within a torque beam cavity reduce weight and drag while maintaining thrust reverser performance in short fan ducts.

Fixed shearing means on stator blades destroy rotor moving blades, preventing overspeed without modifying aerodynamic profiles.

Localized heating confines thermal energy to the weld interface, preventing mechanical strength loss in the polymer matrix.

Composite aft cascade ring with integrated actuator pathways reduces weight while maintaining structural integrity.

A turbofan engine uses aerodynamic coupling to transmit power from a high-speed core compressor directly to a low-speed pre-combustion turbine.

Undulated inner ring flanges accommodate thermal expansion to reduce mechanical stress on the bearing compartment.

Shape memory polymer seals switch stiffness through thermal activation, eliminating complex hinges and maintaining electrical continuity during wing folding.

Material removal between perforations simplifies assembly and seals honeycomb ducts to enhance acoustic performance.

Seal welds isolate cooling channels in turbine vanes, enabling higher operating temperatures while maintaining structural integrity.

A gas turbine seal assembly uses a backside cavity to reduce radial pressure loads on ceramic matrix composite segments.

A concentric annular inlet lip with constant cross-section simplifies gas turbine engine nacelle manufacturing.

A composite fan casing mold uses differential thermal expansion to compact resin preforms during low-pressure injection.

Integrating a forged bull nose into the fan case reduces nacelle volume, enabling compact gearbox placement.

Dynamic speed threshold adjustment prevents free turbine over-speeding during power transmission breaks while accommodating transient peaks.

Radial sound-damping elements extend axially beyond the honeycomb layer to absorb low-frequency vibrations without increasing structural complexity.

Rotating vanes in a turbine inlet nozzle adjust flow area to optimize pressure ratios, eliminating heavy midcompressor bleed systems and extending time-on-wing.

Linear actuators move chevrons forward or aft to optimize acoustic performance and fan duct pressures while minimizing aerodynamic drag.

Nacelle pressure sensors detect inlet flow separation parameters to control actuators, redistributing airflow and reducing fan blade stress.

Branching passages in hollow spokes route cooling air to bearing supports, managing thermal loads while maintaining structural integrity.

Counter-rotating gas ramps manage internal stress during sputtering to prevent DLC coating detachment under high point loads.

Asymmetric conduit cross-sections create uniform jets that eliminate uneven heating and prevent inner casing distortion.

Flexible heat shield with tabs accommodates thermal expansion of oil tube fittings, preventing oil coking and blockages.

Segmented turbine shrouds reduce gas leakage and assembly complexity by using movable attachment features to secure blade tracks.

A nozzle flange made of high expansion alloy paired with a titanium sealing member thermally protects the structure.

A transcowl lock prevents uncommanded deployment by engaging only when the component reaches an over-stow position.

A metal ring clamps a ceramic matrix composite nozzle stage to resolve thermal expansion incompatibility and mechanical stress sensitivity.

Reduced stiffness regions in radial elements redistribute thermal stress away from weld joints, extending component life.

An overrunning clutch transfers torque between hubs using roller elements and resilient members to enable autorotation.

Elastic arcuate plate deflects under thermal expansion forces to maintain pin alignment and prevent misalignment in gas turbine engines.

A compressor bleed passage extends from the core flowpath to egress airflow away from the engine.

Multi-axis simultaneous motion of a disc tool grinds complex airfoil geometries in a single pass, reducing cycle time and extending tool life.

Nesting the electric machine inside the rotor hub reduces overhung moment loads on the bearing while enabling efficient motor and generator operation.

A rotor blade tip portion moves between anhedral and sweep angles using a compact hinge mechanism.

Selective coupling of distributed power units optimizes thrust specific fuel consumption and reduces drag.

Dielectric sensing replaces worst-case idle times with real-time moisture data, enabling immediate takeoff under restricted conditions.

A two-spool turbofan design directs airflow through separate fan stages driven by distinct spools to optimize thrust generation.

Adaptive aircraft engine uses dual bypass ducts with adjustable nozzles to optimize thrust distribution across flight regimes.

Integrated power take-off module drives coaxial shafts from both rotors, reducing structural clutter and compressor surge risks.

A metallic hanger expands thermally to maintain clamping load on ceramic matrix composite vane shanks.