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.