Efficient Propulsion Technologies TRIZ Cases

Control systems regulate electric machine speed to drive rotors, reducing ground noise while maintaining rotor readiness.

Intercooling turbine section bypass routes core flow around cooling stages to adjust bypass ratios for variable cycle operation.

Thermocouples on the stator surface detect shaft failure to trigger fuel supply cutoff, preventing rotor overspeed and catastrophic blade damage.

A gas turbine intercooling turbine section bypass modulates core flow around the turbine to drive spools and reduce fuel consumption.

An annular rim catcher on the driving drum absorbs impact energy and retains the fan assembly during shaft breakage, reducing dynamic loads.

An aircraft propulsion system uses exhaust heat to condense water vapour and reduce contrail formation.

Flexible cable coupling connects gas turbine vane panels to absorb bending loads without inducing structural stress.

Variable fan outlet guide vanes pivot from nominal to open positions to prevent choking at high flight Mach numbers and maintain thrust production.

Single-piece lobed tubular fibrous structures eliminate overlapping fiber layers, reducing weight and aerodynamic imperfections in dual-flow turbojet nozzles.

A shroud hanger assembly uses a conformal seal to bias the ceramic matrix composite shroud against thermal expansion.

Ceramic composite inter-turbine ducts eliminate heavy cooling systems by using segmented structures to resist high temperatures.

Controllers govern electric motor torque to reduce speed error, improving responsiveness to load changes without requiring rapid fuel flow adjustments.

A flexible skin airfoil system uses a roller mechanism to change shape without gaps, preventing turbulence and flow separation.

Segmented fastening components accommodate thermal expansion in gas turbine exhaust liners without burdensome disassembly.

Segmenting the volute into isolated volumes minimizes pressure drops during heat exchange, reducing system mass and volume constraints.

A bearing hub design translates radial vibrations into axial vibrations, resolving critical speed instability in high-speed gas turbine engines.

Aligned fiber plies in composite flowpath structures transfer mechanical loads without metal backing, reducing inter-laminar shear stresses.

Axial passages guide pins through the annular distributor to engage transverse stops on the structural element, eliminating complex bolt assemblies.

A double outlet guide vane assembly with integrally formed end structures provides a continuous surface and primary load path.

Removable cores define undercut stiffening geometry within a single-piece fiber composite component.

An open-loop controller increases oxidant concentration in a combustor to provide primary frequency response while maintaining stoichiometric combustion.

Thrust reverser doors move to an overstowed position before full deployment.

A signal relay device demultiplexes engine control signals to optimize wiring harness weight.

Pneumatic feedback stabilizes torque motor actuators against frictional backlash and throttle disturbances.

Aluminum-doped boron nitride interphase forms stable aluminum borate compounds to prevent oxidation degradation in high-temperature environments.

High hydrogen pressure suppresses coke formation on sulphided zeolite catalysts, extending operational duration during C3-C12 oxygenate conversion.

Segmented strip assembly reduces labor intensity while maintaining aerodynamic performance in jet engine thrust reversers.

Curvilinear and multi-lobed gussets distribute mechanical stress to maintain structural integrity under high airfoil loading.

A wound metal coil pin pivotably connects a hanger and bracket within an exhaust duct liner suspension system.

A ceramic matrix composite blade outer air seal uses a double box hook arrangement for direct structural mounting.

Dynamic coolant flow modulation reduces fuel consumption during part power operations while maintaining adequate stall margin at high power conditions.

Segmenting the support into forward and aft bearings reduces unsupported shaft length, increasing critical speed and maintaining blade tip clearance.

Gas flow momentum pivots stator vanes to block flow and prevent turbine disc overspeed, reducing required disc weight.

A rotatable carrier supports a gas turbine engine module in a horizontal position for cantilevered mounting.

Assemble segmented frame sections and turning vanes to eliminate thermal stresses from over-molding and simplify tooling requirements.

A multicopter propulsion system uses a control device to optimize gas turbine engine operation within efficient ranges.

Tapered septum divides acoustic panel chambers into fluidly coupled cavities to reverse sound waves.

Eliminates oil lubrication in helicopter turboshaft engines using non-lubricated bearings and a brushless generator.

Rotating the airflow modification device on thrust reverser links reduces drag and improves fuel consumption without increasing mechanical complexity.

Defining a specific fan axis angle between the fan tip and turbine rotor reduces engine length while maintaining propulsive efficiency.

Merges the cooling radiator with the helicopter access platform barrier to resolve space conflicts and reduce installation costs.

Segmented blade tracks use flexible clips with u-shaped openings to prevent relative movement and misalignment in gas turbine engines.

Segmented droplet separators and collectors allow manual handling at 40-foot heights, eliminating heavy lifting requirements for rear-mounted aircraft engines.

Operating aircraft gas turbines at higher power during descent increases thermal efficiency, reduces harmful emissions, and captures excess energy in storage.

An axial retention device connects twelve o'clock half-beams to the fan casing, reducing excessive clearance between the thrust reverser and engine.

A composite fan case uses segmented fiber-filled polymer members to provide galvanic isolation and precise machining margins for metallic mounting components.

A movable first casing portion connected via resilient elements absorbs impact energy, minimizing damage to the attrition liner and reducing maintenance costs.

Alternating unidirectional, biaxial, and triaxial fiber layers in the fan case body absorb blade release energy while minimizing delamination risks.

Thread-based sealing device creates a floating hydrodynamic bearing between rotating structural components.