Efficient Propulsion Technologies TRIZ Cases

Repositions the mechanical coupling between the fan casing and air intake to reduce nacelle weight.

A variable cycle gas turbine propulsor adjusts bypass airflow to optimize thrust across flight regimes.

A combustor analysis method calculates Damkohler numbers to assess flame stability.

Asymmetrical door pivoting and fixed fairing positions reduce mechanical complexity while maintaining direct thrust performance during flight.

Anticipatory feed-forward control resolves lag in variable pitch propulsion assemblies by pre-calculating torque adjustments before pitch changes occur.

Integrates outer flowpath ducting with front frame struts to reduce engine weight and manufacturing complexity.

Rigid bars replace flexible harnesses inside inlet guide vanes, eliminating vibration damage and bending radius constraints.

High tensile strength para-aramid screens dissipate impact energy, resolving vibration wear and corrosion issues in turbine intake systems.

A compact thrust reverser deflects primary flow gases to reduce secondary ejection velocity.

Opposing rotary shutters synchronize to control port timing, reducing pressure drops and mechanical complexity in turbine engines.

A variable speed rotor system maintains a minimum rotation rate when electrically energized to provide continuous visual indication of power status.

Movable ballast shifts the center of gravity to balance an integrated unmanned aerial vehicle airframe, resolving stability issues in strong winds.

A low thermal mass joint design connects a diffuser flange to a tangential on-board injector via fasteners and support fingers.

Machining turbine rear frames with a shared reference frame compensates for assembly deformations and ensures precise hole positioning.

An integral tube and spoolie seal bridge an air gap, accommodating thermal expansion while preventing fluid leakage across temperature differentials.

A unified ceramic matrix composite case and stator segment reduces thermal hot-spots and mechanical fatigue by eliminating separate attachment features.

Segmented laminate seals with 20-to-70 degree angled hooks simplify gas turbine engine assembly while maintaining combustion flow reliability.

Segmented nozzle pieces swing inward to form projections that reduce noise during takeoff while maintaining a larger area for supersonic propulsion efficiency.

A rotating agitator converts injected water into steam within the exhaust stream, reducing back pressure and boosting turbine energy output.

Passive one-way clutches replace active control systems to reduce weight and complexity while maintaining versatile operating modes.

A fully integral epoxy cap probe merges sensor elements with the fan case air seal to monitor tip clearance.

Flat seals compress between angular sectors to eliminate bolted T-shaped parts, reducing handling time and improving rigidity.

Internal dog clutches lock the de-oiling tube to the shaft, eliminating auxiliary nuts that disrupt airflow.

Segmented housing isolates high-voltage electrical systems from combustible fluids to enhance safety while maintaining efficient power transmission.

Segmented disks supported by a carrier reduce deflection and prevent contact while maintaining structural integrity.

Hinged flaps in a turbofan nozzle alter the bypass flow path to create a downward thrust vector, reducing required take-off field length.

Segmented inner and outer layers optimize diffusion interactions to prevent alpha-chromium formation while maintaining ductility.

Variable male connector lengths engage anti-rotation stop members without increasing overall device complexity.

A hybrid-electric propulsion system manages power distribution across dual propellers for vertical takeoff and cruise flight.

Interlaced ceramic fibers in a sintered matrix resist oxidation and erosion at 2200°F while maintaining mechanical integrity.

Inclined radial arms integrate the hub and casing to distribute thermal stresses, maintaining stiffness while reducing structural complexity.

A fibrous preform adopts an intermediate geometry before post-forming into a complex lobed flow mixer structure.

Reflective housing surfaces redirect exhaust shockwaves toward rotor vanes to capture additional rotational energy.

Inserting a brazed tab into a through-slot in the support sector limits accidental detachment and stress concentration at circumferential ends.

Compaction bars at flange angles prevent unstickage defects while the vacuum liner enables controlled resin injection and extraction.

An integrated thrust reverser pylon assembly utilizes a translatable cowl and cascade structure to redirect fan air for deceleration.

A magnetically coupled wheel system transfers torque through alternating magnetic fields without physical contact between rotating members.

Replacing redundant units with one dual-mode machine cuts weight and complexity while maintaining flight reliability.

Segmentation and dimensionality changes minimize vertiport footprint to increase traffic throughput without expanding horizontal space requirements.

An aluminum alloy cement co-deposits zirconium with aluminum to stabilize reactive element distribution in protective coatings.

A tri-body nozzle adjusts bypass airflow area and redirects thrust using shared actuators.

Carbon nanotube-reinforced mats resolve delamination at winding turn interfaces without adding casing mass.

A push-lock pin system secures insulation tiles to a gas turbine engine wall using a front-access locking mechanism.

Gas turbine engine partial flame failure detection uses temperature sensors to monitor thermal field variations, reducing false alarms and explosion risks.

A heat exchanger tube uses non-circular reinforcing structures to divide fluid flow into separate channels.

A control method manages electric motors in thrust reversers by alternating operation and rest periods to prevent overheating.

Neural networks generate Pareto frontier solutions for real-time fault accommodation in nonlinear aircraft engines.

Segmented front wall allows independent gearbox removal to reduce maintenance downtime while maintaining structural rigidity.

A movable liner element deflects upon impact to capture detached fan blade fragments within a dedicated containment cavity.

Thermal recuperation converts turbine exhaust heat into electrical power, eliminating heavy battery weight penalties.