Continuous Combustion Chamber TRIZ Cases

Explore a 3D-printed basketball with variable lattice cells and beam thicknesses for consistent rebound without inflation.

Coating channels redirect molten CMAS and limit buildup on CMC turbine parts.

This case uses radial fuel inlets and swirlers in injection tubes to limit backfire and improve hydrogen combustor stability.

Tangential and radial feed conduits mix hydrogen uniformly, while isolated manifolds and metallic foam arrestors support stable combustion.

This case uses cast-in radiused gates to smooth coating transitions, reduce chipping, and enhance gas turbine liner panel oxidation life.

This multi-phase system buffers hydrogen flow and temperature, decoupling pumping from metering for steadier turbine fuel delivery.

Constant-volume chambers use combustion-gas thrust to rotate blades, combining combustion and power transfer in fewer stages.

Premixer tubes mix fuel and air for stable gas turbine combustion with reduced flashback risk.

A channel between mating surfaces routes cooling air through the tongue joint, reducing hotspots and thermal stress in high-heat areas.

This case uses a co-swirl fuel nozzle and swirler to maintain axial velocity, limit flame holding, and support hydrogen combustion.

Serpentine fuel channels transfer heat from mixer walls and the boundary layer into fuel, helping prevent flame holding with hydrogen.

A catalytic metal layer on mixer passage walls promotes removable filamentary coke, limiting thick deposits and downstream shedding damage.

Alternating primary and secondary injectors deliver targeted fuel during starts, flame-outs, and maneuvers to support rapid relighting.

A torch ignitor manifold distributes continuous flame to multiple fuel nozzles, supporting reliable starts and rapid relighting.

Directional fuel apertures and adaptive flow control support faster relighting and flameout resistance, especially with hydrogen fuel.

A rotary fuel slinger feeds liquid fuel to one zone, while a gaseous injector burns downstream exhaust for cleaner turbine operation.

This case combines the combustor wall, engine case, and radial support into one body with tapered ports for integrated airflow management.

A flow control system switches between core and bypass paths to balance subsonic fuel efficiency with supersonic inlet heat tolerance.

A starting fuel pipe and heat shielding protect liquid ammonia from hot air, stabilizing injection without a vaporizer.

Predictive vibration analysis stabilizes combustion while collecting varied gas turbine data.

A parallel coolant circuit keeps staged-off fuel nozzle passages cool, limiting coking during low-power operation.

An external RF transponder sends signals through a nozzle horn and waveguide to diagnose flame and flow-field behavior.

Cooling passages and circumferential oxidizer ports reduce venturi wall temperature without enlarging the oxidation-prone heat shield.

An HF-based etchant removes silicon oxide and damaged environmental barrier coatings, exposing the bondcoat for replacement coating repair.

This aircraft acoustic panel intersperses cells of different heights to attenuate multiple frequencies with less material.

A three-circuit fuel nozzle addresses low secondary-fuel velocity by staging isolated flows through dedicated outlet orifices.

Inner and outer flame-shaping passages guide swirled airflow, containing hydrogen combustion and protecting fuel nozzles.

Additive manufacturing integrates the rotor and cooling vanes to support stable combustion and efficient 1–10 kW micro-gas turbine output.

3D scanning and flow-area ratios validate aircraft propulsion parts without extensive testing or complex full 3D models.

Compact hydrogen combustor sizing reduces residence time and NOx emissions.

Purge orifices adjust airflow in a gas turbine combustor to limit hot-gas ingestion.

This combustor uses internal exhaust recirculation and premixed injection to improve temperature uniformity and limit radiant tube burnout.

Annular injection groups and a slit balance additive-manufacturing shrinkage while supporting flame stability and lower NOx.

A secondary combustor and steam system split reheat combustion, lowering peak temperatures while maintaining turbine power and durability.

Fluid flow testing and 2D aperture imaging estimate rates for aircraft propulsion parts, reducing modeling and validation time.

This gas turbine case routes steam to the secondary combustion zone, reducing CO and NOx while preserving combustion stability.

Cross-flow routes gas heat through temperature-specific materials, producing steam while reducing heat exchanger weight.

A heated supply tank raises ammonia vapor pressure to move liquid fuel while limiting bubbles, corrosion, and pump requirements.

This case uses fuel-oil heat exchangers and zoned spray nozzles to manage SAF properties, coking, and nvPM emissions.

This case uses staged downstream injectors and separate air supplies to improve cooling, emissions, and turndown in gas turbine combustors.

Sensors compare the blended fuel’s Wobbe Index with a target, then adjust fuel parameters for turbine combustion.

An air guide and thick wall portion lengthen the cooling path, slowing flow for liner protection without increasing combustor weight.

Stacked exchanger units and divided manifolds improve heat transfer while reducing gas turbine exchanger size and weight.

A helical preform accommodates compression during ceramic infiltration, helping preserve fibers and improve composite strength.

A fault-detection transfer architecture redistributes fuel between aircraft reservoirs to prevent loss and sustain powerplant delivery.

A deflection member, ribs, and fuel plenum intensify premixing to protect injectors and reduce NOx in hydrogen-capable combustors.

This case shows how metallic support bands mount CMC combustor liners, accommodate thermal expansion, and preserve existing architecture.

This case uses angularly distributed bypass pipes and manifolds to limit hydrogen leakage if turbine blades detach.

A sealed housing encloses the hydrogen pipe and injectors to limit leak spread and explosion risk near the aircraft combustion chamber.

Concentric air passages surround gaseous fuel injection to improve mixing, reduce NOx, and enable turbine retrofits without redesign.