Continuous Combustion Chamber TRIZ Cases

Segmented injectors extend into premixing tubes to improve fuel-air mixing efficiency while simplifying maintenance access.

Segmented combustor cap directs cooling air through effusion ports to relieve thermal expansion stresses.

A catalytic pilot burner generates synthesis gas to stabilize combustion in gas turbine engines.

Longitudinal grooves on a venturi inner surface disrupt coherent liquid fuel sheets, lowering spectral content and improving atomization.

A radial fuel injector uses mixing enhancing members to deliver a fuel and air mixture into a combustor.

A two-stage combustion system burns ammonia and hydrogen to generate energy, then uses excess fuel to reduce nitrogen oxides into harmless nitrogen and water.

Segmented fuel nozzles balance mixing intensity and burning velocity to maintain flame stability while reducing NOx emissions.

Segmented pedestals with varying cross-sections direct and mix cooling airflow to resolve insufficient thermal regulation in turbomachinery components.

Segmented dilution fences offset axially improve quenching efficiency by reducing high temperature regions behind jets, lowering NOx emissions.

Convective cooling holes direct airflow into sequential liner channels to enhance heat transfer efficiency.

An interface shield on a ceramic matrix composite component directly contacts adjacent metallic parts, reducing thermal binding and extending service life.

An active purge mechanism with a backflow preventer valve removes fuel from insulative gaps via ambient air flow, eliminating capillary entry risks.

Segmented nozzle design distributes thermal load across multiple supply passages to maintain uniform fuel injection conditions.

A fuel oil injector divides nozzles into two groups to maintain pressure drop at low load conditions.

Segmented primary holes near spark plugs reduce airflow to raise the re-ignition ceiling while larger holes elsewhere control smoke and NOx emissions.

A non-ferrous obstruction reduces local cross-sectional area to accelerate cooling fluid velocity while minimizing pressure loss.

A curved seal contacts a rear inner discharge nozzle and nozzle guide vane, reducing wear on sealing components.

Pilot cavities maintain natural air rotation, eliminating rectifier systems and reducing aerodynamic energy losses.

Differential air intake configurations in a multi-tube fuel nozzle achieve uniform air-fuel mixture profiles, reducing NOx emissions and heat loading.

Magnesium oxide reacts with vanadium pentoxide to form a protective barrier, reducing corrosion and extending component lifespan.

Throttle plate creates intermediate pressure zone to cool combustor panel interfaces, preventing oxidation damage.

Angled compressed air from a wake energizer diffuses blockage-induced wakes, restoring uniform airflow distribution.

Curved manifold entries stabilize fuel flow and improve air-fuel mixing while reducing combustion vibrations.

A seal member positioned between combustor liner segments directs impingement cooling air to mitigate thermal degradation.

A coaxial lance injector uses a guiding bushing to allow axial sliding of tubular bodies.

Staggered vane apertures direct fuel axially to extend gas residence time, reducing NOx emissions while maintaining combustion stability.

A pressure-activated seal uses gas force to maintain contact between components.

A single yoke connecting flange joins ceramic matrix composite liners and dome to a metallic cowl structure.

A tapered burner cylinder surface directs air and fuel flows to minimize radial spreading.

Merging outer casing with shroud eliminates sliding fixation issues on conical surfaces while reducing diffuser mass.

Porous thermal barrier coatings on CMC film holes reduce heat transfer rates, minimizing thermal gradients and stress in gas turbine engines.

A burner assembly with an uneven inner wall generates longitudinal vortices to enhance fluid mixing and stabilize flame position.

Integrated base nozzle eliminates external supports, reducing airflow obstruction and NOx emissions in gas turbine micromixers.

Air supply holes spaced narrower than the quenching distance prevent flame adhesion and reduce liner metal temperature.

A fuel delivery regulator switches between distinct fuel sources to optimize combustion in gas turbine engines.

A reticulated open-cell porous structure dissipates combustion noise and instability, stabilizing the flame without active control systems.

Reverse fuel flow cools the center body and vanes, preventing flame holding damage while maintaining premixing performance.

Variable area conduits reduce recirculation zones and pressure drop, ensuring uniform air distribution to fuel nozzles.

Varying near-wall cooling channel cross-sections equalizes coolant mass flow across the combustor wall, resolving pressure distribution inconsistencies.

Dynamic flow control maintains warm water temperature, stabilizing gaseous ammonia production despite exhaust gas fluctuations.

A flow sleeve with recessed portions and a retention clip secure the cross fire tube in gas turbine engines.

A main injector uses a central plug to restrict flow and induce swirl, shortening flame length and stabilizing combustion.

Varying vane angles in primary and secondary swirlers decouple purge jets, reducing autoignition risks and improving jet stability.

Radial gaps introduce film air to cool the combustion cylinder, suppressing NOx and CO emissions while maintaining structural integrity.

A modular combustion chamber system burns hydrogen with oxygen to heat steam flow efficiently.

Intersecting outlet holes with sharp corners expand cooling fluid at varying angles for effective film cooling.

Flow deflectors redirect axial air radially outward to preserve impingement velocity on combustion liners.

Homogeneous CMC materials eliminate thermal expansion mismatches that disrupt combustion gas flow in turbine engines.

Contoured surface geometry expands impingement jet contact area beyond hole diameter, increasing cooling effectiveness without adding structural complexity.