Burners TRIZ Cases

Segmented dual fuel circuits with a pressure-activated check valve prevent drooling during low-pressure startup while maintaining clean combustion.

Radially divided pre-film plates atomize fuel via swirling flow, resolving poor premixing at low power.

Helically coiled cooling passage transfers heat from the ignitor to fuel flowing through the torch wall structure.

Longitudinal cooling fins helically circle the combustion channel to reduce thermal stress and extend burner tip service life.

A flame sensing controller evaluates light samples against secondary flicker criteria to detect combustion presence in fuel oil burners.

A smoke removal device burns particulates using a central fuel gas passage and lighter to generate fire within the tube body.

Tangential air nozzles generate rotational flow to clean the mixing chamber, preventing small particle clogging in waste fuel combustion.

Helical barriers separate intertwined fuel channels in burner components, enabling stable combustion across different fuels without external piping.

Insulated modular tips with concentric conduits protect injection devices from gasification reactor heat, extending component life.

Offset air introduction passages direct fuel and air flows toward the spark plug, preventing homogenization that reduces ignition efficiency.

A stepped center body axial flow fuel nozzle reduces NOx emissions by premixing fuel and air in dedicated passages before combustion.

Control system establishes complete closure as a baseline to overcome manufacturing tolerances and ensure accurate compressed air flow measurement.

Thermal diffusion coating resizes holes in gas turbine nozzles, avoiding costly welding damage.

Deflectors guide airflow past spark plug guides, preventing burning and cracks.

Segmented annular cooling channels prevent auto-ignition and thermal damage in gasification systems by maintaining lower temperatures.

A compact combustor uses a baffle plate with varying hole diameters to control compressed air flow rates in the radial direction.

Radial fuel ports and purge air passages atomize liquid fuel to create a protective thermal barrier on the combustor liner.

A unitary fuel nozzle body eliminates braze joints through direct metal laser sintering.

Segmented small holes in the innermost annular line prevent flashback and particulate adhesion while maintaining stable lean combustion and low NOx emissions.

A removable pilot liquid tube with a fixed shroud assembly shields the fuel nozzle from high temperatures, preventing thermal damage and coking.

Periodic high-velocity gas pulses dislodge waste gas deposits from regenerative burner media beds, extending replacement intervals by up to 21 times.

Segmented resonator chambers with offset inner surfaces reduce thermal stress and cracking while expanding the engine operating envelope.

Additive manufacturing creates compact fuel nozzles with intricate internal channels using selective laser sintering.

A three-layer composite cover equalizes surface potential, preventing particle attachment and reducing the frequency of cover exchanges.

Segmented dual fuel injector routes liquid and gaseous fuels through dedicated passages to prevent cross-contamination and minimize flashback risks.

A rotary atomizing head uses overlapped frustconical rims to atomize paint at lower rotational speeds.

Discrete inlet and exit openings in the cooling plenum normalize pressure variations, reducing thermal gradients and structural stresses.

Pneumatic purge air flows through an internal heat shield to prevent coke formation at the fuel injector tip, reducing NOx emissions.

Segmented bluff body gutters and turbulators mix fuel and air to ensure complete combustion, reducing nitrogen oxide emissions in gas turbines.

An integrated heater ignites fuel and purges injector residuals, eliminating separate components that increase costs and cause operational interruptions.

Segmented deflector ribs with micro-structures segregate water flow to improve distribution uniformity and scheduling accuracy.

Concentric annular air ducts within the central lance improve fuel and air distribution while enabling modular maintenance of the combustor assembly.

An annular air gap thermally shields the internal bore of a fuel swirler, preventing fuel choking caused by high temperatures in gas turbine engines.

Physics-based modeling compares expected oxygen levels against sensor data to detect convection fouling and tramp-air leaks, preventing burner tip clogging.

Cylindrical sealing surface swages inward along a conical seat to form a leak-proof seal between the liquid fuel injector and the hub.

Pilot fuel supply passage cools main fuel injector to prevent coking during low power operations while maintaining compact radial size.

Concentric nozzle tips with swirl vanes atomize fuel and create an air shield to prevent coking from liquid droplet accumulation.

Pilot flow cools main circuit exit ports, preventing coking at high power levels.

A floating collar directs plenum air through purge openings to cool the igniter tip.

Sequential swirl devices separate premixing from pressure loss reduction, resolving the trade-off between mixing quality and energy efficiency.

Segmenting the injector into pilot and main units resolves poor ignitability at low airflow while maintaining combustion stability under rapid load changes.

Additive layer manufacturing deposits wear-resistant material on the air swirler flare, reducing manufacturing complexity while extending operational life.

A fuel spray nozzle splitter wall admits cooling air to form a protective film along its surface.

An insulating sleeve spaced by an air gap reduces heat conduction and prevents coke buildup in gas turbine engine fuel nozzles.

Converging fuel passages control velocity and prevent recirculation zones, eliminating thermal stresses and coking in gas turbine engines.

Staged quench air jets in a rich-quench-lean combustor lower peak temperatures to reduce NOx emissions while maintaining complete fuel oxidation.

A fuel injector integrates a heat pipe with a vaporization section at the nozzle and a condensation section at the cooling source to manage thermal extremes.

Flow blurring atomization in a combustor injector reduces power consumption while handling highly viscous fuels.

A fuel burner system injects liquid and gas fuels into a turbine combustor to enable flexible multi-fuel operation.