Burners TRIZ Cases

A rotary sprayer divides fluid into separate working and secondary streams using a rotating disc distribution plane.

A radially outward flowing air-blast fuel injector design directs fuel through a swirler to form an outer sheet.

A fuel injection nozzle uses a Venturi structure to enhance fuel vaporization and air mixing at the distal end.

Fuel injector nozzle atomizes liquid fuel via jet impingement, eliminating atomizing air systems to reduce capital and maintenance costs.

A multistaged lean prevaporizing premixing fuel injector atomizes liquid fuel using high-temperature combustion air to achieve thorough mixing.

Active cooling valve controls secondary circuit temperature at low flow conditions, preventing coking while passive scheduling manages primary fuel delivery.

Upstream fuel distribution and near-exit swirl maintain air flow turbulence, resolving dissipation issues that reduce atomization effectiveness.

A prefabricated combustion assembly integrates a perforated flame holder to optimize fuel and oxidant mixing for efficient heat generation.

Integrated air wipe channels direct airflow to clean the downstream surface, preventing carbon deposition and thermal erosion on gas turbine nozzle components.

Peripheral slots in the plunger segment conductive material to interrupt eddy currents, enabling faster magnetic field decomposition and higher cycle rates.

An auxiliary combustion chamber premixing cup generates a recirculation zone to sustain flame stability under low air pressure.

Segmented double wall curtains and locally optimized exhaust ducts reduce heat loss between tunnel washer chambers.

Positioning special color ink nozzles at a terminal end prevents mixing with adjacent black and color inks while maintaining compact head dimensions.

A dual-fuel burner manages thermal instability of unenriched pyrolysis oil through pre-heating and dynamic air-to-fuel ratio adjustments.

A control arrangement varies fuel supply ratios between main and pilot lines to prevent component overheating.

A gas turbine burner uses a pilot combustor to supply heat and radicals for stable lean premixed combustion.

Casting a single-piece swirler eliminates braze joints that cause hot spots, reducing NOx emissions while maintaining thermodynamic efficiency.

A rotary atomizer adjusts liquid film thickness between 200 and 1000 micrometers to ensure uniform distribution.

A controller generates residual error values to estimate throttle body coking severity and predict sensor degradation.

Nebulizing precious metal oil into fine droplets enables rapid vapor-phase combustion, eliminating crust formation and unburned residue hazards.

A control assembly manages off-gas delivery to glycol dehydrator reboilers using pilot valves and three-way diversion.

A staged cooling flow control valve manages variable fuel split between primary and secondary turbine nozzle tips.

Differential static pressure across stagnant fuel drives purging air through selected passages, eliminating coking risks in gas turbine engines.

Segmented airflow circuits reduce NOx emissions across power ranges by optimizing swirl patterns.

A Helmholtz damper with two interconnected damping volumes replaces burners and fuel lances in gas turbine combustors.

Integrating burner units into gas channels eliminates external chambers, improving temperature distribution and protecting masonry from heat damage.

A combustion nozzle positions fuel outlets inside a Venturi section to accelerate compressed air flow for rapid mixing.

A gas turbine combustor employs a fuel diffusion restraining member to separate injected fuel streams from inner circumferential faces.

A jet device uses a segmented chamber and reciprocating piston to generate non-zero-net-mass-flux flow.

Angled fuel injectors enhance mixing rates in gas turbine secondary combustion zones.

Axially offset fuel plenums disrupt convective timing to mitigate in-phase combustion dynamics, preventing coherent instabilities that excite turbine blades.

A fuel lance with asymmetric air outlets creates a pilot vortex to atomize liquid fuel in gas turbine combustors.

A smoke removal device burns particulates using a central combustion unit.

Axially offset fuel nozzles with non-circular perimeters break acoustic coupling to reduce combustion dynamics amplitudes.

Segmented dimples on the burner surface enhance turbulence, reducing noise by 22% while minimizing smoke.

An adjustable two-material atomizer modifies the annular injection opening cross-section during operation to prevent wall film formation in the mixing channel.

Segmenting the excitation member from the housing prevents cavitation erosion on the nozzle while maintaining multiphase liquid homogeneity.

Helically threaded fluid passages between conical nozzle components prevent braze fillet formation and plugging in intricate airblast injector circuits.

Discrete throttle passages in the injection body reduce fuel film thickness, enabling smaller atomized droplet diameters for improved combustion.

Fuel-lean flow reacts with carbon deposits on heated interior surfaces, preventing erosion and maintaining ignition reliability.

A method fuses powdered metal to a machined component top surface using directed energy beams to create a monolithic structure.

Segmented brazing and spring-supported mounts isolate the heat shield from the centerbody to reduce thermal stress.

Radial compression of a malleable sealing layer creates durable, fluid-tight connections between conduits of different materials and sizes.

Protective plates redirect cold fuel away from hot chamber walls, reducing thermal gradients and extending flame holder arm life.

Breakthrough sensors adjust flow to reduce weight and noise.

A pressure sensor detects atomization air pressure downstream of the valve to prevent untimely electrostatic field activation.

Periodic activation of the detection mechanism extends battery life while maintaining effective malodor response.