Continuous Combustion Chamber TRIZ Cases

Offset fuel and air conduits delay mixing in regenerative burners to lower flame temperatures.

Axially loaded combustor seal eliminates springs to reduce compressed air leakage into combustion gases.

Integrates a microchannel fuel-air heat exchanger within the fuel injector stem to transfer thermal energy from cooling air to fuel.

A pivot-based support hanger connects turbine engine panels while accommodating thermal expansion.

Axial staging of fuel and air injection minimizes NOx emissions while maintaining engine efficiency and reducing aerodynamic pressure losses.

A three-zone ammonia combustor consumes nitrogen oxides via intermediates, minimizing emissions while enabling complete hydrogen combustion.

Primary perforated plate alters fuel flow impedance to dampen combustion oscillations that damage gas turbine engine components.

Adjusting fuel injector flow rates creates frequency differences that minimize coherent vibrations and protect downstream components.

A fuel distribution manifold uses a seamless one-piece construction to route fluid through diverging internal channels.

Serpentine double layer channels reduce temperature gradients and extend component lifetime by minimizing thermal stresses.

Segmented cooling channels route compressor discharge air to cool transition pieces, reducing the need for additional airflow.

Strategic hole arrangement in a laminated alloy liner creates variable porosity, preventing overheating in critical areas while minimizing unnecessary cooling.

A decoupling tool uses a non-circular rod to separate telescoping tubes from gas turbine engine liners.

Segmented fuel injection orifices generate destructive wave interference to dampen thermoacoustic oscillations and reduce NOx emissions in gas turbines.

A porous surface strut injects fuel into hypersonic engine inlets, reducing mixing length by half while preventing flashback.

Variable annular space height increases air velocity and impingement force on the combustor liner, resolving high heat load challenges.

A circumferentially oriented flat spring delivers radial compliance between ceramic matrix composite and metallic turbine shrouds, preventing thermal binding.

Segmented air holes with controlled curvature prevent fuel bias and flashback while maintaining stable flame retention.

Compressed purge air flows through guide member holes to push stagnant mixtures away, preventing soot deposition on heat shields.

An integrated burner support structure eliminates independent headers to suppress flashback and reduce NOx emissions through uniform air-fuel mixing.

Axial cooling fins on a combustor liner manage temperature while reducing coolant pressure loss.

Segmented assembly of annular fairings and cylindrical walls reduces stiffness accumulation, minimizing air leaks and vibration damage.

Staggered air admission holes in annular combustors optimize dilution air mixing with combustion products to reduce NOx emissions.

Simultaneous carrier fluid flow through parallel inlets prevents contamination and corrosion of inactive passages in multi-fuel turbine engines.

An integrally formed front panel unifies the frame, rim, and seal segment into a single unitary body.

A fuel nozzle directs combustion air through internal passages to cool the distal end portion.

Segmented trunk and branch structures minimize jet penetration while maximizing heat transfer coverage on high-temperature turbine components.

Radial clamps constrain CMC ring sectors while annular flanges deflect distributor forces, reducing mechanical stress on brittle ceramic materials.

A fuel heat treatment device heats the fuel flow to a predetermined temperature before it reaches the injectors.

A nickel alloy controls titanium nitride size to improve high-temperature strength and machinability.

A combustor wall applies a bond coat layer and networked ceramic nanofibers to create a porous thermal barrier that reduces heat conduction through the coating.

Laterally directed apertures discharge cooling fluid to perturb high fuel-to-air mixtures, preventing flashback damage during lean combustion.

Upstream valves adjust fluid diversion through circumferential injectors, mitigating flame holding risks in fuel nozzles.

Segmenting hot exhaust gases from cooling air maintains high catalyst temperatures and reduces enclosure pressure while lowering stack emissions.

Segmented pilot and main mixers apply pneumatic atomization to increase fuel vaporization rates, resolving low combustion efficiency in gas turbine engines.

A thermal protection screen blocks heat radiation to prevent fuel coking and maintain spraying efficiency.

An upstream ammonia injector improves nitrogen oxide reduction efficiency by ensuring the reagent acts directly on combustion gases before emissions form.

Radial fuel injection ports in the centerbody injector enable high-energy combustion without increasing combustor length or instability.

A fuel injection nozzle uses a slit-shaped injection port to mix and inject air-fuel mixture.

Nested high-pressure air jets create an air curtain that prevents flame attachment and improves mixing quality in gas turbine combustors.

Additive manufacturing places film cooling holes near mechanical support structures to eliminate laser drilling back strikes that weaken structural integrity.

A base-mounted alignment rod inserts through cover plate cooling holes to position the combustor liner, reducing assembly time and preventing liner damage.

A sliding member connects a female screw block to a combustor transition piece, allowing relative movement perpendicular to the screw axis.

Splitless cowlings slide longitudinally to provide component access while minimizing airflow perturbations and drag forces.

Radial ferrules seal combustor penetrations to prevent airflow non-uniformity and pressure drops caused by large profile hardware.

A gas turbine control system adjusts fuel splits using exhaust temperature and compressor pressure ratio.

L-shaped tile apertures supply coolant over inner surfaces, replacing heavy cooling rings to protect discharge nozzles from high temperatures.

Segmented fuel injectors disperse propellant into an annular tube to sustain detonation waves during low power conditions.