Continuous Combustion Chamber TRIZ Cases

An angled radial fuel delivery system directs the fuel-air mixture to optimize combustion mixing within a gas turbine combustor.

Aligning separate fuel and air plate passages mixes gas flows, reducing manufacturing complexity while maintaining combustion efficiency.

Angled hub and sleeve surfaces in a fuel nozzle valve adjust secondary flow area, resolving poor mixing and high emissions from static dividers.

Axial elongated components create a negative pressure zone that prevents backfire and stabilizes flames, reducing NOx emissions.

A carbureted fuel injection system premixes and prevaporizes fuel within a vane air channel using secondary airflow before combustion entry.

Heat transfer augmenters guide cooling air flow across the single skin combustor liner outer surface to increase heat exchange.

A burner assembly with in-line injectors discharges fuel parallel to air flow through a diagonal swirler.

A turbine blade features interwoven flow channels angled at plus or minus 45 degrees to induce secondary flows.

An integrated ignitor cap uses sequential primary and secondary fuels to provide delayed ignition, eliminating manual submersion hazards.

Segmenting combustor cans into warm and hot zones adjusts pilot fuel splits to reduce carbon monoxide emissions during part load operations.

Zirconium oxide powder reduces thermal conductivity by combining yttrium, lanthanum, and cerium oxides to prevent sintering.

Segmented plate burner module mixes fuel and air rapidly to shrink combustion chamber volume.

Nested bushing and chimney assembly accommodates relative movements in tight spaces without increasing device height.

Varying first combustor fuel flow mitigates uncontrolled power jumps during sequential combustion stage switching.

Cryogenic fuel vaporization replaces compressed air cooling in aircraft turbines, improving engine efficiency while lowering greenhouse gas emissions.

An impingement plate defines a cooling flow return passage that routes heated air back into the combustion chamber to mix with fuel, reducing NOx emissions.

Mixing fuel ammonia with combustion air cools side walls via convection, preventing heat deterioration and extending combustor lifespan.

Co-sintering a green heat shield body and cooling louver eliminates secondary shaping operations and reduces tooling costs.

Downstream air hole plate center flattens temperature distribution to lower NOx emissions while maintaining combustion stability.

A film cooling hole with a swept pocket directs cooling air to align with core flow.

A reheat combustor uses split exhaust streams to cool liners and flame stabilizers without compressor air extraction.

Spherical joint accommodates thermal expansion differences between combustion chamber and damper, maintaining pulsation damping effectiveness.

Acute angle injection openings reduce syngas residence time and prevent flashback in sequential combustion turbines.

Three-dimensional mixer vanes with varying curvature and twist enhance fuel-air mixing efficiency and durability in gas turbine engine combustors.

Segmenting combustion into primary and secondary zones with pure fuel injection minimizes NOx and flashback without expensive water usage.

A thermal fuse on a fuel mixing tube melts during ignition to divert fuel flow, preventing nozzle damage from flashback events.

An integrated ring plate with inwardly protruding walls reduces combustor casing volume to mitigate low-frequency thermo-acoustic instabilities.

Variable geometry valves adjust cooling air delivery to reduce parasitic energy loss during cruise operations.

Flow enhancers inside turbine airfoils promote turbulence to improve convective heat transfer while reducing dust accumulation.

Segmented dual-pump system supplies adequate fuel flow during windmilling, reducing main pump weight and heat generation while ensuring reliable restart.

A thixotropic ceramic paste restores damaged thermal barrier coatings on gas turbine components without removing the engine assembly.

Flexible bellows joints absorb differential thermal expansions between injectors and walls, preventing structural deformation and seal leaks.

Baffles in CMC liners redirect cooling airflow to lower gas surface temperatures, reducing specific fuel consumption without increasing air usage.

Integrating the fuel supply duct into the burner head eliminates external hoses and nozzle lances, reducing assembly complexity and leakage risks.

Vascular engineered structure lattice channels cooling fluid through the fuel conduit to prevent coke formation caused by high core gas temperatures.

Impingement holes eject high-momentum air to divert fuel droplets, preventing carbon build-up on heat shields near injectors.

Bleed ducts inject high-energy air into the diffuser throat to prevent flow separation, reducing nitrogen oxide emissions in compact engines.

Integral annular wall structure with slots and coolant apertures manages thermal expansion in gas turbine engines.

Asymmetric inserts guide pressurized air jets through non-circular admission holes, reducing NOx emissions by controlling air-fuel mixing precision.

Convex-concave cooling sleeve guides jet and cross flows, reducing interference that raises liner surface temperatures.

Axial staged injection of fuel and air in gas turbine combustors manages reactant residence time to control emissions.

A heat exchanger delivers thermal energy to a Brayton cycle combustion chamber from external sources.

Segmenting the orifice insert from the endcover eliminates matched set testing, reducing assembly complexity.

Segmented trailing edge radii reduce coating stress and prevent failure while maintaining tight leakage control.

Adjusting air-fuel ratios enables interburner ignition for peak power, reducing engine weight and complexity.

A centerbody cap uses an external turbulator step to guide cooling airflow, reducing pollutant emissions while maintaining flame stability.

Direct metal laser sintering eliminates leak-prone braze joints and expensive EDM procedures by fabricating a monolithic fuel injection head.

Fluid accelerator mixes high-pressure steam with compressed air to maintain optimal combustor temperature and reduce NOx emissions.

Opposed axial exit ports direct cooling air parallel to swirler flow, reducing nitrogen scavenging and NOx formation in gas turbine engines.

Segmented parallel conduits adjust head losses to ensure uniform flow distribution and prevent coking.