Continuous Combustion Chamber TRIZ Cases

Canted mixing tubes induce swirling flow to stabilize lean premixed flames, reducing NOx emissions while preventing blowout.

Segmented floating collar and bonded flange allow thermal barrier coating to cover combustor edges, preventing hot air exposure and radial cracking.

Multi-coaxial burner system manages fuel-air mixing via inner and outer injection zones to stabilize combustion under fluctuating hydrogen concentrations.

A swirling flow generating part converts axial jet flow into a vortex ring to accelerate fuel mixing within the combustion duct.

A passive bypass valve extracts compressor discharge air to adjust combustor temperature, maintaining emissions compliance during gas turbine load reductions.

A combustor liner element uses internally threaded protuberances to affix securely to the structural wall.

Segmented walls with optimized pressure drops enhance convection while reducing foreign matter accumulation on the heat shield.

Axially staged bundled tube nozzles and radial injection lances balance airflow to reduce NOx and CO emissions.

A gas turbine combustor cooling structure uses a guide to direct coolant along the inner wall surface for film cooling.

Spherical bearing surfaces in a combustor sealing element allow relative movement to prevent fluid flow separation and maintain stable combustion efficiency.

A kinked heat shield panel conforms to shell geometry to eliminate gaps between thermal protection components.

Modular cartridges with integral chutes improve fuel-air mixing uniformity while avoiding manufacturing complexity and integrity issues from brazing.

Injecting oxygen-enriched gas via catalytic hydrogen peroxide decomposition sustains thrust at high altitudes where atmospheric density drops.

Heat shield panels with intermittent pin fins improve wax removal during investment casting, reducing thermal stresses.

Duplex tab obstacles with compound radial and circumferential inclination accelerate turbulent flames through enhanced fluid flow turbulence.

Staggered cooling guides with concave surfaces direct compressed air toward the inner liner, resolving low heat resistance in gas turbine combustors.

Resilient support structures allow axial and radial movement of the ceramic liner to mitigate thermal mismatch and prevent cracking.

A dual-annular counter-rotating swirler fuel-air mixer pre-mixes fuel and air using opposing rotational flows within concentric plenums.

A combustor swirl cup uses an internal impingement ring to cool the flameholder via bypass air flow.

Integrated cooling passages direct fluid onto critical thermal regions, extending service life by reducing thermal loads on the air swirler components.

Segmented annular channels and web pockets direct cooling fluid through combustor panel bosses, reducing thermal stresses caused by excess material thickness.

An inner main air passage guides fuel into the core flow path, resolving wall surface bias and reducing NOx emissions.

Oriented effusion holes in the heat shield panel distribute cooling air to manage thermal stress and improve protection efficiency.

An adjustable combustor swirler modifies blade angles to stabilize the central recirculation zone under varying engine operating conditions.

A deflector redirects axial fuel flow into a circumferential path within an annular plenum to ensure continuous circulation.

Strategic dimples with varying depths mitigate hot spot temperatures and minimize cracking without increasing cooling hole density.

Axial ribs and circumferential pins create turbulence in compressed air to enhance heat transfer on gas turbine combustor liners.

Segmented premixer tubes and annular fuel circuits manage local mixing intensity to prevent flashback while reducing NOx emissions.

A premix gas burner uses a frusto-conical shaped segment and an annular porous wall to direct gas flow for combustion.

A swirling force application unit converts axial air flow into a vortex pattern that stabilizes combustion and reduces NOx generation in gas turbine combustors.

A gas turbine fuel control system measures background nitrogen oxide at the air inlet to adjust pilot fuel distribution dynamically.

Integrating a threaded stud into a ceramic matrix composite blade track eliminates differential thermal expansion stress between dissimilar materials.

Angled holes in the aft combustor rail focus airflow onto the first vane platform, reducing heat distress and mixing losses.

A turbine engine combustor heat shield directs cooling air through a defined gap to displace hot combustion gases downstream.

Closed-loop control of priming flows reduces fuel spikes and dips, enabling aggressive acceleration profiles.

A coupling assembly with a movable block secures a combustion liner to an outer sleeve.

A grommet with integrated cooling air flow channels directs airflow to reduce component temperatures.

Offset cooling conduits with decreasing cross-sections enhance heat transfer through fluid impingement, reducing clogging risks by increasing turbulence.

Segmented prefabricated tiles reduce manufacturing complexity while enhancing coating integrity in high-temperature gas turbine environments.

Micro-decomposition holes eject ammonia-doped fuel at high speed, entraining over-fire air to reduce NOx emissions.

Structural bridges absorb tensile and shearing forces at parting planes, preventing shell tears caused by reduced weld seam strength.

Shared manifolds link nozzles to multiple valves, compensating for failures while reducing weight and complexity.

Nested fuel plenums and shielding air lines reduce device complexity while accommodating thermal expansion in gas turbine injectors.

Catalytic backside cooling reduces flame temperature and prevents flashback, achieving ultra-low NOx emissions below 2 ppm.

Segmented cold skin sliding joints accommodate thermal expansion, reducing air leakage and cooling air demand in gas turbine engines.

A sequential combustor assembly adjusts air flow ratios between stages to stabilize flame position and control inlet temperature.

Segmented fuel nozzles balance flame stability against low NOx emissions by suppressing or promoting local turbulence in a coaxial jet combustor.

Spherical contact surfaces and elastic elements compensate for manufacturing misalignments, reducing wear and air leaks in turbomachine fuel injection systems.

A component handling assembly uses a rotatable beam and counterweight to manipulate turbomachine parts.

A gas turbine cooling arrangement directs flow through wall passageways to cool hula seals and caps.