Continuous Combustion Chamber TRIZ Cases

Downstream ammonia injection after the swozzle improves ammonia-air mixing, avoids film formation, and stabilizes low-flammability combustion.

Strategic bumps and segmented exit-frame panels steer exhaust gas and purge air to limit gap ingestion and cut turbine emissions.

Additive manufacturing merges the mount, stem, and heat shield into one injector body, reducing weld-heavy assembly time, cost, and heat exposure.

Downstream gas supply openings let a gas turbine combustor handle liquid and gaseous fuels with lower design complexity, thermal stress, and emissions.

A CMC heat shield, seal member, and purge orifices protect the fuel nozzle/swirler assembly from hot gas ingestion and frequent replacement.

A collar around the secondary fuel injector creates larger upstream and smaller downstream purge paths to limit exhaust gas ingestion and cut emissions.

Built-in chute turbulators create turbulence to improve fuel atomization and air-fuel mixing while disrupting wall fuel films in AM combustors.

A toroidal recirculation zone with rapid quench and lean burn improves altitude relight while shrinking gas turbine combustor size.

Bleed openings in combustor casings raise vortex driver jet momentum to stabilize toroidal vortices in smaller, lighter gas turbines.

Counterbored CMC cooling holes let coatings cover the diffuser section without plugging, preserving film cooling and simplifying manufacture.

Counter-rotating swirlers, staged fuel delivery, and cooled centerbody passages stabilize lean liquid combustion while cutting NOx and particulates.

Fuel is cracked inside engine component passages to cool hot turbine boundaries and return recovered heat to combustion with lower-emission fuels.

A triple-wall combustor cooling structure traps particulates on an intermediary layer, protecting heat shields from deposition and blockage.

Additively manufactured premix injectors improve air-fuel mixing to cut NOx, CO, and CxHy while extending gas turbine nozzle life.

Radial fuel injection and cellular mixing passages help a hydrogen combustor improve fuel-air stability while limiting flashback risk.

Bleed and inlet openings tune vortex driver jets to sustain stable trapped vortices in compact combustors and improve combustion efficiency.

A one-piece atomizer tip with tapered swirl chamber cuts geometric stack-up, calibration time, and manufacturing cost in gas turbine fuel atomizers.

Mixing inert gas with gaseous fuel slows flame speed and temperature, reducing injector flashback while preserving combustion efficiency.

Tortuous baffle-lined mixing passages delay ignition, improve hydrogen-air mixing, and help prevent flashback in gas turbine combustors.

A variable-area arcuate gallery distributes fuel more evenly in a turbine nozzle while limiting heating, degradation, and coking.

Cooling air routed through a head-shaped fixture passage lowers liner support head temperature in a gas turbine combustor while preserving support integrity.

Dimples at impingement and flow convergence points redirect cooling air and particulates to keep gas turbine heat shields clear and effective.

Angled circumferential fuel passages improve penetration and jet collision, helping engines mix fuel with compressed air and reduce flashback risk.

Complementary cowl indentations break up and time vortex impingement to cut noise and vibration in gas turbine engines.

A secondary gas duct surrounds a fuel-gas jet to improve mixing, penetration, and combustion stability for added gas turbine thrust.

Purge openings, aft-curved lips, and tuned swirl reduce flame holding and flashback in hydrogen-capable turbine combustors.

Integrated resonator and cooling passages in a combustor wall core cut detonation-driven acoustic pressure and wall heat in ramjet engines.

An optical sensor placed in the fuel passage detects hydrogen flame onset early, enabling fast fuel control and lower sensor heat exposure.

Cooling channels built into a combustor tongue joint cut leakage-driven hotspots and improve joint durability in high-heat gas turbine sections.

A two-stage combustor with microburners and a shared annular chamber enables flexible hydrogen, ammonia, methane, and natural gas combustion with lower emissions.

By excluding the highest and lowest combustor temperature readings, control stays stable despite sensor drift, helping maintain combustion margins and lower NOx.

Cooling jets and spacer channels seal tile gaps and cool combustion chamber supports to limit hot gas ingestion, creep, and fatigue.

Angled circumferential fuel passages direct jets to a shared target point, improving combustion mixing while reducing flashback and flame holding.

A central air passage and circumferential fuel outlets improve gas turbine fuel-air mixing and penetration while reducing flashback and flame holding.

Multiple fuel injection zones shorten peak-temperature residence time in a compact turbomachine combustor, cutting NOx emissions.

Separate ammonia and nitrogen-free fuel injection zones hold flame temperature within safe limits and reduce combustor damage at low ammonia co-firing.

Split cooling paths send diffuser air to vane leading edges and intercooler air to trailing edges for better HPT stator temperature control.

Spaced fuel and fluid channels mix hydrogen with air in a secondary combustion zone to limit flashback, flame holding, and injector damage.

Vortex generators on a fuel nozzle support matrix improve hydrogen-air mixing, stabilizing combustion and reducing flashback risk.

A radially guided rotating detonation wave boosts gas turbine thrust while cutting augmentor length, volume, weight, and pressure loss.

Integrally formed scoops and passages in an additively manufactured combustor v-band ring improve cooling flow and reduce static pressure loss.

Staged preheating, vaporization, superheating, and ammonia separation improve decomposition completeness and cut NOx before turbine combustion.

Sensors and closed-loop fuel control keep blended fuels within a target Wobbe Index for more stable, homogeneous combustion.

A two-stage fuel-oil heat exchanger and recirculation layout raises combustor inlet fuel temperature at cruise while improving oil cooling.

A perforated distributor and simplified swirler premix hydrogen with air to limit thermal damage in turbine engine combustors.

Curved fins and upstream fillets keep cooling air attached in aircraft engine partition walls, improving heat transfer with less compressed air.

Embedded passlets redirect high-pressure air within a turbomachine diffuser to shorten combustor length while limiting pressure loss and weight.

Swirler vane angles and converging passages raise airflow velocity to prevent flame holding and flashback in hydrogen-capable combustors.

Integrated injector panels seat across combustor rails to cut cantilever stress, eliminate burner seal leaks, and accommodate thermal expansion.

Shaped driver holes and slots raise jet angle to stabilize toroidal vortices, cut hot streaks, and enable a shorter gas turbine combustor.