Continuous Combustion Chamber TRIZ Cases

Concentric fuel and air outlet arrays improve turbine combustor mixing while reducing flame anchoring through controlled swirl and passage trajectories.

A split fuel-flow pattern across combustor nozzle subsets, paired with SAF, lowers idle nvPM emissions and helps reduce soot and contrails.

A central gas channel with surrounding air premixing improves hydrogen and kerosene mixing while limiting flashback and NOx in aircraft engines.

Balancing 14-22 fuel spray nozzles in an RQL combustor helps SAF-fueled gas turbines cut nvPM emissions without excessive injector complexity.

Different fuel flow rates across nozzle subsets, combined with SAF, reduce nvPM emissions without sacrificing gas turbine thrust.

Pre-mixing, tip fuel injection, and flame stabilizers help compact burners keep flames stable while cutting NOx and CO emissions.

Real-time blend analysis and combustor knock signals adjust hydrogen and hydrocarbon fuel flow to keep turbine combustion stable and emissions lower.

A 14-22 nozzle RQL combustor lowers idle-to-takeoff nvPM with SAF by tuning fuel distribution while limiting soot deposits and contrails.

A 14-22 nozzle RQL combustor using SAF lowers idle-to-takeoff nvPM emissions while preserving fuel-air mixing and combustion stability.

Split fuel flow across combustor nozzle subsets and use SAF to cut nvPM emissions while maintaining gas turbine engine performance.

Split fuel flow across combustor nozzle subsets helps SAF-fueled gas turbines lower nvPM emissions at idle and takeoff while maintaining thrust.

A split fuel-flow pattern across combustor nozzle subsets with SAF lowers nvPM emissions while maintaining gas turbine thrust.

Sensors track the blended fuel's interchangeability index so control logic can adjust fuel inputs and keep combustion stable and efficient.

Cryogenic hydrogen is preheated for aircraft engines by catalytic combustion and exhaust heat exchange, cutting energy use and fire risk.

Circumferential fuel and air passages with common-plane outlets create inward swirling jets for deeper combustor mixing and lower emissions.

A split fuel-nozzle layout cuts nvPM during SAF combustion while preserving thrust across cruise, climb, and takeoff conditions.

An RQL combustor with tuned fuel spray nozzle count and SAF combustion lowers nvPM emissions while maintaining stable gas turbine operation.

Uneven fuel flow across two combustor nozzle groups lowers nvPM emissions when a gas turbine runs on sustainable aviation fuel.

An insulating combustor attachment uses a thermally resistant joint that preserves CMC thickness, cuts heat transfer, and accommodates thermal expansion.

Balancing nozzle count and staged RQL combustion helps gas turbines use SAF while cutting nvPM emissions, soot, and contrail strength.

Asymmetric turbulators on a combustion liner boost cooling air heat transfer while limiting pressure loss and liner erosion.

Effusion passages route oxidant across exposed nozzle cap surfaces to cut thermal stress and coking without disrupting fuel-air mixing.

Staged mixers and sensors adjust fuel flow by measured interchangeability index to keep multi-fuel blends uniform for stable combustion.

Separate gas and liquid passages feed a tapering annular passage, enabling flexible combustor delivery and better fuel mixing.

A swirled central gas passage and annular fuel circuits improve fuel-air mixing and combustion efficiency in turbine engine combustors.

A compliant heat shield segment adapts to thermal growth at the fuel nozzle to block hot-gas ingress and reduce coking risk.

Variable purge orifice blockage maintains airflow around a shifted fuel nozzle swirler to stop hot gas ingestion and thermal distress.

Varying hydrogen fuel temperature through separate heat-exchanger paths raises flow momentum and limits unwanted ignition at low power.

Driver air openings and a contoured liner create counter-rotating vortices that extend residence time, improve combustion, and cut emissions.

A wall deflector at the quench aperture redirects airflow and vortex patterns to stabilize combustor mixing and improve component durability.

Wave-shaped mixer vanes detach and reattach the air-flow boundary layer to boost fuel-air mixing, cut NOx emissions, and steady combustion.

A liner fence redirects dilution air into the combustor core to boost turbulence, improve mixing, cool the chamber, and cut NOX emissions.

Oxidant diverted through cap effusion passages cools exposed fuel nozzle surfaces, reducing thermal stress and coking risk.

A compliant heat shield segment accommodates thermal growth at the fuel nozzle to prevent hot-gas gaps and reduce coking risk in fuel passages.

By injecting steam downstream of trapped vortex cavities, this combustor cuts NOx, nvPM, CO, and SFC without raising flameout risk.

An axial gap that closes under hot conditions helps a fuel nozzle heat shield block gas ingress, reducing injector coking and auto-ignition risk.

Cooling path outlets are routed around the air supply pipe collision zone to block hot gas backflow and protect the combustor barrel.

Bleeding plenum air through platform and vane passages cools turbine nozzle vanes, limiting thermal erosion and extending component life.

Independent fuel staging in split annular passages cuts low-load gas turbine emissions while avoiding the efficiency loss of bleed control.

Placing the acoustic cover inside the gas turbine casing preserves combustion vibration damping while avoiding a pressure-resistant cover.

Turbulators and varied mixing lengths in gas turbine fuel nozzles improve hydrogen flame stability while reducing NOx emissions.

Multiple mixing tubes and upstream turbulators shape lean and rich hydrogen-air zones to cut NOx and stabilize turbine combustion.

Vortex generators on a combustor fuel injector improve fuel-air mixing to limit flashback, flame-holding, and NOx emissions.

Inner and outer swirl zones with a splitter and vanes control airflow to reduce flame holding and flashback in fast-burning fuel combustors.

A removable igniter head and sealing flange cut gas turbine maintenance time while preserving pressure sealing and protecting electrical connections.

Targeted slot cooling uses P4/P3 pressure drop to protect the combustor seal near first-stage HPT vanes, reducing oxidation and durability loss.

T-head bolts and flanged bushings replace combustor studs to prevent hot spots and debris buildup while supporting higher-temperature engine operation.