Continuous Combustion Chamber TRIZ Cases

This case uses downstream seal cavities between CMC liners and dome or cowl connections to preserve air for combustion and cooling.

This combustion nozzle uses a separate burner seal with air-guiding ducts to reduce thermal stress and crack risk.

This case combines liquid-hydrogen pumping and variable-area metering to deliver supercritical fuel evenly to turbine injectors.

This gas turbine combustor distributes smaller pilot nozzles between nozzle segments to preserve main-nozzle space and stable combustion.

A multicavity damper targets low- and high-frequency combustion tones, broadening attenuation while limiting separate damper units.

Concentric tubes redirect pre-mixed air and fuel into rotating flow, improving flame stability and lowering NOx at high aeration.

A CMC bulkhead panel reduces effusion cooling needs, protecting combustor flow patterns and minimizing material fatigue.

A gas turbine combustor uses intersecting air paths to shape the flame, limit liner scrubbing, and improve temperature durability.

Diffuser-integrated cyclonic separators route clean and debris-laden streams, limiting aperture clogging in turbine-engine airflow.

Rails and variable-porosity channels target cooling air where needed, extending tile life without excessive cooling flow.

Double-walled feed arms and air gaps insulate hydrogen fuel, while an integral manifold limits leakage around the combustor.

This case uses selectable fuel filling profiles to balance power response and surge prevention during gas turbine acceleration.

Diverging outer branches spread flame radially and circumferentially, balancing flame stability with lower afterburner pressure drop.

Central and radial fuel injection stabilizes combustion while limiting flashback and blow-out.

Learn how boomerang-shaped wall passages improve heat transfer and cooling while limiting thermal stress in turbine blades.

Controlled co-swirling in the nozzle and swirler reduces recirculation zones, supporting hydrogen-fuel combustion without flashback.

A unitary stepped CMC combustor liner uses controlled slots to manage thermal gradients, reduce heat load, and extend service life.

Swirlers and staged mixing in the fuel supply assembly limit flashback, control flame temperature, and protect turbine components.

A high-voltage plasma micro-injector supports hydrogen, ammonia, SAFs, and mixtures while reducing modifications and emissions.

A dedicated vent line and flame arrestor purge hydrogen and block flame spread during emergency gas turbine shutdown.

This gas turbine case uses articulated spherical-joint ducting to cool moving exhaust flaps with less airflow and reduced thrust penalty.

This gas turbine combustor case replaces failure-prone seals with flexible struts to limit thermal stress and preserve airflow.

Imaging a coated turbine preform locates hidden features before machining, guiding precise cooling aperture formation.

This case uses separate fuel/air circuits and flame-shaping flow to limit auto-ignition risks while stabilizing hydrogen combustion.

This case uses a heat exchanger and dual fuel supplies to vaporize liquid hydrogen and control turbine-engine combustion.

A movable swirl generator redirects combustion products radially, reducing uneven cuts, over-cutting, and webbing in borehole conduits.

This combustor assembly sets radial and axial gaps, with at least one below 0.150 inches, to cool liners and protect attachments.

A dispersion plate and impact cooling path protect the nozzle tip while supporting uniform hydrogen fuel-air mixing.

Asymmetric rail-integrated studs reduce dirt zones and preserve combustor panel cooling.

Shingled floatwall panels use pins and apertures to cool combustors and limit dirt buildup.

Bayonet joints and spring retention secure a CMC combustor deflector while supporting higher temperatures and reduced cooling needs.

A dynamic valve redirects air between AFS and head-end fuel stages to lower firing temperature for reactive fuels.

A diffuser-plenum separator uses cyclonic separation to protect engine components while routing debris-laden air for combustion dilution.

A separator removes debris from a turbine engine's compressed airflow, reducing clogging while directing usable air to the combustor.