Continuous Combustion Chamber TRIZ Cases

HF etching removes damaged environmental barrier coatings at the oxide layer, enabling recoating of silicon-based turbine parts.

High-pressure air jets and elongated mixing chambers improve hydrogen-air mixing, cut pressure loss, and support stable low-emission combustion.

Partially mounting the torch igniter inside the high-pressure case cuts pressure differential, wall thickness, leaks, and rupture risk.

A trapped vortex chamber and staged fuel ports enable a compact burner nozzle to maintain low NOx combustion without bulky external swirlers.

Spaced seal cutouts create defined cooling gaps in a heat shield, balancing hot-gas sealing with targeted airflow and lower material use.

Concentric annular dilution holes and spaced fuel injectors improve air-fuel mixing to lower NOx while maintaining combustion efficiency.

Injecting a mixed wash fluid through late lean fuel injectors reaches deeper turbine stages, cuts residue-driven corrosion, and reduces wash frequency.

Separate radial air and hydrogen channels prevent swirl inside the nozzle, stabilizing hydrogen combustion and keeping flame temperatures low.

Captured CO2 is reinjected into the gas turbine to raise exhaust concentration, enabling smaller, lighter carbon capture units offshore.

Cooled bleed air and a swirled mixer keep hydrogen below auto-ignition temperature, preventing flashback and nozzle damage in turbine combustors.

Angled mixing tubes remove outlet gaps around the fuel supply part, using self-cooling flow to prevent nozzle overheating and balance temperatures.

Auxiliary combustor exhaust preheats hydrogen fuel to cut thermal stress and lower NOx in gas turbine combustion.

Waste heat vaporizes liquid hydrogen into gaseous fuel for combustors, improving fuel adaptability and combustion efficiency.

An isolating conduit lets backfire sensors be serviced without shutdown, enabling continuous detection in multi-nozzle combustion chambers.

An access hatch in the high-pressure engine case enables direct torch ignitor maintenance while preserving sealing integrity and reliability.

Discrete effusion and impingement apertures cool the combustor wall boss while cutting thermal stress, pressure drop, stagnation, and backflow.

Segmented fuel cups, baffles, and dilution air shape combustion to lower NOx while maintaining flame stability and efficiency.

Nested heat shields, isolated fuel conduits, and an air gap keep the nozzle below coke-forming temperatures while preventing fuel backflow.

Angled air passages and a secondary air inlet create swirl for hydrogen-air mixing, stabilizing combustion and preventing flashback.

Steam recovered from combustion products is reinjected through the injector to regulate air and fuel flow and improve turbine combustor efficiency.

Segmented fuel circuits, cooling channels, and a heat shield limit coking in airblast injectors while enabling line-replaceable maintenance.

Additive manufacturing turns the injector head into one piece, removing brazed joints to prevent internal leakage, cut weight, and simplify production.

Heated hydrogen drives a fuel turbine to power the pump, while pre-heating limits recuperator frost and supports efficient engine operation.

Multiple mixing chambers and HP air jets improve hydrogen-air mixedness, cut pressure loss, and support low-emission flame holding.

Counter-rotating inner and outer flow guides improve fuel-air mixing in a combustor transition duct, cutting unburnt hydrocarbons at higher temperatures.

Recuperated hydrogen fuel heating and micromix injection improve combustion stability, cut emissions, and lower fuel use in aircraft gas turbines.

Sacrificial graphite-fiber springs create helical cooling holes in ceramic turbine parts, improving heat transfer without damaging the structure.

A nonlinear resonator neck in the combustor wall damps acoustic vibrations, improving tuning flexibility without disrupting aerodynamics.

Extending mixing passages through an open fuel plenum delay hydrogen ignition and keep mixture velocity above flame speed to prevent flashback.

Dynamic fuel splitting across multiple burners maintains ammonia combustion ratio over changing loads to cut NOx and unburned ammonia.

Clocking temperature rakes against burner arrays creates multiple circumferential positions for cleaner turbine exhaust temperature mapping.

Constant-volume combustion chambers and exhaust thrust are combined in one rotating engine to improve energy extraction beyond piston and gas turbine cycles.

A gas turbine shaft cover uses thick outer and thin inner strut sections to strengthen diffuser connections while limiting airflow resistance.

Swirled and non-swirled premixer tubes guide pilot and fuel-air flow to improve gas turbine mixing, stabilize flames, and cut NOx emissions.

A one-piece additively manufactured combustor body integrates liner, injector, frame, and passages to cut parts, welds, leaks, and build time.

Liquid hydrogen is pumped above critical temperature and pressure, then metered by throttle control for direct gas turbine combustion.

Selective pilot energizing ignites injected fuel to shape flame distribution and mitigate thermoacoustic instability across engine operating conditions.

A minimum of five burner-vane clocking positions improves temperature and flow distribution analysis for better turbine efficiency.

Photonic curing and pulsed heating densify individual CMC plies faster, cutting stress, porosity, and high-temperature exposure.

Sliding radial studs and a ball joint let the fuel manifold expand radially while staying axially fixed, cutting thermal stress and preserving air metering.

Annular air inlets with same-direction swirl blades premix hydrogen to suppress backfire, lower flame temperature, and protect the burner.

Inner and outer lever arms isolate distributor plate expansion from the manifold, reducing thermal stress and extending fuel injector life.

A split fuel nozzle layout and SAF use cut nvPM across idle to takeoff while preserving gas turbine combustor performance.

Multiple combustor liners are nested in a green-state additive build, then assembled and sintered to cut footprint, time, and cost.

A hybrid dilution passage merges discrete jets with annular flow to improve combustor mixing, cooling, and NOx control.

A wind shield cover around gas turbine fuel nozzles redirects combustion air to reduce flow deviation, pressure loss, and abnormal combustion.

A sliding radial stud and fuel inlet support lets the combustor fuel manifold move radially while staying axially fixed, reducing thermal stress.

Unequal upstream and downstream purge paths around a secondary injector improve low-temperature combustion, cut emissions, and protect combustor life.

Porous mixing passages through a fuel plenum delay hydrogen ignition downstream and stabilize gas turbine combustion by arresting flashback.

Central fuel injection with inner and outer air slots shifts hydrogen-air mixing downstream to reduce burn back in gas turbine combustors.