Continuous Combustion Chamber TRIZ Cases

Hollow cavities and radial apertures in pre-diffuser struts enable secondary cooling airflow while reducing weight and maintaining structural rigidity.

A reverse flow combustor liner uses a compound-angle frustoconical outer section to optimize airflow patterns and maintain structural clearance.

A premixed burner reduces cross-sectional area downstream of the injection device to accelerate flow velocity and stabilize combustion.

Merging a secondary servo valve into the primary loop eliminates dedicated redundant components, reducing weight and complexity while maintaining reliability.

Parallel gas tubes connected to a distribution block ensure similar thermal expansion, preventing mechanical deflection of the injector head.

Flow sleeve directs fluid across exterior turbulators to disrupt laminar flow, preventing thermal damage at temperatures exceeding 1500° F.

Segmented edge webs increase natural frequencies to reduce vibration loads while maintaining uniform cooling gaps.

Segmented cooling jackets with rounded entry edges guide airflow into annular combustion chambers, reducing flow losses caused by manufacturing tolerances.

Tapered fuel nozzles and air holes enhance gas mixing, preventing flashback risks in hydrogen-fueled turbines while reducing NOx emissions.

Photonic communication transmits signals from a gas turbine no-flame region to a detector, resolving indirect detection limitations.

Adjustable resonating tube attenuates dynamic pressure oscillations across varying frequencies while preserving liner structural integrity.

Merging resonator volume with annular space reduces NOx emissions while damping thermoacoustic oscillations without extra cooling air.

Seal members with angled configurations fill gaps between adjacent liner segments, directing impingement cooling air to prevent thermal hotspots.

Hydrogen injection into a swirled air-fuel mixture creates secondary wakes that stabilize lean combustion and reduce NOx emissions.

Curved pressure plates distribute clamping force uniformly across the nozzle flange, preventing localized stress concentrations that cause premature wear.

Contoured curved edges between combustor liner panels remove dead regions and steps that cause adverse local aerodynamics.

Air manifolds create cooling barriers between fuel streams and hot housing surfaces, reducing NOx emissions while preventing flashback risks.

Segmented dampening cavities suppress thermo-acoustic vibrations while reducing cooling air consumption and maintaining wall structural integrity.

Secondary mini-combustors exhaust gases into the primary chamber, lowering NOx emissions by reducing oxygen levels and temperature.

Supplemental compressor injects pressurized air into gas turbine combustor to increase mass flow and power output.

A turbine engine cooling fluid system supplies coolant through fuel nozzles to manage component temperatures during operation and shutdown.

Annular metal sheet defines airflow cavity to eliminate heavy deflectors and prevent cooling air leakage in turbine combustion chambers.

Looped liner sections with air cavities absorb mechanical stress from thermal gradients, extending component lifecycle durability.

Integrating a curved surface with internal fuel chambers eliminates separate quaternary nozzles, reducing volume while enhancing pre-mixing.

Rotational azimuthal interlocking joins annular walls to eliminate gas leaks while accommodating thermal expansion without crack formation.

A multi-duct exhaust system uses a bypass flow regulator to redirect fluid flow from the main duct into a side nozzle.

Opposing swirls from adjacent film cooling holes merge cooling media to extend coverage and resolve narrow efficiency ranges.

An annular frame tool with radial hooks engages stoppers to rotate and remove combustor liners, reducing manual labor.

Segmented concentric annular fuel nozzle creates compact flames, reducing emissions and combustion instability in gas turbine engines.

A turbine combustor uses secondary zones to recirculate exhaust gases and lower flame temperatures.

Staggered outward and inward facing filmholes cover transition regions to eliminate localized overheating.

A heat shield protects combustor liner welds from thermal stress using a cooling fluid passage, extending operational lifetime.

Connected tangs prevent warping in pilot nozzle heat shields, maintaining airflow and reducing NOx emissions.

Colorless distributed combustion segments the flame zone to lower NOx emissions while maintaining a uniform thermal field for extended blade life.

Segmenting heat shield panels into etched layers eliminates casting porosity and thread integrity issues while enabling complex cooling apertures.

Premixed injector vanes merge mixing and combustion functions to restore pressure and temperature in gas turbine systems, increasing downstream work output.

Segmented cavities supply fuel radially and air circumferentially, reducing aerodynamic energy loss while stabilizing the flame.

Blade channels feed air to the annular cavity, reducing axial volume without compromising airflow.

A gas turbine cooling air discharge unit exchanges heat between compressed air and cooling water to lower supply temperature.

Segmented heat shields and extracted hub projections increase power output without unstacking the rotor.

Vaporizing fuel absorbs heat from compressor discharge air through a combustor liner wall, eliminating bulky external heat exchangers.

Suspension from the outer casing reduces radial bulk and injector misalignment.

A microchannel fuel heat exchanger integrates a leakage capture channel and sensors to prevent inadvertent combustion in gas turbine engines.

A single fuel injector assembly with multiple orifices supplies fuel to gas turbine mixer elements for efficient combustion.

Spiral fuel passages converge radially inward to guide flow into a mixing cavity, resolving poor fuel-air mixing efficiency in gas turbine engines.

A segmented fuel nozzle and swirler architecture distributes fuel laterally to control flame propagation within the combustor.

An integrated fuel injector heat exchanger cools compressed air via internal fuel flow, solving retrofit constraints in gas turbine engines.

Segmented orifice sets in a fuel injector premixer deliver staged fuel injection, resolving the trade-off between device complexity and multi-fuel adaptability.

A spherical swivel ball in the bearing plate rotates with the fuel injector nozzle to prevent fretting wear and air leakage during thermal expansion.