Continuous Combustion Chamber TRIZ Cases

Segmented mixing tubes create uniform fuel-air mixtures to reduce NOx emissions in gas turbine engines.

A radial fuel distributor mixes gaseous hydrogen with air in a dedicated mixing chamber to ensure stable combustion.

A nested fuel injector design mixes air and fuel through injection holes to optimize combustion efficiency.

A retaining clip secures a swirler and heat-shield to a combustor dome, accommodating thermal expansion while reducing component count.

Integrated torch injectors merge fuel delivery and electrothermal ignition to resolve redundancy gaps in gas turbine combustor systems.

A directionally controllable ceramic matrix composite insert redirects cracks toward low stress regions.

An annular resonator with tuned hole patterns absorbs acoustic energy, reducing destructive screech dynamics during gas turbine part load operations.

Segmented premixing zones stabilize lean flames while reducing NOx emissions.

Internal cooling passages in a swirl vane use fuel as a heat exchanger to protect the premixer from thermal damage during flame holding events.

Asymmetric smoke apertures admit tangential pressurized air to create an aerodynamic barrier blocking unburned fuel escape and reducing exhaust emissions.

Shielding assembly directs compressed air through fuel sweep openings to remove leaked fuel, preventing auto-ignition risks near high-temperature components.

A side-fed shielded fuel inlet tube directs pressure radially to reduce axial load on the manifold.

Angularly offset centerlines in the fuel injector nozzle and air swirler structure create tailored recirculation zones that reduce hot spots.

Radially slidable connectors in an annular fuel manifold eliminate bulky curved pipes, reducing weight and leakage while accommodating thermal expansion.

Combustor liner projections generate turbulent airflow to enhance convection cooling of the outer surface.

Streamlined body with integrated vortex generators accelerates mixing quality while preventing flashback in gas turbine burners.

A turbine combustor separates recirculated exhaust gas into distinct volumes for liner cooling and downstream extraction.

Prefabricated arc segments restore flange stiffness and structural support without requiring extensive additional tooling during repair.

Effusion cooling apertures in heat shields direct coolant to form protective films on annular walls, reducing overheating and minimizing coolant consumption.

Segmented thermal barrier coatings reduce base metal temperature by 167°C and limit thermally grown oxide growth through localized splatted layer cushioning.

An insulating air gap between concentric annular walls accommodates differential thermal expansion while a sealing member prevents fuel ingress.

A tapered and cylindrical installation insert mediates brazing between fuel tubes and assembly plates, accommodating misalignment to simplify manufacturing.

Resilient securing posts maintain fuel nozzle alignment via elastic deformation, eliminating misalignment gaps and reducing mounting complexity.

Integral combustion chamber segments merge frame and inner walls via additive manufacturing to enable complex cooling geometries.

Insulated tubes deliver liquid fuel to prevent nozzle coking, while pneumatic mixing enhances homogeneity and extends combustor liner service life.

Axial cam mechanism compresses insert against combustor end cover, eliminating multiple fasteners and reducing assembly complexity.

Slip joints and cooling chambers reduce thermal stress in gas turbine cross-flame ducts.

Slanted premix tubes in a fuel injection assembly mix hydrogen with air, preventing flashback and reducing NOx emissions.

Radial slots between circumferential segments relieve hoop stress and prevent thermal barrier coating cracking.

A wave pattern combustor liner panel directs impingement flow toward convex peaks to enhance convective heat transfer coefficients.

Radial mixing passages in the combustor injector improve fuel-air homogeneity while preventing flash back from primary zone cross flows.

An annular deflector guides air film along the injection bowl to cool and direct coaxial fuel flows within a turbine engine combustion chamber.

Monitoring soot accumulation with a combustor particulate matter sensor detects fuel leaks early, preventing seal failure damage and hardware degradation.

Merged cooling paths reduce air consumption and NOx emissions.

Curved recesses in L-shaped covers reduce thermal stress at weld zones, preventing cracks without requiring fuel preheating.

Increasing pilot swirler airflow reduces combustion dynamics in high power gas turbine engines.

Counterweight balancing offsets heavy flow sleeve mass, enabling manual installation in confined gas turbine engine spaces.

A coaxial bushing and ring guide device uses segmented welding zones to join annular parts without obstructing transverse movement.

A hooded swirler reduces air velocity and pressure to resolve ignition failures caused by high differential pressures across the swirler.

A dual fuel nozzle adjusts jetting hole diameter via a switching plate to handle natural gas and DME, resolving combustion instability during fuel switching.

An arcuate heat shield minimizes pressure oscillations by guiding flow patterns and eliminating unsteady heat release zones.

Periodic burner switching minimizes thermal stress and carbon monoxide emissions during low load operation.

Injecting hydrogen into the combustion chamber stabilizes lean burn regimes, reduces NOx emissions, and prevents nozzle overheating through improved turbulence.

Interlocking arms accommodate thermal expansion to reduce mechanical stress on the bullhorn without compromising positioning accuracy.

Differential pressure sensor detects sand plugging in combustor cooling holes, preventing thermal distress and premature engine removal.

Sigmoid profiles trap feather seals between segmented tiles to prevent airflow leakage while simplifying manifold complexity.

Segmented acoustic panels merge structural layers to reduce assembly complexity while maintaining damping performance.