Continuous Combustion Chamber TRIZ Cases

A turbine engine combustor heat shield uses cooling apertures with distinct included angles to direct airflow for targeted thermal management.

Sensors monitor fuel density and temperature while the control system prevents boiling by adjusting thermal management parameters.

Multi-layer auxetic structure overlays distinct porous sheets to create tailored negative Poisson's Ratio behavior.

Softens nickel superalloys by precipitating incoherent gamma prime phases, resolving the trade-off between high temperature strength and forging workability.

Non-uniform water injection ports distribute heat release rates to reduce combustion oscillation in gas turbine flames.

Segmenting fuel injection into rotary and nozzle units optimizes atomization, reducing smoke emissions and eliminating complex ignition systems.

Segmented turbine nozzle tips discharge steam and fuel at distinct angles to enhance mixing, reducing carbon monoxide emissions while stabilizing the flame.

Integrating fuel pathways into a structural mounting strut eliminates bypass manifold obstructions and reduces pressure variations.

Segmented struts and sliding joints reduce thermal stress concentrations by allowing radial fairing movement during gas turbine engine transients.

Compressor bleed fluid injection into the combustor modifies fuel distribution to prevent flashback and ensure stable combustion with highly reactive fuels.

A gas turbine combustion section positions a fuel nozzle with defined separation from a heat shield to optimize the internal flow path.

Tapered upper and lower orifices in a DME fuel nozzle prevent flame back and ensure stable combustion despite high fuel velocity.

Segmented can-combustors with premixed burners stabilize combustion dynamics across varying load conditions.

A dual pressure sensor system measures upstream and downstream fuel injector pressures to detect flame holding conditions in gas turbine combustors.

A premixing direct injector nozzle uses cooling fins to manage thermal energy and prevent premature ignition of high-reactivity fuels.

Injecting gas fuel into the liquid fuel cartridge annulus mixes with purge air, lowering flame temperatures and reducing NOx emissions.

Asymmetric tapered cooling cavities accelerate airflow to reduce thermal stresses on turbine engine combustor walls without increasing structural complexity.

Radially-extending supports slidably engage a heat shield to floatingly suspend it around a fuel manifold.

Post-machining caulking corrects excessive orifice diameters in refractory alloys, preventing part scrap and restoring permeability specifications.

Segmented axially staged fuel inputs reduce mechanical complexity of nozzle connections while improving mixing efficiency and combustion control.

A variable geometry combustor adjusts airflow and fuel flow to manage soot emissions in gas turbine engines.

An annular flange heat shield with an airflow ramp redirects hot gas flow to lower thermal gradients in diffuser cases, extending component life.

Asymmetric fuel injector patterns dissipate thermoacoustic instabilities by creating distinct flame zones with varying properties.

A pre-diffuser fairing with spaced side walls forms a cavity that acts as a thermal barrier, reducing stress on struts and the inner diffuser case.

Three-stage injector system uses a dual-circuit distribution device to manage fuel flow across varying engine speeds.

Flexible liner seals accommodate axial and radial thermal expansion between hot and cold combustor walls, reducing leakage and stress.

Segmented annular fuel injection with radial holes and axial air guide grooves suppresses NOx generation while preventing backfiring.

Pins transfer aerodynamic loads from nozzle airfoils to external structures, reducing internal stresses and leakage.

An oblique intermediate portion deflects radiant heat and flames away from the fuel-air mixture in a gas turbine injection nozzle.

A fuel injector with an air blast nozzle atomizes liquid fuel using pressurized air to heat exhaust gases efficiently.

Segmenting the rotating detonation combustor from a primary chamber handles transient conditions while maintaining steady-state specific fuel consumption.

Segmented fasteners replace brazing to allow easy removal while maintaining attachment strength.

Annular premixed burners reduce device complexity while maintaining flame stability and lowering emissions in gas turbines.

Counterweight mechanisms balance heavy combustion cans while slide assemblies ensure alignment during turbomachine maintenance.

Flexible liner deflects to form impingement chambers at hot spots, reducing surplus cooling air and improving Brayton cycle efficiency.

A reversible fastening device secures thermoinsulating tiles in gas turbine combustion chambers using a bayonet-connected bushing and locking seat.

Segmented in-wall flow paths reduce temperature gradients and stress concentrations in gas turbine transition pieces.

Radially inwards curved inlet eliminates sharp edges to prevent local recirculation zones and flashback.

An ellipsoid attachment pin distributes load across curved contact surfaces, eliminating bending moments at ceramic matrix composite holes.

A combustor cooling panel uses a flow guide to direct compressed gas over the outer surface for enhanced heat transfer.

Movable flap check valve prevents hot gas backflow into cooling passages, maintaining lower wall temperatures.

A trapped vortex converts NOx and N2O into water and nitrogen while maintaining combustion stability against lean blow out.

A gas turbine component uses cooling holes positioned to maintain a minimum ligament distance between adjacent outlets.

Perforated lining damper absorbs acoustic energy in gas turbine fuel pipes, reducing structural vibrations without increasing fuel pressure requirements.

A turbine film cooling hole features a conical diffusing section that expands radially to discharge cooling air effectively.

Yttrium aluminum garnet reaction coatings prevent corrosion and erosion of ceramic heat shields, extending component lifetime in gas turbines.

A gas turbine combustor uses primary and secondary fuel injectors to manage combustion zones.

Embedded RMC microcircuits reduce cooling flux by 40% while maintaining film coverage, resolving the trade-off between hot spot temperature and emissions.

Annular combustion chamber modifies air injection orifice distribution to ensure circumferential flame propagation without adding injectors.