Continuous Combustion Chamber TRIZ Cases

Upstream-directed cooling film holes angle airflow against the main gas stream to reduce heat transfer rates and thermal stress on engine components.

A film cooling hole diffuser section generates anti-counter rotating vortex pairs and delta vortices to enhance wall adherence.

Merging peripheral and core dilution flows in a sub-chamber resolves hot spots around dilution holes while maintaining structural simplicity.

Independent cooling circuits manage differential thermal expansion between turbine and exhaust casings, preventing centering fit misalignment during operation.

A laser ignition system focuses optical energy into the combustion chamber bulk to ignite fuel, eliminating electrode carbon deposition and wall heat loss.

Segmented CMC sectors absorb thermal expansion differences between metal casings, maintaining axial stability under high stress.

A pressure sensor mounts on a cross-flame tube to detect combustion oscillations across multiple combustors.

A thermal barrier coating with partially filled columnar voids containing CMAS-reactive material.

Spool piece with separate oxidant injection and recycle gas extraction ports isolates streams before combustion.

Disengaging the liner from the turbine vane carrier using jacking screws or a rail system keeps the combustor in place, reducing maintenance time.

Segmented cooling hoods reduce pressure drop and exhaust emissions by ejecting heated air away from the combustor inlet.

Stepped inclination profile prevents ice clogging and maintains consistent fuel flow.

A combustion chamber guide device uses a metal flange and floating ring to secure energy supply elements within refractory walls.

A machinable ceramic insert sandwiches between a silicon carbide matrix component and a ply, enabling machining without exposing fibers that cause cracks.

A trapped vortex combustor directs continuous annular airflow through a radial driver channel to enhance fuel pre-mixing and pre-vaporization.

A combustor assembly uses a moveable interface between liner segments to regulate dilution fluid entry and accommodate thermal expansion.

Static orifices eliminate hysteresis and tolerance sensitivity while maintaining directional bias.

Flow management devices adjust annulus areas to ensure uniform fuel-air mixture, reducing nitrogen oxide emissions in gas turbines.

An inlet ring creates turbulence to improve fuel-air mixing and flame-holding, addressing insufficient combustion pressure in pulse jets.

Cowl collars redirect compressed air tangentially, eliminating radial velocity components that destabilize flames.

Multi-lobed cooling holes reduce flow separation and fluid requirements, improving thermo-mechanical fatigue tolerance.

Segmenting combustion into detonation and deflagration zones resolves the trade-off between thermodynamic efficiency and stability.

Segmented air passages route combustion pressure waves to a resonator, reducing vibration while maintaining lower temperatures without special cooling.

A floating collar louver directs coolant film along the combustor heat shield face to maintain thermal protection.

A gas turbine assembly positions pressure sensors in the plenum between the compressor outlet diffuser and outer casing to monitor acoustic oscillations.

Film and impingement cooling holes in concentric mixers prevent cold air from extinguishing the pilot flame, minimizing CO emissions.

Tangential flame outlet swirls ignition gas around the main fuel spray, resolving stability and relight bottlenecks in gas turbine engines.

Segmented manifolds with dynamic control valves maintain nozzle pressure ratios, preventing over-speed and ensuring safe operation across varying fuel types.

A segmented annular fuel manifold uses removable ring segments and engine case access ports to facilitate individual component replacement.

Porous transition layers vent gas bubbles via substrate openings, eliminating spallation caused by trapped reaction products in environmental barrier coatings.

Segmented tubes with circumferential fine injection holes create localized flames that protect the main combustion zone from thermal damage and flashback.

A thimble with converging and recovery portions channels cooling air into a combustor assembly.

A Helmholtz damper uses a movable piston to dynamically adjust its internal volume and resonance frequency.

Segmented hollow-cone and full-cone nozzles prevent flashback in high-temperature hydrogen combustion while maintaining stable flame anchoring.

Cooling passages dilute fuel concentration near the spout port to prevent flashback ignition in the nozzle.

A gas turbine engine heater system uses exhaust heat to maintain diesel engine temperature while an electric generator charges the vehicle battery.

Axially slidable combustion chamber assemblies decouple thermal expansion movements, maintaining precise positioning and stable combustion stability.

A hemispherically-shaped dome directs compressed air through angled openings to condition flow before mixing with fuel in a gas turbine nozzle assembly.

A one-piece combustion deflector integrates swirlers and attaches via flexible arms to the cowl.

Segmented fuel injection locations reduce liquid fuel emissions by improving vaporization and mixing while maintaining operational versatility.

A turbine fuel nozzle uses a helical swirler passage to mix air and fuel along a spiral trajectory.

Graded porosity in floatwall panels directs airflow to hot spots, reducing cooling air demand while maintaining structural integrity.

A hemispherical dome assembly directs fuel-air mixtures through passageways to control velocity and minimize recirculation zones at the combustor inlet.

Radial convergence of pre-mixed air-fuel mixture via inner tube structures stabilizes flame and reduces NOx emissions without increasing primary aeration.

Double-wall cooling circuit with bore-cooled pedestals ejects air for film cooling, reducing metal temperatures and cycle efficiency penalties.

Dimples and protrusions in the combustion liner redirect hot gases, reducing flame scrubbing and extending liner life.

A radiused edge on a combustor liner panel blends into the hot side to protect thermal barrier coatings.

A pivotal servicing tool applies radial force to turbine combustion liners.

A trough surrounding a combustor panel boss directs cooling air to the inner face, resolving high temperature distress in gas turbine engines.