Continuous Combustion Chamber TRIZ Cases

Diverging diffuser walls in the mixing zone reduce pressure drop while maintaining high hot gas speed for complete combustion.

Inclined cooling orifices form protective air films along annular combustion chamber walls to manage thermal loads.

A fuel nozzle assembly merges a main body and distribution manifold into a single component featuring axially extending passages for premix flow paths.

A combustion controller calculates average mixer exit temperature using polynomial correlations derived from local sensor readings.

Segmented fins disrupt standing vortices near the igniter aperture, eliminating stagnation points that degrade heat shield durability under high thermal loads.

Ceramic matrix composite heat shield uses bulb-shaped interference fit to secure gas turbine combustor bulkhead without mechanical fasteners.

Segmented cooling flow paths isolate the coolant from the combustion stream, suppressing temperature rises while maintaining gas turbine efficiency.

A particulate oxide treatment creates an overlay layer that blocks vanadium oxide corrosion in gas turbine components, extending component lifespan.

A wavelet analysis system processes dynamic sensor signals to detect combustion anomalies in gas turbines.

A premixing apparatus combines swirl and non-swirl elements to mix fuel and oxidant before combustion.

Segmented tile holder design distributes cooling air evenly while accommodating thermal expansion without manufacturing complex bolt holes.

A ceramic combustor liner panel integrates uncooled and cooled portions to reduce cooling airflow demands in gas turbine engines.

An impingement cooled nozzle tip directs swirling cooling air through angled ports into a plenum, mitigating thermal stresses and coking on the center body.

An inclined surface angle of 16 to 24 degrees in a gas turbine diffuser reduces pressure loss while preventing stream separation and vortex generation.

Segmented outer support directs cooling air obliquely to aft-most panels, reducing operating temperatures and extending useful life.

A chamfered grommet assembly with internal cooling channels directs dilution air into combustion chambers.

Cracking devices decompose ammonia fuel into hydrogen, recovering waste heat to reduce carbon emissions and improve engine efficiency.

A rotating detonation combustor uses a variable radius outer wall to stabilize combustion waves.

Segmented cooling channels and damping volumes reduce cooling air mass flow, suppressing thermo-acoustic oscillations without increasing NOx emissions.

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

Catalytic reactor burns secondary gaseous fuel with inlet air to produce oxygen-rich gases, maintaining stable combustion where reduced pressure fails.

Upstream-projecting manifold walls obstruct circumferential flow, reducing pressure losses and improving combustion efficiency in turbomachines.

Straight cooling orifices in the combustion chamber flange direct bypass air to cool distributor platforms.

Passive recirculating bypass flowpath eliminates sump vessels and parasitic fuel loss for stable flame propagation.

Curved transition sections replace sharp notches to lower hoop stress concentrations, extending aft seal ring fatigue life.

A cooling unit injects water and fuel mixtures onto swirler vane pressure surfaces to enhance atomization.

A combustor liner warming passage directs pressurized airflow to heat the forward end.

Inclined pin fins maintain high cooling efficiency despite larger clearances, reducing manufacturing precision requirements and costs.

Tangential nozzle air jets atomize centrifuged fuel spray, resolving poor low power atomization and reducing emissions.

Relocating the damper chamber into the plenum resolves combustor space constraints while maintaining air flow and mass distribution.

A turbine combustion chamber uses a leaktight axial sliding shroud connection to maintain structural alignment.

Radial walls segment the nozzle housing into independent tubes, resolving thermal expansion stress while improving fuel-air mixing.

Alternating laser scanning with ammonia gas forms a hardened nitrided layer, resolving cracking and shrinkage issues in carbide sealing components.

Cooling rings with impingement and film holes direct cool air to lower transition piece surface temperatures while minimizing combustor pressure drop.

A cooling circuit uses hollow turbulators with internal conduits to redirect fluid flow and increase heat transfer surface area.

An impingement panel directs coolant jets toward a combustor liner exterior to reduce component temperature.

Radial deflection by protruding guide elements counteracts hot gas backflow, preventing nozzle head overheating while maintaining flame stability.

Angled fuel injection holes generate swirl flow to increase mixing area, reducing NOx production and downsizing burner size.

A torch ignitor system uses a pressurized oxygen-containing gas passage to deliver oxidizer directly into the combustion chamber.

Threaded nozzle rear end integrates fastening and sealing interfaces to enable rapid assembly without extra components.

An annular grommet directs cooling air through a chamber to form a protective film on the liner panel hot side.

Centrifugal particle separator prevents aperture blockage by sand and ash, ensuring consistent cooling performance in additive manufactured combustion chambers.

A thimble assembly directs fluid flow through a combustor liner to introduce cross-flow into the secondary combustion zone.

Ridge slots direct pressurized cooling air to cool the heat shield exterior, reducing coolant usage and lowering combustion emissions.

A triple swirl gas turbine combustor uses concentric air feeding swirlers to generate a vortex in compressed air for enhanced fuel-air mixing.

Dummy manifold segments plug adjacent nozzle ports, eliminating specialized terminal nozzles and reducing manufacturing complexity.

Segmented struts with insertion grooves reduce thermal stress and enable easy replacement in gas turbine transition pieces.

Segmented ceramic matrix composite dome tiles shield metallic supports, resolving thermal stress from coefficient mismatch.

Modified quarter wave damper uses side cavities and purging fluid to initiate vortical flows for acoustic power absorption.