Continuous Combustion Chamber TRIZ Cases

Adjusting engine fuel flow between pilot-plus-mains and pilot-only modes to modify contrail optical depth.

Angled lateral walls on resonators direct film cooling across intervening strips and weld seams, preventing thermal stress from uneven heat distribution.

Segmented channels deliver a fuel-rich upstream mixture that resists detonation, then add oxidizer at the combustion zone to achieve complete reaction.

Annular combustion chamber sustains detonation waves via sequential electrode pulses, simplifying initiation and improving thermal efficiency.

Selective resonators absorb acoustic energy from gas turbine combustor cans to suppress pressure oscillations.

Variable through-hole density in the weld part cools hot zones while restricting excess compressed air inflow, eliminating separate cooling jackets.

Fuel injector nozzle assembly prevents hydrogen flashback by removing swirl vanes and using a float swirler for stable combustion.

A combustor skin assembly uses a sliding flange engagement to accommodate thermal growth between hot and cold skins.

Alternating orifice diameters in a single annular row optimize airflow for varying speeds, reducing component count and emissions.

A turbomachine fuel injector annular collar uses surface pegs to disturb cooling air flow and expand the heat exchange area.

Segmented torch igniter allows glow plug replacement without opening the combustion chamber, reducing stress on the pressure vessel.

Multiple radially extending orifices distribute fuel flow across the flange, maintaining even preload and reducing leakage around the seal.

A floating primary swirler moves radially with the fuel nozzle to maintain uniform fuel-air mixing in gas turbine combustors.

Coupling sheet metal cowls to the dome assembly ring eliminates welding or brazing, reducing material waste and manufacturing costs for gas turbine engines.

A flameless burner uses a primary swirl chamber to generate a recirculation zone that entrains hot combustion gases for stable fuel injection.

Segmented fuel channels create low-speed zones that prevent flashback while reducing NOx emissions.

Structural asymmetries in burner mains reduce coherent thermo-acoustic oscillations, lowering pressure levels and mechanical stress on combustor hardware.

Extraction of the dome plate decouples high-stress regions, reducing vibratory loads on cowls to extend engine component lifespan.

Continuously curved sealing surfaces allow axial nozzle removal, eliminating seal damage and leakage risks during maintenance.

A fuel nozzle assembly uses a turning guide with separators to distribute air flow uniformly through the combustion chamber.

Nested conduits shield fuel lines from damage during maintenance, preventing leaks and ensuring reliable operation.

Segmented downstream fuel injection stages control reactant residence time at high temperatures, reducing NOx emissions while maintaining engine efficiency.

Air extraction ports contract cooling airflow through geometric ratios to maintain uniform pressure fields in gas turbine combustors.

Modular diffuser case sections allow targeted maintenance without full combustor disassembly, reducing operational downtime.

Cooling air flows through axial bores in the downstream end plate to reduce temperature gradients, extending component life under high thermal stress.

Asymmetric aperture geometry breaks consistent vortices from circular holes, dispersing particulates to prevent blockages and maintain cooling efficiency.

Angled fuel injectors generate tangential flow vectors that reduce circumferential temperature non-uniformity and improve light-around reliability.

Segmented fuel spray nozzles supply heated fuel to specific subsets, lowering viscosity to balance combustion efficiency against coking levels.

Self-supporting inner cap structures eliminate additive manufacturing supports while Helmholtz resonance dampens combustion instability.

Axially separated main orifice rings with independent galleries enable variable flowrates, reducing engine pump pressure and improving NOx emissions management.

A fuel injection system uses a pre-stressed spring to constrain axial movement of the sliding cross-member.

A turbomachine combustor head end assembly directs compressed air radially inward through tubular bodies to mix with fuel.

Radial steps on segmented guide vane platforms channel cooling air along surfaces to prevent hot gas mixing and maintain thermal protection.

Segmented lattice gasket isolates impingement and film holes, maintaining pressure balance despite liner panel breaches.

V-shaped passage walls in the metering section counteract kidney vortices to reduce flow separation at high blowing ratios.

A dilution gas admixer mixes cooling air with first combustor exhaust to condition the inlet for a second combustion stage.

Sandwiching a polymer char between a monolithic insert and a ceramic matrix composite prevents fiber exposure during machining.

Integrating mixing tubes into the shroud wall reduces thermal strains from uneven expansion while maintaining structural integrity.

Integrating liquid fuel delivery into the centerbody wall eliminates separate cartridges, reducing component count while maintaining low NOx emissions.

A ring assembly spaces and supports inner ceramic matrix composite and outer metal skins using projecting portions.

Integrating fuel channels into the combustion liner wall eliminates external manifolds that disrupt cooling airflow, improving surface cooling efficiency.

Sectoral direction-changing blocks guide reverse secondary waves into arc channels to align with the primary detonation wave.

A turbine combustor injects fluid during high power operation to control flame temperatures.

Diffusion bonding creates a strong metallurgical joint between the spoke and manifold, eliminating stress cracking and leakage without obstructing fluid flow.

A SiO2 barrier layer disperses reactive particles to seal microcracks in ceramic substrates.

Segmented end cap tube bundles inject inert diluent to form barriers that decouple flame interaction and suppress combustion dynamics.

Broaching creates protruding aperture profiles that strengthen ring bonding against thermal fatigue.

Impingement box directs compressed air over upstream welds to resolve diminished cooling effectiveness caused by increased resonator height.