Continuous Combustion Chamber TRIZ Cases

Non-uniform effusion aperture density in a turbine combustor wall tailors cooling air distribution, reducing temperature differentials and material fatigue.

Sliding covers adjust cooling air openings in a combustor liner, resolving thin-wall manufacturing limits for precise temperature control.

Segmented pilot and mains manifolds with series isolation valves prevent unintended fuel flow, reducing hot streak risks from valve failures.

Staggered V-pattern air admission holes direct quench jets to mix fuel-rich gases with excess air, reducing residence times and thermal NOx formation.

Segmented diffuser case assembly with sliding joints accommodates thermal expansion, reducing stress concentrations during transient operations.

An auxiliary elastic support absorbs thermal expansion stress to prevent friction damage and extend component lifetime.

Segmented admixing air holes with specific diameter ratios ensure uniform fuel-air mixing, reducing NOx emissions from incomplete combustion.

A double-jet film cooling structure injects cooling medium through inclined branch passages to generate counter-rotating swirl flows.

Segmented passages and slots in a gas turbine component manage thermal stress by delivering film cooling air, resolving complexity trade-offs.

An annular Helmholtz damper utilizes concentric hollow shapes and multiple necks to damp pressure oscillations in gas turbine systems.

A brazing process diffuses non-metallic constituents away from the braze layer centerline to create a eutectic-free region.

A suspended bracket with a rotatable joint positions heavy combustors for installation.

A segmented acoustic liner maintains circumferential integrity while enabling damper communication through a dedicated opening.

Differentiated fuel flow control compensates for localized air extraction, eliminating hot spots and protecting high-pressure distributors.

Injector assembly generates shielding air flow to delay reactant ignition, reducing flame temperature and NOx emissions while lowering cooling air consumption.

Segmented fuel manifold and valve system dynamically adjusts injector supply to disrupt acoustic oscillation propagation in gas turbine engines.

Impingement purge ejects cooling fluid from dedicated cavities to reduce structural wear while maintaining high-energy combustion efficiency.

A combustor control method adjusts the pilot fuel split to stabilize combustion during gas turbine transients.

An angled liner panel mounted via studs eliminates interface steps that cause adverse aerodynamics and reduces dead regions for better durability.

Variable radius scoops on a flow sleeve collect compressed cooling air, compensating for upstream pressure loss to cool the upper transition piece.

Radial fixation with cooling pressure differentials accommodates thermal growth in CMC combustor liners, eliminating metal fastener melting risks.

A regenerative micro-turbine preheats compressor air via exhaust heat recovery, reducing fuel consumption while maintaining thrust output.

Sealed chambers inside thermoinsulating tiles hold liquid marker substances that flow out to reveal surface cracks, replacing time-consuming visual inspections.

A pressing support mechanism decouples axial force from bolt connections in rotary machine casings.

Obliquely angled elongated apertures in auxetic structures reduce stress concentration around cooling holes while maintaining high thermal effectiveness.

Channels formed in a spacer between fixing flanges cool turbomachine walls obstructed by traditional multiperforations.

Aerodynamic deflectors extend radially from the downstream wall to limit pressure loss in turbomachine injection systems.

A premixing tube with an inner diameter enlarging portion guides swirl flow to set the flame lift distance in gas turbine combustors.

Segmented fuel injection zones prevent liner wetting and coking while staged combustion maintains high thermodynamic efficiency.

Spiral trip strips on a baffle insert create vortices that enhance convective cooling, reducing thermal loads and extending airfoil service life.

Vortex modification system disrupts flow vortices in turbomachine combustors, mitigating high-frequency noise while preserving heat transfer efficiency.

Movable pistons adjust cavity volume to tune damping frequencies, eliminating shutdown requirements and reducing NOx emissions from unnecessary purge air.

Segmenting the diffuser flow prevents local pressure drops while directing cooled air to turbine vanes for effective heat management.

Dual swirlers dynamically adjust recirculation zones to stabilize the flame and maintain low NOx emissions across varying gas turbine loads.

Non-intersecting effusion holes on adjacent combustor panels reduce hot spot stress while preserving emissions integrity.

Preheating the distal flame holder with a pilot flame maintains combustion stability and reduces NOX production during state transitions.

Pneumatic starter expels oxygen-rich gas to power turbine rotation and supply oxidant.

Segmented mounting brackets resolve restricted access in compact gas turbines by enabling independent installation and removal of combustion modules.

Helmholtz resonating dampers integrate into combustor liner throats to absorb acoustic energy through viscous dissipation.

Cooling insert recovers spent air via discarding and recovering principle, boosting turbine efficiency while maintaining component durability.

A pre-nozzle mixing cap assembly uses fuel tubes with holes to mix air and fuel upstream of nozzles.

Segmented injection nozzles apply localized fuel rates to suppress thermoacoustic pulsations without increasing NOx emissions.

Reposition fuel injectors in gas turbine combustors to balance circumferential temperatures.

A porous ceramic insert joins a silicon carbide matrix composite through co-infiltration, preventing fiber exposure during machining.

Bent multi-perforation holes in an annular combustion chamber wall utilize total air pressure to reduce crack risk downstream from primary and dilution holes.

Angled neck damper mitigates grazing flow interference, enabling placement in high velocity regions while maintaining acoustic damping efficiency.

A fuel control device adjusts flow ratios in humid air turbines using coaxial jets and staged supply to maintain combustion stability.

A metallic grommet with collars attaches ceramic matrix composite liners to turbine domes.

Embedded micro-cooling channels in the combustor aft frame transfer thermal energy via compressed air, reducing igniter housing deterioration.