Continuous Combustion Chamber TRIZ Cases

A ceramic panel assembly uses a slot and insert configuration to provide secure fastening elements.

A pressure-balanced fuel valve equalizes chamber pressures to reduce actuator force requirements.

Radial segments on the nozzle tip create localized recirculation zones that enhance flame holding and reduce NOx emissions without increasing pressure loss.

Nested inner and outer tubes maintain fluid isolation between fuel streams while a spring section accommodates thermal expansion in gas turbine combustors.

A guide ring directs fuel gas to stabilize ignition, reducing pressure loss in the afterburner.

An inward-firing premix burner uses a composite semi-cone substrate to direct fuel-air ignition toward the center, reducing thermal stress on chamber walls.

Impingement cooling rings direct air through bulkhead holes to cool heat shield panels, reducing dead spots and debris accumulation.

Through-holes in a combustor sound attenuator cool fuel to prevent incomplete burning, reducing carbon monoxide emissions.

Tubular combustion chambers arranged around the rotor enable sequential fuel injection for controlled gas turbine operation.

Integrating the fuel manifold into the combustor dome reduces device complexity while maintaining large nozzle sizes for improved combustion efficiency.

Isolation gas separates nitrogen from diffusion flames, reducing thermal NOx while maintaining stability.

A tapered outer ring eliminates stagnation regions at the downstream end, preventing flow separation and suppressing flashback in gas turbine combustors.

Segmented corrugated positioning stabilizes the CMC liner against thermal expansion while cooling air reduces conductivity.

A combustion assembly closure device adjusts air intake orifices based on thermal expansion states.

Segmented combustor panels overlap to form a circumferential air gap, preventing hot air egress and enhancing thermal reliability.

Compliant mounting features allow relative movement between ceramic matrix composite ducts and metal structures.

Multi-layer environmental barrier coatings on ceramic matrix composite endfaces prevent recession without purge flow, maintaining turbine efficiency.

A conical deflector plate maintains a constant gap from the combustion chamber bottom to ensure uniform cooling air flow distribution.

Scoop ring bores form jet nozzles that enhance air penetration and static pressure drop despite low local pressure from high velocity outer annulus flow.

Segmented tubular locking elements secure shingles while enabling effusion cooling holes, eliminating thermal bottlenecks from conventional screw attachments.

YAG infiltration seals porous ceramic surfaces, preventing corrosion and extending service life.

Integrates rigid polyurethane foam cores with epoxy-impregnated carbon fiber skins to resolve weak junctions in traditional metal-composite manufacturing.

A center body assembly segments fuel into pilot and main circuits to minimize smoke generation during light off.

Automated extraction valve adjusts oxygen flow to stabilize flame front position in gas turbine combustors.

A single integrated diffuser reduces cumulative flow deflection angles, cutting component count and weight while minimizing energy losses.

A lean burn combustor uses an S-shaped recirculation zone to anchor the flame and support stable combustion of pilot and main fuel mixtures.

A non-linear channel between combustor panel endrails obstructs direct line-of-sight to the combustion chamber.

An active cooling system siphons air through a heat exchanger to protect fuel injectors from high temperatures.

Segmented inner diffuser case struts meter secondary flow air to balance axial thrust loads on bearing structures while maintaining cooling efficiency.

Passive flow dividers equalize fuel distribution to reduce flame temperature variations, eliminating complex electronic control systems.

Heat shield rib constrains axial movement to prevent thermal degradation of the combustor vane support lock.

Circumferentially aligned film cooling regions mitigate thermal stress from stator vane bow waves while minimizing structural complexity.

Bluff body fuel injectors generate turbulent recirculation zones that stabilize flame and improve lean blowout performance in gas turbine engines.

Piezoelectric actuators vary fuel flow rates per injector to resolve non-uniform combustor exit temperatures, extending turbine component life.

Quarter-wave tubes in the air plenum dampen specific frequency oscillations, reducing vibration and stabilizing combustion.

A multi-layer adhesive system bonds metal substrates to ceramic matrix composite components using bond and alumina coatings.

Porous outer nozzle walls reduce pressure losses and enthalpy waste from unburned propellant, enhancing combustion efficiency.

Hot surface igniter heats premixed air and fuel in an insulated chamber to initiate combustion, solving high pressure ignition reliability.

Segmented combustor liner inner wall members slide within a support guide structure to enable free insertion and extraction.

Merging the guide vane and combustor body reduces axial length and manufacturing complexity while improving fuel-air mixing efficiency.

Segmented flow sleeve maintains compressed air pressure for mixing and cooling, reducing pressure drops in gas turbine engines.

Segmented effusion cooling holes with varying tangential angles maintain effective film coverage across major orifices, reducing complexity and cost.

Tuned injector resonators damp acoustic pressure fluctuations, eliminating combustion chamber wall modifications and reducing manufacturing complexity.

Segmenting the cooling circuit into prioritized and restricted flow regions reduces thermal gradients by directing more cooling flow to high-heat areas.

Segmented ring and nut fastening enables secure attachment within flame-holder arms without disturbing primary flow.

Multi-lobed cooling holes reduce flow requirements by distributing fluid via electrical discharge machining.

Radial ribs and effusion holes accelerate cooling air flow to achieve isothermal temperatures on combustor bulkheads exposed to extreme heat.

Angled impingement ribs direct cooling airflow through holes to enhance heat transfer, resolving inaccessibility of internal component surfaces.

Axially offset mixer assemblies distribute fuel across multiple planes, reducing hot flame streaks and emissions during high-power operation.