Continuous Combustion Chamber TRIZ Cases

A fuel delivery system uses a moveable attachment assembly with a bellows to accommodate thermal expansion of the fuel tube along the combustor axis.

Nested steam passage in sidewall reduces flame temperature and nitric oxide production.

Segmented holes in the seal prevent flow blockages while maintaining sealing integrity against thermal growth and misalignment.

Segmented injectors and plenums create phase-opposed mass flow fluctuations that cancel acoustic oscillations, stabilizing temperature and pressure conditions.

Offset angled liner panels maintain consistent rail thickness to accommodate thermal expansion while preserving uniform cooling air flow.

Lobed diffuser sections in airfoil cooling holes enhance lateral film spreading for gas turbine protection.

Merging nozzle airfoils with combustion liners eliminates flow path steps and purge flows while reducing assembly weight.

Centrifugal flow stabilizes combustion at high aeration, reducing NOx emissions and preventing flame-out.

Segmented impingement holes and divider walls reduce temperature gradients in a gas turbine heat shield while minimizing cooling air consumption.

Nested radial holder rings with comb-shaped ends secure the annular combustion chamber, reducing hairpin breakage from dynamic excitation.

Annular combustion chamber uses radial sealing strips to bear against turbine distributor rims for reliable gas containment.

A liner cap integrates cavities and an impingement plate to absorb acoustic vibrations within a gas turbine combustor.

A fuel nozzle assembly uses a swirler and air injection feature to mix secondary fuel upstream of combustion.

Segmented auxiliary support prevents downstream vortex formation and combustion gas stagnation by guiding airflow from the liner to the transition piece.

A turbine combustor recirculates exhaust gas to cool the liner while extracting a separate flow for energy recovery.

A gas turbine combustor uses a flow sleeve with internal diameter changes to cool the liner.

A turbine engine particle separator uses centrifugal and electrostatic forces to divide air flow into distinct streams within the diffuser.

Parallel driving cylinders connect via a connecting member and a fitting member that constrains axial movement, reducing distal end error displacement.

A fuel injector manifold trim device adjusts flow between the manifold channel and nozzle inlet to ensure consistent fuel delivery.

Segmented liner panels with discontinuous rails guide impingement and film cooling air to reduce thermal stress at panel interfaces.

A main air collection chamber captures upstream gas and injects it through openings to form a parietal cooling film along the annular casing.

A pin and bushing mounting assembly secures ceramic matrix composite heat shields within a turbine engine combustor slot.

Segmented late lean injectors spray cleaning mixtures onto compressor stages to remove contaminants while preventing residual water corrosion.

Tubular cooling duct extension increases heat transfer surface area on gas turbine combustion chamber walls without adding significant wall weight.

Segmented reverse flow combustors reduce axial length while maintaining high pressure ratios without thermal damage.

A fuel divider valve uses a movable member and spring counter force to adjust pilot and main port openings based on fuel pressure thresholds.

Effusion holes and fins direct cooling air through the heat shield to reduce coolant usage while maintaining combustion efficiency.

Intermediate rail and heat transfer augmentors create convergent passages that resolve sealing effectiveness trade-offs against manufacturing ease.

A tubular particulate mitigation device extends from a gas turbine heat shield to direct cooling airflow above the boundary layer.

A combustor base plate defines a purging air space and flow passage to inject cooling gas into the burner case.

Segmented fuel injection pegs offset concentration fluctuations to suppress combustion oscillation, reducing flashback risk while maintaining low NOx emissions.

Segmented polyphase motor windings maintain fuel supply reliability despite electrical faults, reducing weight and complexity.

Segmented oxidation and SCR catalysts maintain emissions compliance during low load operation.

Downstream fuel outlets and constant area passages maintain high velocity to reduce NOx emissions without diluents.

Axial zoning with richer upstream mixtures stabilizes part-load combustion while lean downstream zones minimize NOx emissions.

Active valves segment the fuel manifold into independent zones, suppressing thermoacoustic instabilities during transient deceleration.

A flexible spring seal assembly maintains sealing contact between turbine components through elastic deformation.

Radial tube elements distribute fuel to stabilize combustion and reduce NOx emissions in turbomachines.

Porous heat shield floatwall panels mitigate local hot spot cracking by reducing maximum stress range, improving durability without complex fabrication.

Upstream edge cooling purges combustion gases from T-junction gaps, reducing metal temperatures by 65 C.

Segmentation and intermediary principles enable acoustic coupling without modifying thermoinsulating tiles, preserving mechanical strength.

Segmented disk stacks eliminate complex couplers to reduce turbulence and construction costs in boundary layer turbines.

A bridging member connects inner and outer wall structures in a turboengine vane carrier unit to maintain precise guide vane alignment.

An asymmetric triangular-section diffusion portion shifts cooling air away from counter-rotating vortices, reducing hot gas ingestion and boosting efficiency.

Modular planks and clips on a combustor liner mesh structure minimize air leakage and hoop stress.

Open-cell metallic foam within pilot injectors stabilizes hydrogen combustion, preventing lean blow-out and controlling NOx emissions.

Concave annular grooves on the radially inner wall expand the duct area, compensating for flow guide element profiles that obstruct air supply.

A segmented double-wall structure channels cooling air through a hollow space to discharge at optimal angles across gas turbine platform surfaces.