Continuous Combustion Chamber TRIZ Cases

Oriented effusion holes downstream of dilution holes stabilize the cooling film against disruptive vortical structures, reducing panel temperatures.

Helical fluid passages in a gas turbine pre-mixer create swirling motion that improves fuel-air mixing completeness while reducing device length.

Tilted cooling ducts generate a sealing film on the vane platform, reducing hot gas leakage and air consumption.

A detachable swirler unit connects the swirler and heat shield for easy removal through a holding aperture.

Combustor inserts guide pressurized air jets through dual wall liners to reduce NOx emissions while managing high temperature operability.

Metal bonding flanges act as intermediaries between CMC parts, accommodating thermal growth mismatch while ensuring reliable attachment.

Central pilot and annular fuel injectors create a separating air film between combustion zones to control mixture richness.

Overlapping frictionally engaged members dissipate vibrational energy to mitigate high and low cycle fatigue in gas turbine fuel injectors.

Curved leaf spring bridges dampen upstream vibrations while rigid downstream flanges maintain structural stability against thermal expansion.

Pre-assembled LLI modules with serpentine conduits reduce assembly complexity and thermal stress in gas turbine combustors.

Rotatable arms on a base body adapt to diverse burner orientations, eliminating complex installation procedures and reducing assembly time.

Varying fuel channel cross sections in mixed nozzle types adjusts individual flow rates to minimize soot emissions and thermoacoustic oscillations.

Strategic air admittance hole placement mitigates thermal maldistribution and hot spots in gas turbine combustors.

Asymmetric inclined perforations replace deflectors to cool the chamber end wall, halving cooling airflow while maintaining uniform temperature.

Segmented radial injectors distribute liquid fuel across large diameter nozzles, resolving coverage gaps that cause inefficient combustion and high emissions.

Oblique primary fuel discharge from a turbine nozzle tip creates swirling flow to enhance steam mixing.

Coaxial fuel injector uses vane arrays to impart swirl and create distinct combustion zones.

Secondary compressors and combustor modules reheat extracted air to offset performance losses from cooling air withdrawal.

Segmented impingement and pedestal cooling zones reduce pressure drop and extend component lifetime.

Bolted base plate attachment replaces welding to resolve maintainability issues in gas turbine combustors.

Sector nozzle assembly uses longitudinal struts to stabilize the shell against mechanical loads.

An internal stem assembly transfers pressure loads directly to the casing wall through a sealing element.

Merges anti-rotation features with removal threads in combustor liners, eliminating separate puller grooves that increase weight.

Segmented CMC heat shield eliminates cooling fluid requirements, reducing turbine emissions and simplifying assembly.

A fuel injection assembly integrates heat exchangers within a high-pressure casing to preheat fuel for combustion.

Primary inlet positioned upstream of obstacles pre-establishes airflow, while secondary inlets prevent flow reversal to sustain the cooling film.

Segmented insertion holes enable straight combustor removal while preserving casing strength.

A fuel injector nozzle assembly uses a core swirl plug to modify flow velocity and act as a heat sink for the fuel.

Transient liquid phase bonding joins dissimilar heat shield and shell materials, reducing gas leakage caused by thermal warping in turbine engines.

Split retaining rings and clamping means immobilize injection system collars, preventing axial movement and reducing vibratory wear on fuel injector nozzles.

Radial supply port extender directs high temperature air away from the first cooling passage inlet to maintain effective fluid introduction.

Tapered retaining elements interface with recessions to resist guide plate rotation, improving air sealing and reducing wear in gas turbine engines.

Ionizing the mixture with a plasma generator stabilizes lean flames at high velocities, reducing NOx emissions and unburnt fuel.

Integrated heat shield cooling channels manage thermal loads on multi-functional fuel nozzles, preventing overheating and erosion in combustion turbines.

Core and offshoot passages within a combustor panel attachment feature channel cooling air from the diffuser chamber, reducing hotspots near structural joints.

Angled ejection slots in a dual-wall combustor tile assembly direct cooling air to mitigate hot spots and improve thermal efficiency.

A film cooling circuit uses a substrate channel and coating aperture to direct cooling air flow.

Late lean fuel injection nozzles at the transition duct aft end adjust the combustor exit temperature profile.

A fuel sweep system directs leaked fuel through louvers into a combustion chamber passage.

Internal ribs expand fluid path surface area within cooling holes, boosting in-hole heat convection and reducing reliance on film cooling.

Apertures in the transition piece direct compressor discharge air into the interior space, reducing heat transfer to withstand temperatures exceeding 800°C.

Surface ribs on a gas turbine fuel nozzle disturb flow to promote uniform mixing, suppressing local flame temperature peaks and reducing NOx emissions.

A floating collar seal assembly uses a spring retention member to maintain radial distance from the injector.

A cooling system uses opposite swirl flow paths to generate counter vortices that neutralize natural vortex formation.

Circularity recesses on a gas turbine combustor liner accelerate cooling air flow to enhance heat transfer.

Segmented flexible sealing rings accommodate thermal expansion at the turbine nozzle and combustor liner interface, reducing unpredictable leaks.

Zirconia-dispersed silicate coatings prevent delamination by matching substrate thermal expansion while resisting steam erosion.

A venturi structure restricts and diffuses airflow within a gas turbine combustor passage to stabilize the flow field.

Extracting fuel lines to the combustor exterior via thermal isolation prevents ignition risks while simplifying assembly and maintenance.

Automated fuel split adjustment modulates combustion distribution based on real-time Modified Wobbe Index measurements.