Continuous Combustion Chamber TRIZ Cases

A fuel manifold adapter decouples engine components via a sliding transfer tube assembly.

Segmented combustion chamber assemblies use pivoting hooks within slots to manage thermal expansion stress while maintaining radial restraint.

Segmented structural members prevent modal crossing and panel bulging in compact heat exchanger pedestals under thermal loads.

Axially extending cooling air channels with single inlets and outlets improve distribution reliability in gas turbine transition ducts.

Actuating a translatable converging-diverging liner section changes the primary combustion zone volume, reducing NOx emissions and improving fuel efficiency.

A swirl dilution air injector introduces rotational flow into a gas turbine combustor to accelerate mixing with hot combustion products.

A gas turbine uses premixed ammonia and cooling air to uniformly cool stator vanes and rotor blades.

A leakage gas emission system directs fuel gas through a pipe to an outside unit using pressure differentials.

A flow distribution member with curved guide surfaces and multiple channels directs air into outer nozzles to ensure uniform fuel-air mixing.

Composite nickel alloy supports with ceramic coatings prevent oxidation and creep, extending service life in gas turbine combustion chambers.

Segmenting the combustion zone into pilot and main chambers stabilizes the shockwave to increase fuel delivery volume.

Curved rail guidance aligns heavy liners for safe installation, eliminating manual lifting risks and reducing maintenance downtime.

Varying oxidant port configurations shift combustion dynamics frequencies away from resonant points to reduce modal coupling and vibratory responses.

Segmented cooling passages apply tailored heat removal to distinct combustion zones, preventing exhaust overcooling and preserving engine efficiency.

Segmented flow sleeve assembly accommodates thermal expansion differences between casings, reducing damage risk during operational transients.

Pre-sintered braze foil secured to a tube eliminates manual paste variances and re-work in tube-to-plate assemblies.

An inclined flow path reduces radiant heat transfer from the combustion chamber, preventing spontaneous ignition while maintaining high mixing efficiency.

Undulating profiling on angled plates prevents block detachment by increasing bending resistance without adding material thickness.

A converging-diverging combustor liner design with throat dilution openings enhances gas quenching efficiency.

A combustion cylinder cooling part adjusts medium flow rates based on connection angles to manage heat transfer across the combustor basket.

Turbulators define tortuous cooling paths along rail-less edges to enhance heat transfer, minimizing air leakage and energy loss at critical boundaries.

Geometric surface features on a combustor wall paired with an oxidation-resistant metallic coating maintain thermal transfer while preventing burn-through.

A swirl preburner system generates swirling flows to mix fuel and oxidizer efficiently within combustion chambers.

Mechanical fasteners secure CMC heat shields without machining threads, preventing fractures while improving thermal durability.

A cooling hole with a diffuser portion expands air to reduce momentum and improve film coverage.

Injects steam generated from combustor waste heat into the core air flow path, increasing mass flow and thermal efficiency while managing device complexity.

Segmented spring device allows pre-assembled installation and easy removal of heat shield elements, resolving accessibility issues during maintenance.

Inner wall air channels eliminate outer surface vortexes that cause backfire, ensuring stable combustion.

A cooling circuit forms on a combustor liner wall to reduce distress from air jets in cross-flow.

Trailing-edge vortex generators on lobed fingers prevent flow separation and reduce NOx emissions by accelerating fuel-air mixing.

Internal grommet cooling prevents localized hot spots and oxidation damage at dilution holes, preserving combustor liner integrity.

Integrated extraction interfaces enable cold installation of the tube, eliminating welded joints and reducing maintenance complexity.

Angled impingement cooling apertures direct high-momentum air to prevent stagnation and particulate accumulation on gas turbine components.

A radial acoustic damper creates resonance space within a combustor cylinder, reducing casing volume and simplifying maintenance.

Nested damping volumes target specific acoustic frequencies to resolve the trade-off between broadband oscillation control and structural complexity.

A fiber preform coating method uses solvent vapor pressure differences to form a uniform porous surface layer.

Chevron-shaped ribs generate opposing vortex pairs within cooling passages, preventing flow separation and liftoff while maintaining engine efficiency.

Internal mounting reduces pressure differentials, allowing thinner walls that contain ruptures while protecting temperature-sensitive components.

Screening plates in staged injectors improve fuel-air mixing uniformity while reducing NOx emissions and minimizing aerodynamic pressure losses.

Segmented pilot burner with up to 30% oxygen concentration maintains flame stability while reducing NOx emissions in the main combustor zone.

A combustor cap assembly recirculates cooling air through an impingement plenum for premixing with fuel.

Offset mount flanges and attachment posts enable relative movement between ceramic matrix composite heat shields and combustor shells.

A premixed pilot nozzle directs fuel and air axially to stabilize combustion at low equivalence ratios.

Segmented combustion regions in a two-shaft gas turbine reduce switching frequency during rapid load changes.

Axially spaced rows of bias effusion holes redistribute cooling air to reduce temperature gradients and enhance structural integrity.

A tangential transition nozzle directs combustion gases into a gas turbine engine, eliminating first-stage vanes and reducing cooling system complexity.

Segmenting a thermal barrier coating with intersecting slots prevents molten CMAS infiltration, maintaining strain tolerance and delaying spallation.

Segmented hollow planks on a mesh skeleton reduce hoop stress and enable modular replacement of damaged combustor liner sections.

A fuel swirl nozzle uses a dolioform swirler profile and blended joints to enhance air-fuel mixing.

Variable protuberance density on the heat shield directs cooling air to hot spots, reducing pressure drop and improving combustion efficiency.