Continuous Combustion Chamber TRIZ Cases

A fuel injector heat shield incorporates a drip guard to intercept falling fuel droplets before they reach the sliding expansion joint.

Merging separate cooling mechanisms into one liner reduces structural complexity while maintaining high temperature durability.

Simultaneous gaseous and liquid fuel flow enables reliable turbomachine ignition without pre-established flames.

L-shaped seal assembly with side plate enhances cross-sectional stiffness, preventing deformation from self-excited vibrations in gas turbines.

Axial stop parts constrain combustion chamber movement within the outer housing to maintain precise positioning.

A premixed direct injection nozzle uses coolant film cooling along its converging walls to manage thermal loads in combustion systems.

Asymmetric annular land accommodates thermal expansion while directing cooling air to quench apertures, reducing thermal stresses.

Replacing metallic welding with a ceramic resonator eliminates complex cooling channels and reduces fuel consumption.

Radial inlet slots and bent tubes increase tube count to resolve aft plate cooling challenges and non-uniform fuel distribution.

Radially offset fuel injection bores in separate dome walls enable independent pilot and main stage control, resolving temperature profile trade-offs.

Relocating the fuel manifold ring radially inward within the combustion case reduces engine diameter and weight while eliminating elastomeric seal leak risks.

Inner and outer joint grooves in the annular CMC interface accommodate differential thermal expansion between ceramic and metal skins, reducing thermal stress.

Friction-grip bolt system secures brittle CMC liners to bulkheads without threading, preventing cracking during thermal expansion.

Symmetric detonation manifold orifices adjust fluid velocity and pressure to maintain combustion efficiency across varying thermal loads.

Ceramic tiles shield metal fasteners from combustion heat, eliminating cooling needs and extending component lifespan in gas turbines.

Axial fuel stage immersed injectors reuse cooling air for secondary combustion, recovering energy lost in conventional turbine systems.

A gas-only cartridge mixes compressed air with gaseous fuel to enhance flame stability.

Segmenting the head end assembly into independent modules reduces nitrogen oxide emissions by half while simplifying construction complexity.

A burner with a rectangular inlet and round mixing section creates secondary vortices to enhance fuel-air distribution.

Segmented mixing tube outlets with asymmetric outward projections disrupt recirculation zones to reduce flame holding and screech tone vibrations.

Varying the cooling air channel cross-section increases velocity and pressure recovery, reducing differential pressure stress on the inner duct.

Longitudinally asymmetric cooling holes in an impingement sleeve optimize local thermal loads while minimizing pressure drops across the transition duct.

Throttle ring stabilizes film cooling layer to improve liner durability without increasing cooling air consumption.

Embedded 3D ceramic fiber fabric bridges cracks in monolithic blocks, eliminating protective coatings and reducing oxidation damage.

A combustor thermal shield uses a gradient material transition region between ceramic panels and metal studs to resolve structural integrity issues.

Offset filtering apertures draw fuel from a debris-reduced layer, preventing rust and debris blockages in carbon steel manifolds.

Fuel injector nozzle uses circumferential vanes to define inlet flow paths for fuel discharge and air mixing.

Segmented support ring with anti-rotation tabs restricts stator rotation while maintaining structural strength for effective cooling.

Arranging inlet holes at an acute angle reduces pressure loss from turbulent collision while maintaining effective cooling for higher combustion temperatures.

An apatite structured rare earth coating prevents volatile silicon species formation to reduce substrate recession in gas turbine engines.

Resilient mounting assembly accommodates differential thermal expansion between ceramic matrix composite liner and metal dome, maintaining airtight seal.

Asymmetric oblong shrouds generate targeted turbulence to resolve inadequate air-fuel mixing in annular combustors, improving emission balance.

Outer wall apertures target tile lips while upstream fasteners and downstream slots isolate heat paths, reducing stress in the annular structure.

Segmented pin fins resolve wax mold removal difficulty by using flat-topped second fins alongside rounded-top first fins for efficient heat dissipation.

Segmented bristles in a combustor heat shield absorb thermal cycling stresses to prevent cracking and coating spallation.

Varying injector tube lengths and contoured forward walls adjust convection time to mitigate combustion dynamics without adding complex damping mechanisms.

Angled cooling air holes and guide ring direct airflow for impingement cooling of the crossfire tube assembly.

A gas generator uses an inner tube with through holes to transfer a burning transfer charge, shortening discharge time and inflation start time.

A segmented combustor cap retention system uses a spring plate to secure components without permanent welding.

Phase-matched supports and cross fire tubes accelerate flame propagation, resolving thermal shock and NOx emission trade-offs during ignition.

Segmented nozzle outlets orient pilot and primary streams separately to enhance mixing stability, reducing carbon monoxide emissions in gas turbine engines.

Oblique side walls in the annular sector outlet prevent intermediate area expansion, suppressing flow separation and reducing pressure loss.

A fuel injector uses converging air paths and adjustable swirlers to enhance atomization across engine power levels.

Tangential coolant apertures in a combustion chamber seal align with swirling fuel-air mixtures to reduce smoke emissions.

Segmented stand-off devices maintain spacing between CMC and metallic combustor skins to accommodate thermal expansion differences without direct contact.

Segmented U-shaped passages invert airflow to deliver targeted cooling, reducing NOx emissions while maintaining high combustion efficiency.

Integral CMC attachment features eliminate metal fasteners, preserving structural integrity at high operating temperatures.

Segmented combustor inner skin uses pin fins upstream and effusion holes downstream to manage cooling air distribution.