Continuous Combustion Chamber TRIZ Cases

Compound chevron film cooling holes diverge laterally to diffuse cooling air, preventing flow separation and improving wall coverage.

A cavity coupled fuel injector mixes fuel with air in an expanded chamber to improve atomization quality.

Segmented retention ring secures annular heat shield to support lock, preventing axial liberation during thermal growth.

A hydrogen-exhaust gas heat exchanger transfers thermal energy from turbofan exhaust to cryogenic fuel.

Interconnected Helmholtz volumes damp broadband pressure oscillations, resolving narrow bandwidth limits in gas turbine combustion chambers.

Additive manufactured injector assemblies reduce pressure loss and NOx emissions by enhancing mixing of injected reactants with passing combustion gases.

Swirl vanes in the dome passage enhance flame front turbulence to reduce NOx emissions.

A single-walled combustor liner integrates a venturi section with an external air deflector to direct cooling flow onto the reduced diameter portion.

Laminated alloy liners with variable porosity zones deliver tailored cooling flows, reducing critical liner temperatures and improving engine efficiency.

Conical-flat heat shields stabilize flames and reduce acoustic pressure oscillations by altering flow patterns with a specific half-angle geometry.

A folded annular combustor directs fuel and air radially to enhance mixing.

A dual pump fuel system segments flow capacity into a main and support unit managed by valve assemblies, reducing parasitic power draw during cruise conditions.

A turbine combustion chamber bottom uses sliding sleeves and radial clearance to allow free thermal expansion relative to axial walls.

A hermetic self-sealing environmental barrier coating layer stabilizes volume during heat treatment to prevent structural failure.

Segmented catalytic converters maintain emissions compliance below 50% load, preventing grid instability.

Rib-defined cooling channels in the transition nozzle reduce thermal stress on turbine components, extending lifespan while eliminating costly seal maintenance.

Noncollinear cooling passages in gas turbine igniter mounts increase path length to reduce local temperatures near the hot side flowpath.

Concave curved vortex generators improve homogeneous fuel mixing while reducing flow resistance and pollutant emissions.

A turbine fuel system uses a catalytic reformer to convert hydrocarbon fuels into hydrogen-rich reformed fuel for secondary injection.

Polygonal air and segmented hydrogen orifices improve mixture formation quality for gaseous fuels.

Segmented air passages cool the cartridge tip while maintaining pilot flame stability and optimal emissions in gas turbine combustors.

An asymmetric annular cowl reduces total pressure loss and improves primary air distribution in gas turbine engines by resolving flow dynamics trade-offs.

A turbine component cooling system redirects coolant flow by altering the cross-sectional area of specific passages to manage thermal loads.

Water injection into the second combustion area consumes oxygen, reducing NOx emissions while maintaining stable hydrogen operation.

A turbofan afterburner system diverts core exhaust flow through a dedicated second duct using controllable doors and fuel injectors.

Segmented lobes divide the mixture to reduce emissions while removable design simplifies maintenance.

Textured outer surface increases cooling medium turbulence to enhance heat transfer while preserving cooling hole integrity during manufacturing.

A wave-shaped combustor seal directs cooling fluid through impingement holes to enhance convective heat transfer on the liner surface.

Coupling pipes link independent fuel lines to shared nozzles, enabling rapid gas turbine combustor swaps without modifying the manifold.

Impingement wall directs coolant through apertures onto a solid aft wall, reducing thermal stress and preventing nozzle cracking.

Varying transition portion lengths in bundled tubes create multiple residence times, mitigating combustion instabilities without increasing device complexity.

A cooling sleeve directs chilled diffuser air around the fuel conduit to lower heating rates.

Equipment controller detects acoustic pressure amplitude changes and adjusts fuel split ratios between circuits.

Honeycomb seal accommodates thermal transients through elastic deformation, reducing plastic deformation risk and leakage at the combustor-turbine interface.

Helical cooling channels extend air flow residence time along the combustor liner downstream end portion to enhance thermal management.

Oblique cooling port arrangement in a gas turbine transition piece suppresses crack growth while maintaining thermal management.

Circumferential heat shield segments form complementary overlap joints to accommodate thermal expansion within a combustor assembly.

Tangential air jets prevent flame holding and reduce NOx emissions by keeping hydrogen fuel away from mixer walls.

An air injection annulus and divergent connection ring enable relative displacements between the injector and mixer device.

Axial staging of fuel and air injection reduces NOx emissions by minimizing reactant residence time at high temperatures while maintaining engine efficiency.

Dehumidified silicon-doped air minimizes silica volatilization, preventing material loss in high temperature combustion environments.

Elliptical inlet geometry and curved flow paths prevent sand accumulation in gas turbine combustor liners, maintaining cooling efficiency.

Segmented metering portions in a film cooling channel array diffuse cooling air laterally, preventing vortex formation that draws hot gas toward the surface.