Continuous Combustion Chamber TRIZ Cases

A cross-fire tube assembly uses a windowed retention clip to secure the tube against the combustor liner.

Angled effusion holes in combustor liners direct airflow to create time delays that decouple noise frequencies.

An electrographitic carbon bushing guides and supports an augmentor fuel conduit to minimize wear.

Helical premix passages mix fuel and air before injection to maintain flame stability while reducing emissions.

Additive manufacturing forms a unitary gas turbine structure, eliminating assembly steps to reduce component count and production costs.

Burner plate protrusions create high-temperature recirculation flows to stabilize flames in coaxial jet combustion systems.

Dual arm V brackets manage thermal expansion between ceramic matrix composite and metallic annular members to prevent material damage.

Oblique swirling guides in a combustor nozzle improve air-fuel mixing, reducing nitrogen oxide generation while maintaining flame stability.

Removable axial retention prevents weld breakage during maintenance by segmenting fastening elements on the combustion chamber walls.

Pivoting arm tool extends through compressor casing to apply longitudinal force on cross-fire tubes, resolving limited maintenance access in plenum designs.

Integrates a coolant fluid circuit within turbine engine link walls to eliminate temperature gradients that cause mechanical stress and crack formation.

Wing-like flow directors guide air to an internal swirler, resolving poor fuel-air distribution and reducing emissions in gas turbine engines.

Internal cooling flow paths in the downstream plate reduce attached flame risk while simplifying fuel injector structure.

A flexible leaf spring hanger assembly supports exhaust duct liners using a locking member and mounting member.

A liquid air energy release apparatus pressurizes cryogenic fluid and extracts power through a thermal cycle.

Resupply cover shields injected air in hybrid skin core cavities, reducing pressure loss while maintaining thermal cooling effectiveness.

An acoustic driver generates counter-waves to eliminate pressure perturbations at fuel injection orifices.

A serpentine groove on a gas turbine substrate mechanically interlocks with a protective coating to enhance bond strength.

A composite damping member absorbs vibrations between a transition duct and its mounting points in a gas turbine engine.

Segmented passages control volumetric flow ratios to prevent flame holding and nozzle damage during syngas combustion.

A double-swirling burner structure elevates flame temperatures to stabilize combustion in gas turbines.

Pressure sensors measure flow rates via differential drops to eliminate mechanical meter complexity and reduce system pressure loss.

Injecting exhaust directly into feed water eliminates surface-based heat exchange losses and reduces boiler system complexity.

A dynamic control system adjusts diluent flow to maintain homogeneous fuel mixing in gas turbines.

Communication holes position film air at low flow regions to prevent flashback in gas turbine combustors.

Adjacent redundant endrails create a pressure gradient that maintains cooling airflow and prevents rapid oxidation when the primary structure sustains damage.

Split-ring collar system secures ceramic matrix composite heat shields to combustor domes.

Segmented retention blocks with integrated tabs transfer axial loads to eliminate circumferential clearance requirements in gas turbine vane supports.

Axial mounting means and local spacer ribs maintain minimal gaps between segments, enabling film cooling while reducing assembly time.

Shared common skids heat, filter, and pump biofuel to injection points, preventing gelling and enabling real-time blend ratio adjustments.

Deflector panels use circumferential scallops and centerline studs to distribute stress.

Plasma actuator deflects leakage fluid through variable stator vane clearances, suppressing vortex formation and reducing energy losses in axial compressors.

Integral manifold and flow sleeve reduce vibration while dissipating heat in the transition piece.

Integrating the deflector and mixer into one retainer eliminates bolted joints, reducing thermal stress.

Reinforcing ribs on the shroud outer surface resist centrifugal stress without obstructing combustion gas flow.