Continuous Combustion Chamber TRIZ Cases

Helical apertures create counter-rotating vortices that dampen thermo-acoustic instability while ensuring uniform air-fuel mixing.

Segmented air injection stages manage fuel mixing to reduce NOx emissions while maintaining combustion stability.

A sealing clip locally deforms the combustor liner to seal the heat shield rail, eliminating coolant leakage gaps without blocking impingement holes.

Multi-staged combustor segments primary and secondary zones to reduce NOx emissions below CAEP/11 regulations while maintaining high combustion efficiency.

Segmented welded sleeve prevents hot air leakage while distributing thermal expansion stress, reducing component damage and material costs.

Intermediate burner section dampening cavities attenuate thermo-acoustic vibrations without increasing air consumption or lowering flame temperature.

Real-time oxygen monitoring in exhaust gas enables dynamic oxidant adjustment, resolving insufficient composition control and enhancing CO2 capture efficiency.

Spiral trip strips on a baffle insert generate vortices to boost heat transfer coefficients and reduce cooling flow requirements.

Segmented flange slits distribute thermal stress at pin holes, reducing cyclic fatigue and extending maintenance intervals.

Floating seals direct cooling air through impingement holes to lower igniter tip temperatures without disrupting combustion efficiency.

Segmented burner units with independent fuel supplies regulate air-fuel ratios to suppress precessing vortex cores and reduce NOx emissions.

Direct metal laser sintering creates a monolithic fuel injection head with integrally formed pre-mix tubes and injectors.

Exhaust diffuser temperature sensors detect flame failure in gas turbine engines, reducing false positive plant trips caused by sensor malfunctions.

Segmented outer wall isolates cooling cavity to prevent thermal interference, while sloped vanes swirl dilution air for improved temperature control.

A method for repairing bundled tube fuel injectors extends pre-mix tubes using fixed tube tips as radial heat shields.

A conical diffuser redirects coolant flow radially outward to preserve momentum and enhance cooling distribution.

A dual-wall tile assembly channels cooling air to impinge on hot tiles, enhancing heat transfer via turbulators.

A fuel nozzle assembly uses varying distances between swirler leading edges to maintain uniform air flow rates through the combustion device.

Radially offset swirl slots in a swirler body impart rotational flow to air, reducing thermal gradients and improving fuel atomization.

A microtube cluster burner discharges fuel and inert fluids at multiple longitudinal positions to optimize combustion modes.

Segmented cooling paths supply air to a resilient annular seal, reducing leakage while maintaining premixing air availability.

Radial air apertures and axial fuel injectors in mixing tubes achieve uniform combustion, reducing manufacturing costs and repair complexity.

Non-concentric fuel pipe arrangement compensates for thermal expansion and simplifies maintenance by allowing individual pipe exchanges.

Mechanical buffers between frames absorb thermal expansion and vibration, extending combustor lifetime.

A Helmholtz damper assembly integrates into a gas turbine fuel manifold to attenuate acoustic energy through resonant cavity design.

External cooling fins and effusion holes boost heat transfer efficiency in single skin combustors, reducing thermal fatigue without increasing air consumption.

A pivoting stowable spray bar moves between a deployed fuel delivery position and a stowed flow path clearance position.

A convolution seal accommodates thermal expansion between offset turbine transition ducts, preventing hot gas leakage and cooling air mixing.

Distributes hydrogen-rich fuel streams along a gas turbine combustion chamber to reduce nitrogen oxides and carbon monoxide emissions.

A contact prevention mechanism directs high-pressure carbon dioxide flow to shield the laser ignition heat-resistant glass from combustion gas exposure.

Radial openings in a conical deflector guide vectored oxidizer flows to cool the combustor wall, preventing hot gas trapping and reducing emissions.

Inclined flow path redirects mixed fluid injection to minimize radiant heat exposure, preventing auto-ignition and flash-back phenomena in combustors.

Friction fit intermediate ducts accommodate thermal expansion to prevent binding and reduce NOx emissions in gas turbine engines.

Modifying contact surface zeta potential prevents carbonaceous deposits on gas turbine components, reducing maintenance needs.

Axially-elongated airflow injection holes optimize cooling distribution across a gas turbine combustor liner wall.

A gas turbine fuel flow rate setting device adjusts the fuel distribution across premixing nozzle groups to maintain stable combustion.

Outlet duct assembly fluidly connects the second turbine to the diffuser and primary combustor in a dual-spool gas turbine engine.

A floating aft plate assembly accommodates thermal expansion in gas turbine combustion nozzles.

Segmented guide vanes rectify airflow to each nozzle array, stabilizing combustion and reducing NOx emissions without complex fuel supply systems.

Support plate rigidly joins fuel nozzle to endcover, reducing vibration and improving high cycle fatigue margins in gas turbine combustors.

A gas turbine combustor louver directs airflow to generate a protective air film along the outer liner.

A discontinuity in the internal profile creates recirculation zones that enhance turbulence and mixing, resolving large droplet formation issues.

Varied preform aperture contours compensate for non-uniform coating application, ensuring uniform slope profiles and reliable cooling effectiveness.

Segmented combustor zones reduce NOx via chemical reduction while maintaining burner reliability against flashback risks.

Reformer uses exothermic heat to vaporize heavy hydrocarbons, eliminating expensive high-temperature piping materials.

Segmented metering and lobed diffusing sections reduce flow separation in gas turbine components, minimizing excessive cooling fluid requirements.

An angled hub extension redirects compressor exit flow to improve pressure recovery and reduce back pressure in gas turbine engines.

A gas turbine combustor design uses specific burner length and dome height ratios to manage hydrogen flame propagation.

A precombustion chamber generates hot combustion gases to reliably ignite constant-volume turbine engine modules under severe cold and high altitude conditions.

Liquid ammonia injection into gas turbine compressors cools intake air through evaporation, eliminating water usage and scale formation risks.