Continuous Combustion Chamber TRIZ Cases

Diverging section directs cooling fluid to prevent particle accumulation in effusion cooling holes.

Placing an igniter upstream within the fuel injector reduces peak burn temperatures and controls burning velocity, extending engine lifespan.

A gas turbine combustor pipe portion deforms to accommodate thermal expansion differences between connected components.

Low-temperature carbon dioxide cools the combustor casing, allowing inexpensive Fe-based steel instead of costly Ni-based alloys.

A bellows-shaped flexible sleeve seal prevents pressurized gas leakage between turbine cases, eliminating wear from rigid components.

Multi-stage fuel injection modulates flow across distinct injector groups, maintaining stability and low emissions at part-load conditions.

An impingement plate with an increased cross-flow structure creates larger cavities to manage airflow dynamics.

Segmented impingement and effusion passages create pressure drops that cool walls, resolving low supply pressure limits at high altitude.

A rare-earth silicate bond coat layer with compressive residual stress protects ceramic matrix composite turbine parts.

A fuel-air heat exchanger integrated into a gas turbine fuel nozzle transfers thermal energy between the fuel stream and cooling air.

Bolted fasteners couple interchangeable combustor liner segments, allowing replacement of worn areas without discarding the entire assembly.

A gas turbine combustor turn guide protruding from the inner cylinder smoothly connects to the outer cylinder to stabilize compressed air flow.

Heated mandrel expansion plastically deforms gas turbine engine flange bolt hole circumferences, countering stress cracking from heat loads.

Unitary cowl integration eliminates coupling locations and reduces weight while maintaining structural integrity in gas turbine engines.

Axially staged air and fuel injection systems reduce NOx emissions by lowering combustion temperatures while maintaining engine efficiency.

A rotary furnace tube with a moveable electrode and wave energy source sustains plasma via tangential flow.

Segmented dome and deflector assemblies use mechanical fits instead of welds, allowing repair without destroying components.

Fluid boundaries obstruct working fluid flow through combustor tubes to dampen resonant frequencies and reduce combustion dynamics.

Segmented injector openings inject fuel perpendicular to airflow, improving mixing efficiency and combustion stability across supersonic speed ranges.

Secondary fuel nozzles in the dilution fence enhance mixing and cooling, reducing high temperature regions and NOx emissions.

Radially extending cooling passages route coolant through the aft frame body and into the combustor flow path.

A molybdenum-rich alloy manufacturing method produces gas turbine components with enhanced strength and thermal resistance.

Differential cooling at portal holes reduces thermal stress and maintains sealing integrity at the outer casing split plane during transient operations.

A coupling device selectively transmits energy between a power turbine and a compressor boost stage to adjust rotational speeds.

Segmented coaxial injection of liner cooling air achieves uniform temperature distribution while minimizing pressure drop in sequential combustion systems.

Optimized cooling arrangement delivers targeted fluid distribution to specific combustor zones.

A fuel injector injects secondary fluid jets into a main flowpath to enhance turbulent mixing and combustion efficiency.

An embedded ceramic connector in a CMC liner tile accommodates thermal expansion differences, reducing structural stress on the metal support.

A deflector assembly with legs and panels directs cooling air through liner apertures to resolve non-uniform temperature profiles.

Segmented chute assemblies with threaded retention washers prevent damage during operation while allowing easy removal for maintenance.

Spring-loaded retention plates replace permanent brazing to enable premix tube replacement and reduce assembly time.

A fuel-gas heating channel diverts high-pressure gas to raise blast furnace temperature before the wet dust collector inlet.

Angled spiraling injectors reduce vortex shedding and thermal gradients, extending combustor hardware life.

Pockets on the second wall redirect cooling fluid to prevent particulate blockages in gas turbine hot section components.

An integrally formed ceramic matrix composite combustor dome and liner assembly eliminates mechanical seams to improve internal aerodynamics.

A catalytic partial oxidation reactor converts heavy hydrocarbons into stable combustion gases.

A retaining ring and shoulder mechanism mechanically secures the injection system to the combustion chamber deflector.

Segmented support ring assembly with lateral openings engages transition ducts to minimize leakage and accommodate thermal stresses.

Through-holes in segmented walls supply cooling air to the gas washed surface, preventing oxidation and premature degradation of the abradable liner.

Skewed non-linear combustor liner interfaces eliminate steps and dead regions that reduce cooling efficiency.

A burner fuel passage includes a turn-back part that cools the outer circumference to prevent flashback while reducing NOx emissions.

Entrained aluminum oxide particles flow through combustion chamber cooling passages to remove fine sand and dust obstructions that reduce cooling efficacy.

Dual-pressure premixing nozzles mix fuel with high and low pressure air streams to prevent nozzle coking during liquid fuel combustion.

Trailing edge nozzle injection on a streamlined burner prevents flashback and reduces pollutant emissions with hydrogen fuels.

Strategic heat transfer ribs on combustor liner panels boost convective cooling to resolve insufficient thermal protection in high temperature zones.

A vortex combustion chamber creates rapid air rotation to enable stable flameless combustion in gas microturbines.

Internal tabs and caps join combustion chamber fairing components, eliminating bolt heads that disturb airflow while allowing repair by grinding welded zones.

A nozzle assembly with a central fuel pipe and radial air channels directs separate streams for downstream mixing.

Axial swirler with discontinuous trailing edge creates distinct radial flow velocity profiles for controlled fuel distribution.

Effusion holes in heat transfer augmentors channel compressed gas to reduce panel temperature and extend component lifespan.