Continuous Combustion Chamber TRIZ Cases

A liquid-cooled air-breathing rocket engine uses a funnel-shaped intake and toroidal combustion chamber to generate thrust via pressure differentials.

Movable plunger and rotating disk systems alter fuel system acoustic impedance to shift combustion dynamics frequencies.

Segmented air purge passage with vanes removes trapped air from nozzle guide interface, reducing wear and improving fuel atomization.

Elliptical-to-circular air guide unit minimizes pressure loss by aligning swirl angles with turbine rotation, improving combustor efficiency.

Segmenting panel and stud manufacturing resolves casting porosity and dimensional conformance issues.

Extending the fuel nozzle to the combustion liner end cap exit plane reduces residence time while increased swirler angle maintains fuel-air mixedness.

Dome cooling holes direct airflow onto the heat shield deflector lip, preventing premature wear from high temperature exposure.

Segmented ducts reduce exhaust velocity to improve contaminant removal without increasing the nozzle outlet area.

Segmented blade injector achieves lean combustion and reduces NOx emissions through precise staged fuel delivery.

Embedding fuel circuits in the mixer sidewall directs flow through an inner passage, reducing NOx production and shortening combustor length.

Segmented lance injectors distribute primary fuel and inert fluid to minimize NOx formation while maintaining flame stability across varying load conditions.

A turbomachine combustor injects hydrogen mixtures into primary and secondary zones to stabilize combustion.

A silicon bond coating melts within substrate cavities to maintain adhesion under thermal stress.

Premixing fuel with compressor discharge air in an elongate conduit increases CO consumption while limiting NOx emissions.

Segmented metal sheet profiles yield resiliently to compensate for thermal expansion and vibrations in gas turbine combustion chambers.

Dynamic spray apparatus rotates and translates to mask complex geometries, preventing incomplete coverage on curved compressor vanes.

Segmented heat shield panels with varying rail heights seal the combustor shell, preventing radial air leakage and maintaining cooling efficiency.

Open areas in swirl vanes communicate pressure across the vane thickness, damping combustion dynamics instability while maintaining structural integrity.

Cross-over ribs and pedestals align to form structural support in gas turbine airfoils, reducing pressure losses while maintaining cooling efficiency.

Additive manufacturing consolidates discrete turbine components into a single part, eliminating assembly complexity while maintaining precision.