Continuous Combustion Chamber TRIZ Cases

Beveled upstream faces on the sliding bushing and annular cup eliminate flow obstacles, reducing pressure drops and coke deposits in turbomachines.

Casting locators enable precise film hole positioning, converting unwanted byproducts into functional cooling features for temperature reduction.

Removable adapter extends flow passage length in bundled tube fuel nozzles to shift acoustic pressure oscillations out-of-phase with combustor resonance modes.

A steam passage provides a radial buffer between fuel and air flows, preventing flashback while maintaining combustion efficiency.

A gas turbine combustor casing uses segmented cooling zones to lower manufacturing costs.

Fences on combustion chamber tiles direct coolant axially, preventing hot gas ingress and flow reversal at dilution ports.

A plasma igniter with an electronic driver unit generates a stable arc to ignite fuel-air mixtures in gas turbine engines.

Fuel injection ports direct flow into air circulation spaces to atomize droplets, resolving low-speed mixing bottlenecks that cause large particle sizes.

Slotted exterior overlapping portions accommodate manufacturing tolerances without interfering with cooling airflow or fuel nozzle openings.

Vaporizing support structures enable complex additive manufactured combustor shell geometries without permanent mass penalties.

Integrated CMC heat shield cups and collars compensate for thermal expansion differences between the shield and metal dome, simplifying fabrication.

Segmented axial slots in the fastening web reduce thermal stress and extend service life while lowering cooling air consumption.

Exhaust holes in the chamber walls discharge cooling air, preventing fuel-trapping films that reduce combustion efficiency.

Segmented cooling channels direct high-pressure air across the igniter wall to prevent thermal stress and extend component life.

An annular wall defines a cooling flow channel within the bundled tube fuel nozzle, reducing aft plate heat exposure and material degradation.

Reroutes cooling fluid to combustor resonators via a distributor manifold, reducing NOx emissions and improving engine efficiency.

A fuel cell stack positioned around a gas turbine combustion chamber provides output products to adjust local temperature distribution.

A turbine transition piece uses a boss fixed by a single bolt to secure the duct and cover.

Concatenated dilution passage merges discrete holes and annular slots to resolve low turbulence mixing inefficiencies in gas turbine combustors.

A combustor mixing assembly uses non-uniform fuel injection ports to create static pressure differences that evacuate residual fuel from the main mixer.

Direct waste gas flow between jet carriers stabilizes flames while reducing nitrogen oxide production and chamber volume.

Inclined pin-fins create turbulence that boosts heat transfer, reducing cooling air volume and lowering NOx emissions.

Varying cooling hole densities near large openings stabilizes airflow and reduces thermal stresses on combustor liners.

Radial supports brace the combustor end cap to raise resonant frequency, stabilizing combustion dynamics and extending component lifespan.

An inclined cooling hole in a nozzle guide prevents blockage by the open flange part, ensuring reliable air supply for weight reduction.

A mobile frame with a vertically extendable arm and carriage replaces lower combustors without fixed rails, reducing downtime.

Nested housing transforms dead space into functional volume, enabling Stirling engine integration and eliminating wasted interior capacity.

Steam injection nozzles within the combustor cowl deliver steam to a plenum, reducing NOx emissions while preventing flameout conditions.

Segmented void structures in auxetic metamaterials eliminate stress concentrations at minor radii, preventing cracking in gas turbine components.

A convex anti-fretting part transfers sliding contact from the membrane to a sacrificial ring.

Axial springs maintain sealed contact on ceramic matrix composite liners, preventing leakage and wear from thermal expansion mismatches.

Flow conduits deliver pressurized fluid into the cap chamber, increasing pressure drop to overcome dynamic waves and prevent hot gas ingress.

Nested concentric tubes distribute axial stress while a vacuum cavity insulates fluid from external heat in gas turbine fuel systems.

Segmented reintroduction slots distribute bypass flow to prevent flame quenching and tailor temperature profiles.

Segmented dilution passages with protruding extensions balance sealing reliability against manufacturing complexity in gas turbine combustors.

Segmented aperture patterns achieve negative Poisson's Ratio behavior, reducing thermal stresses and extending fatigue life without complex manufacturing.

Axially staged injectors extend through flame fronts to improve fuel-air mixing, reducing rich zones and minimizing NOx emissions.

A dual-zone gas turbine combustor uses segregated fuel injectors to control combustion zones.

A combustion chamber guide device uses a floating ring with an intermediate overflow space to prevent weld obstruction.

Segmented thermal barrier and reflective coatings reduce component temperatures while maintaining cooling air flow.

Optimizing the axial distance ratio between vortex generator trailing edges and nozzle injection plane improves fuel air mixing quality to reduce NOx emissions.

A contoured cooling passage accelerates airflow through a decreasing cross-sectional area to cool the mixer.

A gas turbine combustor nozzle employs a venturi-shaped profile to prevent flashback damage while ensuring stable combustion.

Differentiating peripheral and center swirler inlet cup dimensions eliminates air pocket formation and improves air-fuel mixing quality.

Flow disruption surface reduces mixing losses and pressure drops by improving flow uniformity before the turbine.

Annular resonating tubes attenuate acoustic oscillations via dissipative losses, reducing dynamic pressure pulses without increasing emissions.

Segmented nozzle tips create distinct recirculation zones through axial flow, reducing pressure drop while maintaining flame stability.

Dual-end support reduces member length and weight, enabling easy attachment in restricted spaces without complex rail systems.

Pre-chambers isolate resonators from hot gases, preventing overheating and maintaining resonance effectiveness in rocket engines.