Continuous Combustion Chamber TRIZ Cases

A film hole with optimized hooded length to metering diameter ratio diffuses cooling fluid before it contacts hot combustion gases.

Staggered plunged air admission holes in annular combustors reduce NOx emissions by controlling peak temperatures and minimizing recirculation.

Segmenting the diffuser case into modular walls and struts cuts weight while maintaining structural integrity for gas turbine engines.

Tapered premixing tubes in a micromixer injector enhance fuel-air mixing efficiency to reduce nitrogen oxide emissions.

Elastomeric seals accommodate thermal expansion in gas turbine combustors to maintain uniform contact between rigid components.

Opposing scarf orientations on fuel posts create pressure differentials that drive purge air flow, preventing fuel stagnation and coking during low operation.

Concentric perforated diffuser holes stabilize turbine flames in high-temperature recuperator cycles, eliminating soot and reducing pollutant emissions.

Segmented planks on a skeleton mesh reduce air leakage while maintaining liner durability.

Spacer shoe retains air baffle via intermediary lugs, preventing heat shield weakening from machining.

Segmented annular combustors use axially staged panel fuel injectors to reduce NOx emissions while maintaining air flow balance.

A T-bar hanger system connects spaced gas turbine components using a rotating crossbar and bracket assembly.

Staggered supply ports create a vortex for uniform mixing, preventing radiant heat from reaching the mixing region to stop flashback.

Inclined pyramidal injection holes generate recirculation areas that prevent local heating of combustor components while reducing NOx emissions.

Applying metal oxide or carbide coatings to ceramic cores prevents breakage of fine details during gas turbine engine manufacturing.

Nested annular passages in the manifold body reduce volume and complexity while enabling independent fuel staging.

Angled combustor liners extend the flowpath length within compact gas turbine engines, reducing pressure losses and improving flow uniformity.

Ceramic matrix composite dome deflectors resist thermal breakdown through integrated cooling passages, extending service life.

Segmented duct links accommodate thermal expansion while simplifying assembly.

Segmented baffles redirect compressed working fluid through an arcuate annular guide, achieving uniform radial distribution without increasing pressure drops.

Segmented flange lands reduce heat transfer to the fuel nozzle, preventing leakages and blockages caused by high temperatures.

Spring-loaded pins preload CMC panels against liners, reducing force concentrations that compromise structural integrity.

Non-perpendicular liner panel edges sweep gaps to prevent axial hot streak injection and shell burnback.

Offsetting the fuel injector axis within the swirler breaks combustion flame symmetry, preventing resonance with acoustic modes.

Radial deformations guide cooling air around fuel injection systems to ensure uniform heat distribution across deflector surfaces.

A recess isolates the neck mouth from chamber grazing flow to maintain undisturbed bias flow conditions.

Additive manufacturing merges walls and pedestals to eliminate tolerance variations in gas turbine cooling.

Segmented combustion zones balance efficiency against NOx emissions by applying leaner stoichiometry in secondary stages.

Threaded hanger rotates relative to inner duct via bushing to accommodate thermal growth and misalignment in gas turbine engines.

Compound angled cooling features improve coolant attachment to hot gas path surfaces, reducing mixing and manufacturing complexity.

A catalytic igniter uses a metallic shell and fuel tube to direct gas flow across a catalyst for auto-ignition.

Groove surrounding fuel injection hole directs airflow to prevent recirculation bubble formation and flame holding.

Segmented cooling passages route compressor air to reduce operating temperatures without complex effusion holes.

Internal helical fuel passages in a gas turbine nozzle stem increase residence time to reduce heat transfer and prevent coke formation.

An auxiliary combustion chamber creates a recirculation zone that stabilizes flame propagation, ensuring reliable ignition during cold starts with heavy fuels.

Offset film cooling hole rows create staggered coolant jets that counteract combustion gas swirl, reducing thermal defects on the liner surface.

A movable restrictor plate adjusts inlet port area in wave rotor combustors, optimizing combustion efficiency across varying engine operating conditions.

A dual fuel combustor nozzle uses a pre-emergence zone to facilitate efficient fuel mixing for turbomachine applications.

A contoured thermal barrier coating manages flow fields around combustor dilution holes, reducing liner distress caused by air jets in cross-flow.

Segmented boss geometry minimizes flow restriction in cooling passages to ensure uniform airflow distribution into the primary combustion chamber.

A manifold fitting provides dual fluid communication paths in a compact configuration.

Decouple the aft plate from a bundled tube fuel injector to expose pre-mix tubes for inspection and repair.

Axially-staged lean-direct injectors reduce NOx emissions by stabilizing turbulent flames and preventing flashback in gas turbine combustors.

Radial cooling vanes act as heat sinks to lower operating temperatures and reduce thermal erosion in turbine engines.

Segmenting radial fuel delivery into multiple independent injectors achieves high-energy combustion without generating large swirls that cause instability.

Laser-drilled insert holes direct cooling air to the tip, reducing NOx emissions while maintaining component temperature.

Percussion welding attaches cooling pins to a fabricated supplemental body, restoring damaged float wall panels and reducing maintenance costs.

Extracting distressed regions from gas turbine combustor liners reduces material wastage while maintaining critical dimensional accuracy.

Strategic nozzle placement upstream of the flow restriction section prevents combustion gas ingestion into inactive fuel lines, eliminating cross-talk.