Continuous Combustion Chamber TRIZ Cases

Hydrogen introduced downstream shifts CVD equilibrium to limit pyrophoric exhaust deposits and keep ceramic matrix composite production running.

Arcuate members and a linear actuator re-round an out-of-round combustor body in place, cutting repair time and avoiding removal.

A continuous curved seal enables axial nozzle installation and removal while reducing seal damage and leakage between combustor liner segments.

A spring-retained CMC combustor liner avoids direct threading and accommodates thermal growth to reduce cracking and delamination.

Relief-cut curved seals fit radially offset gas turbine slots, easing installation while reducing leakage between adjacent components.

Low-profile tabs and removable stop brackets stabilize a gas turbine combustion liner while reducing airflow blockage, wear, and emissions.

High-pressure bypass airflow keeps a segmented piston ring engaged with the combustor liner, limiting leakage during takeoff rotation.

Angled outer rib corners boost turbulence for cooling, while curved inner corners cut stress concentration and cracking in gas turbine passages.

A press-fit spacer in an oblong combustor shell aperture keeps panels secure during thermal expansion, reducing buckling, cracking, and fatigue.

A radiused perimeter step in a gas turbine case boss eases wall-to-boss transitions, cutting stress concentration and extending case life.

A coiled fuel conduit with locally thicker bend regions accommodates thermal expansion and limits stress fractures in gas turbine injectors.

Sacrificial Au-Cu braze plugs keep cooling holes open during thermal barrier coating, then are cleared by heat, gas, and vibration.

Additive manufacturing turns multi-part gas turbine fuel manifolds into seamless spray bars that cut joints, leakage risk, weight, and service complexity.

A non-circular washer and puck interface lowers pressure-driven force on internal components while preserving sealing and axial sliding under thermal expansion.

Pressurized fluid expands a fastener head inside a stepped cavity to secure ceramic composite parts while minimizing thermal stress.

Peripheral channels and airflow passages cool combustor attachment features, reducing hotspots, oxidation, and thermal damage.

Diffuser-shaped rail orifices direct cooling air into a protective film that cools combustor panels and liners while limiting oxidation and burnback.

A locking member and compliant interface secure a turbine engine grommet while reducing CMC delamination, wear, and tool-based removal damage.

Bevel-edge channels and recesses help ceramic thermal barrier coatings absorb thermal strain and resist edge spallation in turbine parts.

A splined fitting and drive-wheel tool speed gas turbine hose removal and installation while reducing injury risk, scrap, and gasket damage.

Laser drilling and weld-closing form impingement and effusion holes after bonding, avoiding distortion, masking cost, and bond-quality loss.

Laser drilling and welding form impingement and effusion holes after panel bonding, improving hole accuracy, bonding quality, and coating flow.

Incremental axial positioning and circumferential force distribution help install or remove combustion liners without coating damage.

A gas bearing with a transmission disk and damping member supports supercritical turbine shafts, cutting vibration, stress, and oil-bearing maintenance.

Wick-based heat transfer cells move liquid metal coolant without pumps, helping gas turbine combustors handle high heat loads and avoid hotspots.

Inclined first and second cooling holes focus compressed air on the combustor seal area, improving local cooling while limiting pressure drop.

Temporary braze plugs block coating entry into cooling holes, then remelt for removal to preserve heat transfer and coating coverage.

Staggered core extensions reshape internal airfoil cooling flow to improve heat transfer and reduce cooling-air cycle penalties.

Segmented honeycomb seal rings block compressed air leakage between the liner and transition piece while accommodating thermal expansion.

An integrated threaded insert seals the fastener interface in gas turbine engines, reducing fluid leakage and supporting fuel economy.

Localized wall thickening at curved sections helps a coiled fuel injector conduit absorb thermal gradients, reducing stress fractures and service needs.

A track-guided lift arm and engagement frame reduce handling force while improving combustor assembly alignment during turbine maintenance.

Impingement cooling holes and a plenum shield the fuel nozzle venturi from high thermal loads, extending heat shield life and easing replacement.

Angled rail-member orifices redirect cooling air across adjacent combustor panels to improve thermal protection and reduce oxidation distress.

Cooling holes cast and drilled along common vectors spread air uniformly across a combustor heat shield to improve thermal protection.

A crimped boss and annular element secure and position the flame tube without TIG welding, cutting deformation, rework, and replacement effort.

Capillary wick heat transfer cells move liquid metal coolant without pumps, helping combustor liners handle high heat loads and avoid hot spots.

Alternating members with different thermal expansion coefficients adjust turbine clearances automatically, reducing leakage and collision risk.

Multiple axial fuel stages split compressor air between nozzle and injectors to improve turndown, liner cooling, and NOx control.

Alternating primary and secondary injectors enable faster relight and stronger flame-out resistance in aircraft gas turbines, especially with hydrogen fuel.

Steam injected through a combustor quench aperture mixes with air to lower flame temperature, cut NOx, and preserve combustion efficiency.

Annular fuel galleries around each air passage improve hydrogen micro-mix uniformity, helping aircraft gas turbines cut NOx and avoid outlet blockages.

A split fuel-nozzle combustor and SAF use cut gas turbine nvPM emissions by tuning nozzle ratios and local fuel flow rates.

Radial and axial swirlers create a recirculation zone that improves turbine combustor light-off, re-light, and smoke reduction.

Separate hydrogen and hydrocarbon injection paths in mixing tubes stabilize flames and support low-emission gas turbine combustion.

A position sensor and diagnostic unit detect when a gas turbine combustor ignition plug fails to reach insertion, avoiding wasteful restarts.

Integral heat-pipe and cavity features spread impingement cooling across combustor panels to cut hot spots and extend component life.

Heating fuel with engine oil lowers viscosity before the combustor, improving lean-burn atomisation while limiting pump wear and coking.

A multi-tube fuel nozzle uses an integral air diffuser to redirect flow radially inward, improving uniformity and reducing flow separation.

Raised walls segment the impingement surface into cells that block cross-flow and eliminate static zones, maintaining jet stability and improving heat removal.