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.