Continuous Combustion Chamber TRIZ Cases

Obliquely oriented conduit members redirect cooling air through sleeve holes to enhance flow capture efficiency.

A turbine blade cooling air hole uses an expanded diameter portion to spread airflow across the external wall surface.

Segmented combustor nozzles employ micro-channel cooling passages to balance airflow requirements and reduce NOx emissions.

Segmented apertures direct cooling air to impinge against a turbine heat shield panel for targeted thermal protection.

A dual-perforated plate combustor uses an air chamber to cover gas nozzle jet holes with airflow during pilot fuel burning.

Annular heat shield with circumferential groove retains support lock tab to minimize convective heat transfer.

Rail studs bridge large manufacturing tolerances between cast liners and sheet metal shells, reducing leakage while maintaining structural integrity.

Reducing tail pipe flange stiffness balances thermal expansion forces to minimize side plate stress and improve fatigue resistance.

Segmented fuel channels feed burner nozzles from a lightweight support, reducing weight and cost.

Offset posts disperse gap flow obstruction and maintain uniform distance to improve gas turbine vane cooling performance.

Two independent air supply passages enable dynamic routing that reduces NOx emissions while minimizing pressure loss across the combustion system.

Web-like ribs protrude into fastening grooves to direct cooling air, resolving uneven distribution that causes hot gas entry and structural damage.

A multi-port fuel injector uses monotonically downward passages to maintain consistent fluid flow across varying phases.

A trapped dual vortex cavity sustains counter rotating vortices to optimize fuel air mixing in gas turbine engines.

A load compressor driven by a turbine directs compressed air to cool the gas generator section of an auxiliary power unit.

Electrical resistance heater initiates catalytic combustion during start-up, reducing emissions and complexity compared to continuous pre-burner systems.

Aerofoil feed arm deflects airflow radially inward, resolving obstruction issues and improving combustion efficiency.

Varying fuel nozzle outer diameters by radial position reduces vibration stress while maintaining uniform combustion.

Axial swirlers in the pilot housing optimize fuel-air mixing to reduce NOx emissions while maintaining thermal efficiency across operating conditions.

Balanced alloying elements control gamma prime precipitation and reduce eta phase formation to resolve dwell fatigue resistance versus density trade-offs.

Airflow system prevents cooling hole obstruction during thermal spray coating, reducing costly clearance processes and improving coating bond quality.

Progressively decreasing channel areas accelerate coolant airflow to eliminate localized hot spots and ensure uniform cooling across the combustor liner.

Dual cavity acoustic dampers target combustion pressure oscillations via Helmholtz resonance, suppressing structural degradation risks.

A combustor flame holding ring uses circumferential openings to vary air inlet density and impair local flame stability.

A recuperated micro gas turbine combustor uses a segmented single burner to stage combustion and mixing for stable operation.

Radial turbine layout increases efficiency by expanding outer circumference while maintaining compact height.

An adjustable bypass conduit creates destructive interference to attenuate pressure oscillations and vibrations in gas turbine fuel systems.

Corrugated combustor geometry accelerates hot gases to ideal turbine inlet velocities, eliminating first stage vane nozzles and reducing flow losses.