Turbine/Propulsion Engine Cooling TRIZ Cases

Impingement plates adjust pressure to reduce cooling air flow to the suction side, preventing wasted air from mixing with combustion gas.

Closed loop liquid metal cooling uses Bismuth fluid and Tantalum liners to cool turbine stator vanes without bleeding compressor air.

A gas turbine engine shaft uses segmented cooling circuits to manage heat loads from high torque and increased fan diameters.

Alternating open and sealed cooling holes in a turbine disk alleviate tensile stress concentration while maintaining sufficient cooling passage area.

A reconfigurable fan exit nozzle directs airflow through a heat exchanger to cool lubricating fluids.

Adjustable dual heat exchanger rows in gas turbine flow ducts manage pressure drop to reduce fuel consumption penalties.

A fixed flow cooling compressor regulates air delivery to resolve pressure changes and flow resistance issues during variable vane actuation.

An annular partitioning member guides compressed gas uniformly through communication holes, preventing circumferential flow unevenness and reducing engine size.

A movable member modulates airflow into a gas turbine rotor bore to adjust the clearance gap between blades and casing.

Segmented cooling circuit with axial skin cores and core cavities reduces dedicated airflow consumption while maintaining heat transfer.

Temperature sensors gate cleaning agent delivery to prevent thermal damage, while optical flame detectors trigger fire suppression.

An integral metering feature merges directly into the swirler tube structure to precisely constrain cooling air flow rates.

An electric motor replaces pneumatic starters to eliminate bowed rotor conditions from uneven thermal expansion while reducing mechanical wear.

Electric drive decouples auxiliary compressor speed from the main engine, reducing energy losses while maintaining optimal turbine temperatures.

Dynamic valve control eliminates airflow imbalances across turbine air lines, preventing energy waste and system overloading.

Periodic valve operation removes condensed water from the cooling air system to prevent corrosion while maintaining compressed air pressure.

Rotating detonation combustors pilot scramjet operation to resolve unstart conditions across varying Mach numbers.

A gas turbine engine delivers intercooled air to rotating components via a cooling compressor and heat exchanger.

Radial arm inlet draws primary flow air to cool lubricating oil pipes, resolving insufficient heat exchange capacity in new turbine architectures.

Bypass valves dynamically adjust heat transfer rates in gas turbine engines, reducing thermal strain and transient shock during hydrogen fuel operation.

Temperature sensors detect gradients and trigger localized cooling on the stator to prevent rotor deformation during shutdown.

Radially positioned purge openings create a targeted air barrier that prevents hot gas ingestion while reducing required purge mass flow rates.

A staged bleed conduit system incrementally depressurizes high-pressure gas flow through expansion sections and diffuser plates.

Narrow passage portions in lateral channels curb cooling air flow rate to preserve combustor efficiency.