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.

Interlocking flange teeth and lugs constrain the movable ring, reducing thermal gradient stresses and extending service life.

Injection nozzle protrusions guide cooling fluid flow inside turbine blade leading edges, reducing uneven thermal loads and preventing structural deformation.

An oil-cooled heat exchanger chills phase change fluid that sprays onto the engine inlet, removing ice without parasitic load or bleed air extraction.

Heated fuel and oil thermally interact with super-cooled air cycle machine flow upstream, preventing ice accumulation on heat exchanger leading edges.

Cryogenic fuel lines condense exhaust water vapor to recover thermal energy, reducing engine weight while improving combustion efficiency.

Segmented dual cooling circuits reduce thermal-mechanical fatigue and oxidation risks in turbine platforms.

A segmented flow diverter redirects cooling fluid circumferentially around the diffuser case to eliminate hot spots and improve compressor durability.

Circumferential surface air-oil heat exchanger in the inter-flow compartment reduces aerodynamic drag and mass compared to radial arm designs.

An obstruction and ramp feature equalize fluid pressures in adjacent cooling passages, reducing leakage through cross channels.

A turbine anti-ice valve integrates an internal heat exchanger to cool muscle air using a separate cooling passage.

A heat exchanger mounted in an intermediate chamber cools high-pressure air using lower compressor bleed.

Dual bleed lines and a bypass line supply cooling air to hot parts, preventing heat damage when control valves fail.

A gas turbine cooling system directs mixed airflows to maintain component temperatures.

A combined cycle power plant uses waste heat to cool gas turbine intake air via a carbon dioxide operating fluid.

Aligning stator blades with cooling injection ports reduces thermal loads and minimizes compressor bleed air consumption.

Modulates thermal transport bus pump speed and valves to stabilize working fluid state during engine transients.

TBPP lubricant vapor cools bearings without recirculation, eliminating heat exchanger failures in high-temperature supersonic applications.

Injecting water into compressed air increases mass flow and heat extraction efficiency, overcoming power limits from ambient temperature constraints.

Positioning an engine electronic component in the fanstream duct enables passive cooling and active heating to mitigate temperature-induced stress.

Thermal expansion inserts modulate cooling fluid flow in turbine components, reducing engine weight by eliminating complex valve networks.

Segmented radial cooling channels manage thermal gradients across ceramic matrix composite stator airfoils.

Segmented lid portions create turn-back flow passages in a serpentine airfoil, reducing thermal stress while maintaining cooling efficiency.

A sleeve creates a flow passage around a torque probe, using bearing cavity fluid to cool components and maintain measurement precision in hot engine sections.

Segmenting the cooling channel with circumferential expansion joints absorbs thermal elongation differences, preventing blade ring deformation.

A gas turbine cooling system adjusts cooling air flow rate based on detected high-temperature portion readings.