Turbine/Propulsion Engine Cooling TRIZ Cases

Centrifugal fan moves cooling air through turbine blade passageways during non-working cycles, reducing exhaust temperature and enabling lower-cost materials.

A controller adjusts coolant flow through an exhaust conduit to manage gas temperature entering a heat recovery steam generator.

Communication holes in the outer cooling passage redirect cooling air flow to eliminate stagnation zones downstream of struts.

An integrated air-to-air cooler uses an ejector to drive cooling airflow through a compact heat exchanger matrix.

Self-contained gas turbine drives cooling pumps, eliminating complex electrical systems and diesel maintenance during reactor outages.

A helical deflector creates a swirling cooling air flowpath to reduce thermal gradients and mechanical distortion in gas turbine engines.

A low pressure compressor compartment directs fan bypass airflow to cool electrical components.

A turbine blade cooling structure straightens vortex flow via a flat surface portion, preventing mixing with high-temperature gas and improving film cooling.

A cooling steam supply portion directs pressurized steam from superheater stages to the high-pressure turbine rotor.

Segmented bevel gears distribute core engine power to multiple fan rotors, resolving transmission complexity while improving bypass ratio.

Deoxygenized fuel absorbs heat from compressor bleed air to cool turbine components, preventing coke formation and extending engine life.

Segmented fractal branching distributes thermal gradients to alleviate mechanical stresses and extend service life.

An ejector section draws bypass air into a motive flow within a cooling conduit, reducing pipe size and eliminating flow perturbations.

A gas turbine vane shroud uses circumferential blowout passages to cool the central region.

Concave joint surfaces on the support member engage convex lobe surfaces to absorb thermal and radial displacements while reducing vibrations.

Circumferential channels and elastomeric mounts allow an aluminum fluid cooler to slide within a titanium engine case, eliminating thermal stress.

A turbine engine fuel system uses a steam loop to recover waste heat from combustion gases.

A plate fin heat exchanger uses a barrier with void space to isolate hot fluid passages and reduce direct heat conduction.

A supplemental airflow fan directs ambient air over an oil cooler heat exchanger to prevent overheating during low turbo fan operation.

Relocating cooling air supply paths to the outer casing eliminates center shaft tubes, boosting compressor and turbine aerodynamic efficiency.

Widening the retainer opening reduces rigidity at the inner shroud, suppressing thermal stress and improving durability.

Dual cooling system enables flexible gas turbine operation in simple cycle mode without water infrastructure.

Varying impingement hole density meters coolant flow to separate airfoil zones, reducing thermal resistance without increasing sidewall thickness.

Auxiliary compressor unit compresses air cooled by a dual pass heat exchanger to deliver high pressure cooling flow for turbine sections.

Upstream fluid injection cools compressed air, enabling higher overall pressure ratios without exceeding material temperature limits.

A turbine blade outer air seal divides internal cavities using partial restrictions to create distinct pressure zones for cooling air.

Bleed air system tailors pressure and temperature to reduce fuel consumption.

A turbine engine cooling system injects consumable liquid to protect components from thermal damage.

A variable motive nozzle ejector adjusts its primary nozzle area via a movable ram to mix compressor bleed air with secondary flow.

Intermediate carrier buffers thermal stress between metallic and ceramic components while impingement tubes cool the blade track segment.

Segmented double wall inlet duct structure with plenum channels mitigates icing and preserves aerodynamic symmetry without distorting geometry.

Unified casing supports turbine and compressor units to prevent shaft misalignment caused by differential thermal expansion.

Planar hot part cooling flow path uses outer peripheral surface turbulators to increase air velocity and heat transfer.

Integral diffuser walls and staggered fins reduce pressure losses in high-velocity gas turbine engines.

Hollow radial arms channel secondary gas flow to cool power turbine and mechanical transmission components in non-faired propeller turbo-engines.

Zone-based thermal delivery maintains equal temperatures across critical components, preventing rotor bends and clearance changes during turbine shutdown.

A movable valve regulates cooling airflow to a gas turbine heat exchanger compartment.

A movable door directs fan air through a heat exchanger to cool turbine cooling air, reducing parasitic engine losses by adjusting flow based on demand.

Pressurized tank releases cryogenic fluid through an expansion valve to cool the gas turbine engine during shutdown, preventing thermal soakback.

Independent combustion chambers adjust gas volume dynamically, preventing reservoir fracturing while maintaining stable extraction pressures.

A thermal management system integrates heat exchangers within a common plenum in the bypass flow path to reduce weight and ducting complexity.

A tangential on-board injector directs cooling air parallel to a rotating disk-hub surface.

A fluid-filled conduit surrounds an electric probe body to thermally insulate the sensor from high ambient temperatures.

Pedestals direct coolant airflow through turbine blade trailing edge exits, reducing mixing losses between cooling and mainstream streams.

Segmented cooling tubes and radial grooves prevent air stagnation in turbomachine casings.

A protruding guard part on a gas turbine casing restrains the heat insulating material from shifting outward.