Turbine/Propulsion Engine Cooling TRIZ Cases

A film cooling hole with side and layback diffusion portions controls coolant flow angles for stable coverage.

A bore tube directs cooling airflow through an annular passage within the inner shaft, reducing temperature and preventing material degradation.

Rotor centering cooling system reduces thermal gradients between top and bottom struts to maintain exhaust bearing body centering.

An airfoil leading edge trough creates a vortex that limits bow wave upstream extent, preventing hot gas ingestion into temperature-sensitive cavities.

Segmented baffles with radial gaps protect composite casings from thermal damage without restricting auxiliary equipment cooling.

Variable frequency drive controller regulates electric oil pump torque and speed independent of engine rotation to maintain cooling during low-speed operations.

Baffle plates in the mixing chamber redirect cooling flows to generate swirl, reducing pressure losses and improving heat transfer in turbine wheel spaces.

Independent pressurizing means supplies heated air to expand turbine clearances, reducing startup time and preventing cat back during shutdown.

A gas turbine cooling system uses a heat exchanger and valve assembly to manage air pressure and temperature.

Separate cooling conduits bypass complex combustor paths, reducing pressure loss while maintaining reliable turbine component cooling.

A fluid-driven propeller increases bleed air flow through a pre-cooler, resolving insufficient cooling capacity in undersized units.

Circumferential air scoops divert bypass airflow through fairings to cool the outer ring, reducing thermal stress without sacrificing engine cycle efficiency.

Power strut cooling system directs air through internal passages and external heat exchange units to stabilize turbine components.

Selective clutch engagement drives the boost compressor to raise pressure for turbine cooling while recapturing energy.

An ejector taps compressor air to augment airflow across an air oil cooler, reducing heat exchanger weight while maintaining cooling at low power.

Buffer cooling system conditions bleed airflow via heat exchange to deliver thermal management to critical engine components.

Intercooler heat recovery preheats steam generator feedwater, reducing water consumption and eliminating visible exhaust plumes.

Extracting a generator to the nose cone eliminates complex cooling systems required near exhaust gases while maintaining efficient thermal isolation.

A gas turbine clearance control system adjusts cooling medium flow rates to manage stationary part dimensions during operation.

A compact multi-pass heat exchanger uses counter-flow coolant direction and herringbone channels to enhance thermal transfer efficiency.

Segmented airfoil cavities reduce pressure losses from serpentine flow direction changes, enhancing engine efficiency.

A diffuser case strut flow system mixes cooled air with secondary airflow to cool compressor rims.

Segmented ceramic airfoils use refractory interlayers to resolve fabrication complexity and reproducibility issues in turbomachine manufacturing.

Nested air cycle machine driven by engine rotor generates high-pressure cooled air, eliminating bulky external units and freeing under-cowl installation space.

Integrating the heat exchanger within the gearbox housing reduces packaging space and installation complexity while maintaining effective thermal management.

Deformations in layered bounding walls create cooling-air outlet orifices, reducing weight and manufacturing complexity compared to cast parts.

A pulsating heat pipe transfers thermal energy between a turbomachine fluid circuit and an acoustic noise-attenuation structure.

Limiting the turbine inlet to compressor exit temperature ratio to 1.85 eliminates compressor air bleeding for cooling, preserving engine efficiency.

Pre-heating turbine discs reduces thermal stress gradients during rapid engine acceleration, extending component service life.

Segmented spools decouple compressor speed from load requirements, reducing fuel consumption while maintaining synchronous drive capability.

Partial ledges on the plate inner wall enable closer impingement hole placement, reducing thickness and improving heat transfer in hard-to-cool regions.

A nose cone pump drives airflow through a heat exchanger to manage thermal energy and prevent ice formation during idle conditions.

Heat exchangers use superalloys with gamma-prime intermetallic phases to maintain cooling performance despite high pressure ratios.

Centrifugal separator extracts particles from cooling air, preventing blade clogging and extending operational time.

A turbine engine compartment unit integrates an intake muffler and gas filter device to manage air quality.

Compressed air heats liquid for injection while cooling turbine sections, improving power output and reducing nitrogen oxide emissions.

A preheater exchanges heat between superheated steam and fuel to raise combustion temperature.

Integral tubular sleeves in a turbine casing cooling device maintain constant air gaps, resolving non-uniform spacing issues that reduce cooling effectiveness.

Segmented baffles and nested passages resolve leading edge convective cooling limits in high-pressure turbine airfoils.

Bernoulli ejectors amplify compressed air to cool structural components, reducing thermal damage risks and material costs.

Pliable fin members in a gas turbine surface cooler flex to align with airflow, reducing pressure and friction losses across varying operating conditions.

Deriving firing temperature from cooling air mass flow compensates for adjustable cooling effects, resolving accuracy deviations in gas turbine operation.

Segmented brackets with rigid and resilient members offset thermal expansion forces while resisting high-frequency vibrations in gas turbine engines.

Lattice structures enhance thermal energy transfer and structural integrity in gas turbine components exposed to hot combustion gases.

A connecting tube passes through air-distribution casing sidewalls to eliminate overhanging connections that crack under vibration.

A controller moderates airflow through a fuel air heat exchanger to maintain fuel temperature below critical decomposition limits.

A turbine blade platform features a U-shaped channel and an impingement hole that directs cooling fluid onto the underside of the platform.

Segmenting the scroll cooling flow path via a dividing part distributes medium to inner and outer regions, reducing thermal stress on the turbine scroll.

Segmented impingement plates create localized high-pressure zones that cool thinner airfoils while minimizing gas-path flow losses.