Turbine/Propulsion Engine Cooling TRIZ Cases

Accessory gearbox heat exchangers apply a specific capacity range to resolve the contradiction between compact volume and high heat duty processing.

A flow diverter redirects cooling air from radial to axial paths through cylindrical vents in gas turbine air separators.

Integrated heat exchanger generates thermal gradient to stabilize boundary-layer airflow and prevent ice formation in geared architecture gas turbine engines.

Recessed areas in a gas turbine core assembly enable secure insert placement and straightforward adhesive extraction during manufacturing.

Integrating an air-oil heat exchanger into the separator nozzle minimizes aerodynamic drag while cooling oil and preventing nozzle icing.

Electroforming creates a monolithic heat exchanger with tailored material zones, reducing structural complexity while maintaining high heat transfer efficiency.

Position-linked valves modulate cooling fluid flow to exhaust liners, preventing overheating while conserving supply.

Segmented bypass pipes with temperature-controlled valves lower overpressure in frozen oil circuits without expanding component cross-sections.

Radially extending fins augment heat transfer from conduits to bypass airflow, resolving thermal efficiency limits within constrained engine volumes.

Segmented tooling reduces production time and design change delays for curved composite panels.

Emergency oil tank positioned above radial bearings enables gravity-fed lubrication, eliminating long supply lines that increase complexity and cost.

A turbine blade tip protrusion directs cooling fluid through exit holes, preventing hot combustion gas from invading the internal cooling passage.

A hybrid cooling system for gas turbine engines combines cooled air and vapor cycles to manage component temperatures.

LAPS system adjusts gaseous air mass flow to match turbine load, resolving efficiency losses from renewable intermittency.

A bleed air cooling system uses delta-pressure valves to route airflow from compressor ports to turbine sections.

Redirects cooler compressor extraction fluid to the exhaust stream during startup operations.

A buffer cooling system directs conditioned airflow through a mid-turbine frame passageway to protect hardware from high operating temperatures.

An aircraft propulsion ventilation regulator adjusts airflow passage sections to maintain equipment cooling under normal conditions.

Internal plenum merges external pipes into single manifold, reducing part count and leakage risk while lowering thermal stress.

Separate air intake supplies cooling medium to the heat exchanger, avoiding specific thrust reduction and surge margin loss caused by compressor offtakes.

Bushing adapter accommodates differential thermal expansion to prevent stress failure while providing dedicated cooling airflow paths.

A turbocharger outer housing welded to a bearing flange via a peripheral web with a widened base section reduces temperature gradients at the connection area.

A fuel temperature control system uses sensors and a controller to adjust heating at the nozzle inlet.

A turbine blade varies thermal barrier coating thickness from leading edge to trailing edge to alleviate suction side deceleration gradients.

Varying cooling passage pitch and area along the axial direction reduces excessive cooling air loss into the combustion gas, enhancing thermal efficiency.

Integrating cooling channels into discharge duct fins merges thermal management with debris ejection, reducing aerodynamic losses in turbojet engines.

Heat pipe tubes link acoustic attenuation structures to exchangers, preserving fan duct wall area and reducing aerodynamic drag.

Oil tank structural walls feature immersed protrusions and exterior fins to transfer heat between oil and ambient air.

Low-friction wear materials and spring-loaded isolator sheets in forward and aft brackets allow thermal expansion while damping high cycle fatigue.

Removable shims adjust the outer cowl position relative to the bypass inner wall in gas turbine engines.

A flow path forming plate uses tapered side passages to direct cooling air toward gas path surfaces.

A stagnant air gap between cooling tubes and stator walls reduces heat pickup, maintaining lower air temperatures to improve cycle efficiency.

A multi-fluid heat exchanger cools motive fluids using air flow through integrated vanes and manifolds.

An electrically-driven air mover introduces auxiliary air into a ram-air duct to augment mass flow and enhance convective heat exchange.

Precoolers reduce bleed air temperature, allowing less cooling air usage to maintain turbine thermal protection while preserving engine efficiency.

A barrier chamber in a fuel heat exchanger prevents air-fuel mixing during thermal transfer, resolving safety risks from high operating temperatures.

Phase change material in a gas turbine rotor cavity absorbs thermal energy to reduce stress and enable higher compression ratios.

Shaped diffusion exit holes at 30 to 60 degrees prevent coolant blow-off at the leading edge, maintaining effectiveness despite small radius curvature.

A coupling device transmits motive power from a rotating power turbine shaft to an oil cooling fan during flight operation.

Movable turbulence generators on inter-vane walls enhance heat exchange efficiency while minimizing pressure losses caused by protruding air-cooled oil coolers.

Coned washer preload accommodates thermal growth in bypass air conduit, reducing low cycle fatigue stresses on turbine engine components.

Resilient fingers apply opposing forces to mount surface coolers, reducing component weight and mounting complexity without exhausting available space.

Internal flow passage directs cooling air between nozzle panel and fairing to reduce thermal stress on aircraft propulsion components.

Segmented internal cavities with tailored pressure regulation mimic exit pressure along the radial span, reducing excess cooling flow.

A boost compressor raises pressure of the third air flow path to match exhaust nozzle levels, enabling high thrust generation and cooling.

Tortuous strut passages cool compressor air, resolving insufficient turbine temperature control.

A bleed air cooling system uses strategically located ports and ducts to deliver targeted airflow for turbine section temperature management.

Tapered leading edge assemblies use vapor chambers and phase change materials to absorb thermal energy, reducing mechanical stresses during hypersonic flight.