Turbine/Propulsion Engine Cooling TRIZ Cases

Integrated housing passage merges with primary flowpath to cool the electric machine without adding weight or leakage risks.

A non-recirculating lubrication system delivers pressurized air and oil to gas turbine bearings for cooling and lubrication.

A turbine casing sleeve creates a cooling fluid passage to maintain mechanical strength of the inner structure.

Retaining plate with crimped nuts secures connecting sleeves, reducing securing parts and mounting complexity while maintaining axial blocking.

Segmenting the steam cycle with two working media reduces temperature difference losses, improving thermal efficiency while maintaining operational safety.

Segmented tip cooling holes discharge fluid to cool turbine blade tips, preventing thermal expansion damage that degrades gas turbine efficiency.

Pedestal arrays in the tip flag path increase heat transfer at the radially outer trailing edge, preventing spallation and burning.

Switching cooling air sources between compressor bleed and atmospheric intake maintains thermal efficiency during varying load operations.

Integrated mount ring routes air through structural ribs, reducing stress concentrations in small diameter core engines.

Partition walls isolate bearing cases from heated diffuser cooling air, preventing thermal transfer that degrades lubricating oil.

Actuator flap moves follower flap to adjust fan nozzle area and redirect exhaust flow for thrust reversal.

Segmenting the thermal bus into isolated loops prevents single-point failures while aggregating capacity for peak demands.

Engine gas pressurizes the fluid tank to inject water into operational engines, removing heavy redundant pumps and boosting power.

A gas turbine cooling air system routes high-pressure auxiliary flow through a connecting line to lower-pressure circuits.

A centrifugally actuated passive coolant valve modulates cooling air flow through turbine blade passages based on rotor speed.

A blade ring cooling system adjusts tip clearance using high-pressure bleed air and compressed air flows.

A drying air system supplies dry gas into the cooling air circuit to maintain low humidity levels during idle periods.

A turbomachine oil cooling device uses a flow regulator to divert oil through a bypass path when temperatures drop below 80°C.

A tapered plenum divider baffle maintains constant coolant velocity, preventing regional overheating of stator blades.

A combined cooling system uses a single heat exchanger to cool bleed air for both aircraft and engine subsystems, reducing oversized dedicated units.

A diverging curved ramp side wall creates lateral airflow swirl, eliminating pressure drops from deflectors in submerged intakes.

Connecting struts integrate air inlet openings and sealing barriers to cool turbine walls while maintaining bearing housing pressure.

A nose cone assembly circulates air through a frustoconical heat exchanger to cool fluids in gas turbine engines.

Electronic control unit adjusts gas turbine operating parameters based on component health to reduce fuel burn from worst-case design inefficiencies.

Suction device extracts residual working fluid from internal turbomachine areas, reducing thermal stress and energy consumption caused by high-velocity cooling.

An upstream inlet heat exchanger cools the incoming fluid stream using a separate medium before it reaches the core engine.

Merging heat exchanger with bypass duct fairing cools compressor air while maintaining aerodynamic efficiency.

A tapered exhaust distribution manifold with varying openings directs cooling airflow from a heat exchanger.

A swirler tube directs cooling airflow in a circumferential direction through the mid-turbine frame.

Branching a bypass line from an existing return path reduces construction costs while suppressing CO emissions during low-load operations.

A movable sealing mechanism adjusts the air inlet opening area to intercept fan duct airflow and redirect it into the engine passage.

A bypass conduit directs heat-exchanged buffer air around a bearing compartment to mix with turbine cooling air.

A turbine casing clearance system directs compressed air to thermally contract or expand the shell.

Switchable air system diverts compressor discharge to turbine inlet, varying semi-dimensional mass flow to reconcile high thrust with thermal efficiency.

A turbine seal uses an air supply conduit to move gas from a high pressure region toward the seal interface.

Centrifugal acceleration creates pressure differentials that prevent fuel backflow, maintaining mechanical balance while cooling the rotor.

Segmented internal pedestals optimize cooling airflow patterns and flow rates within gas turbine airfoils to manage high external heat loads.

Dynamic cooling air flow adjustment minimizes rotor-stator clearance gaps during gas turbine cool-down, reducing leakage losses while preventing blade rubbing.

A turbine cooling system circulates onboard fluid through heated components after engine shutdown to manage thermal deformation.

Spray nozzle atomizes pressurized water into mist along the main shaft, increasing thrust gas volume while reducing erosive effects on engine components.

A bypass duct heat exchanger uses a flow divider to create a sub-passage, improving cooling efficiency without increasing structural complexity.

Extracting bleed air from a lower compressor stage reduces energy waste in cooling and pressure regulation while eliminating atmospheric inlet complexity.

An intercooler transfers heat from engine waste fluids to pre-heat make-up water in a combined cycle system.

A tangential on-board injector uses a 90-degree inlet extension to direct airflow and separate particles from the gas stream.

Dual bleed air circuits with a dynamic controller pressurize bearing seals to maintain lubricant containment across varying power conditions.

Spent cooling steam transfers thermal energy to compressor discharge air through a dedicated heat exchanger unit.

A stabilizing heat exchanger system regulates cooling air flow to maintain fuel within a stable thermal region.

Profiled walls guide and accelerate air flow through turbomachine heat exchanger fins, reducing pressure losses while maintaining effective oil cooling.