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.