Turbine/Propulsion Engine Cooling TRIZ Cases

A bypass pipe connects steam pipes to maintain temperature during shutdown, reducing gas turbine restart time and moisture accumulation.

Segmented auxiliary compression systems supply high-pressure cooling air to gas turbine components, preserving combustion airflow and engine efficiency.

Serpentine core design channels cooling fluid through split pass inlets and multiple turns to resolve thermal stress challenges in rotary machine endwalls.

Tapered airfoil wall thickness accelerates cooling airflow through embedded passages to dissipate heat from thick solid sections where traditional methods fail.

Valve switching between fan air and compressor air paths reduces thermodynamic efficiency losses while minimizing thermal stress on engine components.

Microchannels in the aft frame main body connect to cooling channels that exhaust into a cooling annulus.

Merging the heat exchanger with the air intake reduces ducting complexity and resonance noise while maintaining thermodynamic efficiency.

Segmented flow path members direct cooling air between rotating shafts to mitigate windage heating while maintaining thrust balance.

A gas turbine rotor disc uses a rim cavity and airflow openings to thermally condition the cover plate.

A turbine airfoil uses internal partitions and a perforated plate to distribute cooling air through segmented passages.

Integral circulation duct channels within the nacelle fairing structure reduce aerodynamic drag and added mass while maintaining cooling efficiency.

An Organic Rankine Cycle system cools compressed air using a working fluid to generate power.

Centrifugal impeller on rotor disk draws ambient air to pressurize cooling channels, eliminating wasted compressor bleed air.

Full capacity valves adjust opening degrees based on real-time pressure measurements to ensure sufficient cooling flow across varying ambient temperatures.

Staged compression with intercooling delivers high-pressure cooled air, resolving insufficient pressure and temperature limits in gas turbine components.

Liquid injection on cooler fins absorbs heat via evaporation, reducing component weight while maintaining oil temperature during high-stress takeoff.

A turbomachine heat management system refreshes heated fluid streams using a bypass duct hatch to introduce cooler air between series heat exchangers.

A thermal transport bus circulates heat exchange fluid to transfer waste heat from accessory systems directly to engine surfaces.

Cryogenic fuel tank and vaporizer convert liquid LNG to gas, providing engine cooling that reduces specific fuel consumption and greenhouse gas emissions.

Multiple heat exchangers arranged in a partial-series configuration within the bypass flow bifurcation area reuse cooling air.

A diffuser case strut delivers conditioned air directly to compressor components via a dedicated radial passage.

A composite thermoelectric material integrates fibrous layers and conductive mesh within a matrix to enable active cooling in electronics enclosures.

Water injection nozzles route cooling air through ventilation conduits to reduce compressor bleed air demand and boost power output.

Segmented heat exchangers with auxiliary turbines reduce thermal stresses on components by maintaining small pressure differentials across stages.

A cooled cooling air system conditions rotor assemblies using a heat exchanger and tangential injection nozzle.

Segmented cooling paths and local quality principles reduce compressed air usage while maintaining blade temperature control.

Recess portion with angled side walls blocks acoustic propagation between combustors, reducing vibration and thermal stress during positional displacement.

Segmented circulation pumps and controllable valves adjust lubricant flow and temperature to optimize power gear box efficiency under varying conditions.

A bifurcated duct splits fan airstreams to cool lubricant, reducing back-pressure distortions and energy losses in the engine core compartment.

Segmented axial cooling flow passages with radial return channels prevent radial temperature distribution in gas turbine blade rings.

Segmenting cooling air into two paths bypasses combustor heat while maintaining rotor temperature control during heat exchanger failure.

An integrated heat exchanger assembly merges an ejector directly into the core structure to induce airflow without external fans.

Airfoil flow guide reduces pressure loss in aero engine bypass duct while maintaining heat transfer performance.

Turbulator rib fillets extend into the cooled wall to increase heat transfer while reducing pressure losses in gas turbine components.

Integrating a wicking heat pipe into flow bounding structures reduces weight and drag while preventing oil exposure to foreign objects.

A unitary thermal management manifold consolidates fuel and oil coolers into a single cast structure with integrated fluid passages.

A turbine engine taps bleed airflow upstream of the combustor, compresses it, and uses exhaust heat to drive an auxiliary compressor.

Turbine expansion cools bleed air for heat exchangers, preventing ice formation during thermal management.

A microchannel cooling system removes heat from a gas turbine electric device stator to maintain operating margins during peak power demand.

Counter-flow heat exchanger in aircraft fuel systems prevents ice formation by transferring waste heat from exhaust gases to cold fuel return lines.

Dividing fluid flow via a free-piston compressor cools the combustion chamber and turbine, resolving overheating risks while maintaining energy efficiency.

An annular heat exchanger merges with fan duct walls to maximize cooling fluid flow through radially layered channels.

A thermal transfer bus couples an air cycle machine heat exchanger to a fuel delivery system in a gas turbine engine assembly.

Inlet precooler uses a heat exchange system to cool supersonic airstreams, reducing shock wave thermal energy.

A lubrication pump controller adjusts oil flow rates relative to shaft speed for electric machine cooling.

A compressor-fed manifold cools turbine exhaust case struts, enabling lower-grade materials and reducing manufacturing costs.

Downstream throttle positioning eliminates complex duct transitions, reducing inlet pressure loss and flow distortion in gas turbine engines.

Segmented radial members create a tortuous path that reduces leakage and pressure distortion while enabling effective cooling.

Segmenting heat exchange into dedicated units cools extraction air and heats fuel via an intermediary water circuit.