Turbine/Propulsion Engine Cooling TRIZ Cases

A valve opening degree determination device calculates optimal cooling air supply based on operating states.

Non-steam-driven ejectors increase cooling airflow to reduce thermal energy waste and extend plant operational flexibility.

Intermediate air extraction cools vane rings to reduce tip clearance without adding external cooling equipment.

An integrated pressure sensor in a turbine vane flow port measures cooling air consumption to diagnose blockages and optimize engine performance.

Interstage cooling condenses vaporous oil into liquid droplets, enabling a two-stage centrifugal separation process that reduces aircraft engine oil loss.

A turbine diffuser energizes the boundary layer using high-pressure fluid injection to reduce pressure losses.

Multiple bleed ports and sensors divert airflow to specific turbine locations, reducing excessive cooling requirements.

Segmented cooling channels with widened return paths resolve insufficient fillet cooling in high-temperature rotary turbomachines.

A thermal management system circulates a thermally neutral heat transfer fluid through integrated heat exchangers to regulate engine component temperatures.

Segmented airflow paths and air curtains decouple tip clearance control from fire safety zones, maintaining extinguishing medium concentrations.

A turbine bucket tip plenum collects cooling fluid from internal passages and directs it toward the trailing edge for expulsion into the main flow path.

A downstream air compression impeller overcomes insufficient ventilation pressure in compact gas turbine engines.

A gas turbine oil tank integrates a heat exchanger to manage lubrication temperatures within the core compartment.

Segmented high and low pressure taps cool distinct turbine stages, resolving insufficient upstream cooling efficiency.

Varying tubular extension lengths optimize impingement flow, reducing thermal stress and metal temperature in high-speed gas turbines.

Segmented cooling air supply passages deliver targeted airflow to individual turbine disks for precise thermal management.

An inner manifold segregates compressor air from heated purge flow using tie-rods and distribution panels.

A multistage compressor cools air via a nitrogen circuit between stages to vaporize liquid natural gas.

A shielding member covers the disc and turbine blade gap using inclined guiding surfaces to adjust cooling fluid flow.

Pre-cooled bypass air regulates core compartment temperatures, preventing overheating when environmental controls are inactive.

An auxiliary rotation device uses an electric machine to slowly rotate a gas turbine rotor after shutdown, preventing thermal warpage and casing damage.

Dynamic valve positioning directs oil flow between circuits to maintain optimal fluid temperatures across idle, cruise, and takeoff conditions.

A cooled cooling air heat exchanger system manages compressed airflow through segmented elements to maintain thermal balance.

A turbine engine heat exchanger cools compressor bleed air using thermal transfer between booster and high-pressure compressor flows.

A heat exchanger cools and pressurizes compressor discharge air for engine sump assemblies.

Segmented ceramic panels on a gas turbine airfoil resist heat while reducing compressor bleed cooling needs.

Separate cooling circuit reduces thermal impact on core flowpath, improving operational efficiency.

Merging the lubrication pump into the starter-generator housing reduces system weight, cost, and complexity while ensuring reliable oil scavenging.

A coaxial fan electrical machine uses a C-shaped annular member to integrate the stator and bearing support.

A variable core cowl vent nozzle system adjusts the vent area to optimize airflow and thrust generation across different flight conditions.

A segmented heat exchanger arrangement increases cold-side frontal area to improve cooling capacity within gas turbine engine passages.

A combined power generation system utilizes turbine cooling air and waste heat to improve energy efficiency.

Segmented heat-exchangers lower bleed air temperature to eliminate Over Heat Detection Systems, reducing system weight and complexity.

A gas turbine control device adjusts a cooler side valve opening degree based on disk cavity ambient temperature measurements.

Decoupling separable plugs at threshold temperatures directs cooling fluid only to spalled regions, preventing unnecessary overcooling of intact areas.

Merging separate lubrication circuits prevents fluid congealing at subzero temperatures while reducing weight.

A turbine cooling plenum directs air through a mini-disk to the inner bore.

A gas turbine control computer adjusts a bleed valve opening based on fuel and cooling air state measurements.

Partial ribs within turbine airfoil cooling chambers distribute cooling flow and provide structural support, reducing panel bulge and vibration.

Variable speed discharge pumps maintain temperature stratification in chilled water storage tanks during gas turbine inlet air cooling operations.

A heat exchanger placed at engine case joints inhibits airflow through gaps using thermal expansion.

Clocking stator blades guides wake flow to downstream leading edges, reducing pressure variations in axial cavities without sealing air leakage.

A controllable baffle vane directs airflow within gas turbine enclosures to optimize cooling distribution across varying ambient conditions.

An insert with a flow discourager prevents cooling air from passing over internal ribs, reducing thermal stress and enabling high-temperature materials.

Segmented coolant passages isolate transmission flow from heat transfer, preventing coolant overheating during core path transit.

Pedestals and turbulator strips create turbulent mixing to increase heat transfer efficiency while reducing required cooling fluid volume.

Segmented plenum channels maintain high cooling air velocity at the turbine airfoil tip, resolving the trade-off between coverage area and flow speed.