Turbine/Propulsion Engine Cooling TRIZ Cases

Heat exchanger outer walls shield an overlapping area with a hydraulic fluid reservoir, reducing dead weight and manufacturing costs.

An angled access passage directs cooling fluid into a particle collection chamber, preventing blockages in hot gas path components.

Integrating a heat exchanger within the diffuser case cools bleed air via bypass flow, resolving thermal management complexity in gas turbine engines.

A turbine bearing chamber pressurization system supplies cold air from upstream of the low-pressure compressor to maintain lubrication integrity.

Trailing edge notches on inlet turning vanes mix pressure and suction side air streams to reduce total pressure loss in gas turbine bypass ducts.

Segmented heat exchanger by-passes balance pressure and temperature gradients, preventing flow reversals in gas turbine engines.

Parallel oil loops raise fuel temperature to 135°C while air cooling prevents coking risk.

Integrating a heat exchanger into the gas turbine cooling plenum lowers component temperatures, allowing smaller clearance gaps and improving engine efficiency.

A buffer system communicates conditioned cooling air to gas turbine engine shafts and bearing structures.

A heat exchanger system merges outlet guide vane units with surface coolers to expand cooling capacity.

Rear ducting relocates the heat exchanger exhaust downstream to eliminate upstream noise and performance penalties.

A boost compressor driven by a low spool shaft pressurizes cooling air to resolve insufficient pressure for high-pressure turbine components.

A platform cooling core circulates fluid through a gas turbine rotor blade to prevent hot gas ingestion at the mate face.

Segmented seals isolate the cooling plenum from primary flow path leakage, reducing thermal gradients and extending component lifespan.

A thermal storage system manages intercooler temperatures using a secondary cooler and heat exchange fluid to optimize gas turbine performance.

A fan casing cooler uses thermally sensitive fins that change shape to position itself within the airflow path.

A compressing device increases cabin air pressure within the conditioning system.

Segmented plates mounted radially in the annular bypass duct optimize heat transfer efficiency while managing limited space constraints.

Connecting the cooling ejector nozzle to the bleed system reduces duct count and mass while maintaining low-speed efficiency.

A temporary oil filter installs between the auxiliary pump and journal bearing to capture debris during engine startup.

Segmented cooling passages optimize flow velocity across distinct blade zones, reducing leakage flow and minimizing required cooling air supply.

A gas turbine cooling control device adjusts cooling air flow rate using a load change determination unit and command generation sections.

A control apparatus switches compressed air sources to supply exhaust-side bearings with seal air during gas turbine operation.

Recirculates exhaust gas to cool and seal turbine components, reducing thermal stress while managing emissions.

Coanda-based flow channels in an adaptive pre-swirler maintain optimal swirl ratios across varying operating conditions.

Segmented upstream and downstream air sources protect the heat exchanger from high temperatures while maintaining turbine cooling pressure.

Integrating an overexpanded supercritical CO2 loop with the primary gas turbine recovers waste heat, converting thermal loss into additional shaft work.

A heat exchange system uses a recirculation line and flow-rate adjustment unit to control refrigerant temperature entering the first heat exchanger.

Adjusting guide blade cooling outlet mass flow during part load stabilizes combustion and prevents thermal overloading.

Forced air convection removes heat from the load coupling, reducing thermal deformation and axial bearing loads without adding fan blades.

A hybrid propulsion engine uses a precooler to manage compressed air temperature, reducing oxidant mass requirements for single-stage-to-orbit vehicles.

Integrated printed board heat exchanger reduces shell housing temperature and turbine damage risk by merging cooling functions with structural containment.

Segmented fluid paths deliver cooled lubricant to specific components, resolving the trade-off between system complexity and effective thermal management.

Clutch-driven compressor segmentation delivers targeted cooling gas to prevent overheating and extend turbine life.

A modulated turbine cooling system adjusts airflow based on component health to optimize engine performance.

Segmented heat exchanger assembly with shroud directs airflow for efficient cooling while enabling easy maintenance through a dedicated access panel.

A pressure-responsive closure system regulates gas flow through an aircraft engine heat exchanger duct.

Nickel plating on a polymer substrate resolves the trade-off between lightweight construction and fire resistance in gas turbine engine ducts.

A turbine rotor compartment uses a sealed plenum to distribute cooling air uniformly, eliminating thermal gradients that compromise component longevity.

Introducing a secondary working fluid buffers the generator rotor, reducing windage losses and pumping power while maintaining efficient heat removal.

A radial pathway connects turbine blade and platform cooling circuits, reducing stress concentrations from circumferential holes.

Segmented outlet slots distribute cooling fluid evenly within the mid-turbine frame, preventing impingement and maintaining minimal pressure drop.

Integrating an oil reservoir and heat exchanger into the engine frame protects components from debris while reducing weight.

Varying back channel opening density across blade regions reduces total cooling air flow while maintaining durability against high-temperature combustion gas.

Segmented axial skin core cooling passages absorb surface heat via convection, maintaining coolant pressure and preventing internal flow losses.

Axial thermal regulation channels direct coolant flow through radial passages to effuse into the gas path at aerodynamically favorable locations.

A heat exchanger positioned within a bifurcation duct cools compressed air using bypass flow.

Measuring rotor-casing clearance allows the control system to vary parameter change rates, preventing contact damage while maintaining rapid response times.