Turbine/Propulsion Engine Cooling TRIZ Cases

A secondary oil fuel heat exchanger mounts in a bypass pipe to route flow through control valves, reducing head losses on oil recovery pumps.

A Z-shaped connecting member constrains cooling tube positioning within a turbine casing assembly.

Liquid water injection enables rapid power achievement before steam generation, resolving slow cold-start pressure limits.

A cooling air manifold splash plate redirects radial airflow circumferentially to distribute gas across turbine vanes.

Forward-facing cooling holes on the pressure side wall reduce mixing losses and maintain suction side tip temperatures in high lift airfoils.

Support pins stabilize angled ports during additive manufacturing, enabling precise impingement distance control for tight-to-reach spots.

A turbine cooling system mixes overcooled bleed air with direct flow to achieve uniform temperature.

Spaced-apart fins augment heat transfer via increased turbulence, reducing aerodynamic losses while maintaining compact engine weight.

Rotating impeller increases cooling fluid pressure within the turbine disc cavity, reducing pressure loss in blade passages.

Expansion turbine supplements drive shaft power by expanding cryogenic fuel, reducing storage weight and volume.

Dual-channel struts cool oil using bypass airflow and heated fluid, eliminating separate heat exchangers and reducing aerodynamic drag.

A cooling flow director channels radial air from the aft frame to shield the flexible sealing element from high temperature combustion gases.

Segmented baffle cavities direct cooling air to stator end walls and rotor shrouds, reducing total cooling air requirements.

A fuel-oil heat exchange system uses a control valve to direct engine oil flow between two separate heat exchangers for primary and secondary fuel lines.

Shaft-driven impeller pump circulates air through a heat exchanger to manage nose cone thermal loads, ensuring consistent heat rejection at idle conditions.

A gas turbine cooling valve modulates airflow through an offtake duct to manage primary and secondary flow paths.

Curved inner and outer plates form an arcuate heat exchanger that reduces airflow turbulence and pressure drops while cooling lubrication fluids.

A combined cycle power plant recycles turbine cooling medium to preheat fuel via a counter-flow heat exchanger.

A gas turbine vane incorporates a purge flow interface with a pocket to reduce gas leakage and delay oxidation at mateface locations.

Dual heat exchangers manage fuel temperature and sulphur content, resolving trade-offs between combustion efficiency and thermal stability.

A fan-driven inlet guide vane draw heat exchanger system circulates cooling air through a supply passage using pressure differentials.

Heat exchange system raises fuel temperature to at least 135°C for combustor entry.

Recovering stator blade coolant and merging it upstream reduces enthalpy loss in high temperature CO2 turbines.

Elevated pump assembly prevents liquid ingestion by utilizing natural convection, thereby enhancing gas turbine reliability and durability.

A compliant shroud expands radially using pressurized fluid to adjust blade tip clearances in gas turbine engines.

Segmented pressure and suction side channels eliminate pin bank thermal conduction paths, reducing peak stresses and improving airfoil durability.

A variable blower adjusts thermal fluid flow through a distribution manifold to control turbine tip clearance.

FADEC-controlled auxiliary fan initiates cooling airflow before shutdown to prevent thermal soak-back damage to electronic components.

A heat exchanger modifies compressor bleed air temperature using a fluid supply system to optimize thermal conditions within the turbine engine assembly.

Pedestal turbulators enhance convective heat transfer within gas turbine cooling passages, reducing required cooling flow rates.

A reverse core flow gas turbine engine uses a 180-degree duct to redirect airflow through concentric spools and a geared fan for high efficiency.

Segmented heat exchangers transfer heat through a thermally neutral fluid loop that matches system pressures.

A thermal management system recirculates heat from lubricated components using a neutral fluid to optimize engine performance.

Internal protrusions in turbine blade cooling passages increase heat transfer area, reducing pressure loss and cooling medium consumption.

A variable eductor mixes ambient air into exhaust streams to reduce thermal stress on HRSG components during startup.

A perforated structure in thermal contact with a hot fluid circuit cools lubrication oil while warming the air inlet sleeve.

Integrating a heat exchanger into the fuel path eliminates heavy air-to-air units, reducing weight while recovering waste heat to improve engine efficiency.

A fluid exchange apparatus with interleaved pathways directs separate streams through distinct passages to manage thermal energy distribution.

Radial cooling air flowpath merges heat exchangers into the outer casing to reduce core diameter while maintaining thermal management.

Integrating heat exchanger tubing within the exhaust assembly reduces backpressure losses while preheating liquid hydrogen fuel for efficient combustion.

A static mixer cools turbine extraction gas with compressor air, boosting steam production while reducing wasteful power generation.

Partition ribs divide the shroud into independent cavities, reducing cooling air consumption while maintaining blade temperature control.

A radially-extending rib in a gas turbine seal segment decreases the pressure loading moment arm, reducing stress on the seal material under high thermal loads.

A fluid cooler uses helically extending inner tubes to increase effective heat transfer length within a compact outer tube volume.

Closed cycle turbine extracts energy from a fluid coolant to intercool compressed air, reducing ducting complexity and weight while boosting engine efficiency.

An internal cooling channel within a full-hoop blade track isolates coolant flow to maintain optimal tip clearance and prevent hot gas ingestion.

Segmented cooling passages with divergent exits route thermal fluid to improve heat transfer efficiency while managing device complexity.

Segmenting the manifold cavity directs cold air across inner case flanges while isolating hot air, reducing thermal gradients and extending component life.

Merging separate units into one device reduces system complexity and weight while optimizing temperature control for aircraft engine operations.