Turbine/Propulsion Engine Cooling TRIZ Cases

Temperature sensors trigger variable frequency drives to modulate fan speeds, reducing energy consumption during low thermal demand.

Merges the heat exchanger with the sump structure to reduce footprint area while maintaining heat transfer effectiveness for lubrication oil.

A turbine engine cooling system routes bleed air through a heat exchanger to condition airflow for component thermal management.

Pneumatic actuators move a door to control flow through a heat exchanger, resolving the trade-off between adaptability and device complexity.

Level detectors monitor coolant accumulation in a fuel-gas cooler and trigger pump shutdown to prevent overflow damage to compressors.

A coolant circuit vaporizes fluid to absorb heat from a power converter during engine start.

A disc shaft center adjusting mechanism regulates cooling air flow through struts using sensors and flow rate adjustors.

A multi-bypass gas turbine engine uses a stepwise area increase in the first bypass flow path housing to define a component placement cavity.

Shield plate with multi-directional cooling passages directs air to form a protective barrier, blocking high-pressure gas leakage between segments.

A perforated wall structure with intermediate pipes integrates acoustic attenuation and thermal exchange functions.

Segmenting air supply with a subsidiary compressor reduces engine off-take while maintaining cabin pressurization and de-icing performance.

Bi-directional strut flow passages direct cooling air between inner and outer exhaust structures, reducing thermal stress on bearings.

Separate circuits with dedicated heat exchangers resolve thermal load contradictions between gear trains and bearings.

A tangential on-board injector uses a purge cavity to remove particles from airflow.

A humid air turbine power plant uses adjustable valves to switch coolant between compressed and humidified air streams for high-temperature components.

Pedestal structures optimize internal cooling passages to reduce thermal fatigue while maintaining engine efficiency.

Radial liquid cooling removes heat from the inner rotor and support, managing high temperatures within the gas turbine core.

Basalt and carbon fiber layers in a cyanate-ester matrix replace titanium covers to withstand 250°C temperatures while reducing fatigue sensitivity.

A cooling flow channel guides lower-temperature air along a strut to cool the bearing periphery within a gas turbine exhaust section.

A flow control assembly directs cooler compressor air to turbine blades using an orifice and meter device.

A flow guide creates an axial passage between a blade outer air seal segment and its support structure to direct cooling air.

A particle separator diverts fluid flow through a diversion passage to remove contaminants from turbomachine cooling air.

Tapping cooling air upstream and boosting its pressure avoids energy waste from fully compressing air, improving delivery efficiency.

Interdigitated fingers biased by an outer spring clip provide dynamic damping to resist thermal expansion stresses in gas turbine engines.

Segmented airflow paths cool discharge air via intermediary posts, reducing pre-discharged heating in gas turbine components.

A gas turbine control method adjusts air intake valve opening degrees to maintain consistent operation conditions after component upgrades.

Segmented inner and outer bands use interstitial cooling channels to direct coolant along gas side surfaces.

A control system adjusts the backflow margin pressure ratio using a scalar based on fired hours to manage bleed air flow.

A buffer system selects between dual bleed air supplies to maintain bearing compartment pressurization.

Closed cooling circuits utilize LNG vaporization cold energy to chill gas turbine inlet air, reducing wasted heat in steam turbine condensers.

An annular mount channels secondary air through impingement holes to cool critical components.

Segmenting oil flow through parallel-serial fan outlet guide vanes reduces pressure drop while maintaining cooling capacity.

A shroud assembly particle separator diverts cooling fluid through a virtual impactor to extract particulate matter from the flow stream.

Protrusions on gas turbine heat sinks direct cooling air to enhance thermal transfer while serving as integral part markers.

Segmented cooling holes reduce metal temperatures on gas turbine vanes, resolving thermal distress and complexity trade-offs.