Cooling arrangement for a gas turbine engine and corresponding gas turbine engine

A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel (30) for air flow from a compressor, a first cooling channel (44) and at least one aperture (40) providing communication between the flow of air through the discharge channel (30) and the first cool...

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Bibliographische Detailangaben
Hauptverfasser:	SAHA, RAJARSHI, BOMMANAKATTE, HARISH, GUMPINA, KRISHNA KISHORE, JHA, SANJEEV, PEMMI, BHASKAR, GIRI, SHEO NARAIN, DONKADA, SANTHOSH
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel (30) for air flow from a compressor, a first cooling channel (44) and at least one aperture (40) providing communication between the flow of air through the discharge channel (30) and the first cooling channel (44). A restrictor device (42) in the aperture (40) regulates the flow of air between the discharge channel (30) and the first cooling channel (44). The restrictor device (42) deforms to vary air flowing through the aperture (40) in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device (42) responding to regulate the flow of air based on that temperature. The restrictor device (42) may be a two-way shape memory alloy.