Gas turbine thermal control and related method

Thermal control is provided for a gas turbine (110) casing by supplying thermal control gas from a compressor (112) to a space between an outer casing (123) and an inner casing (121), and transferring the thermal control gas from the space through the opening in the inner casing (121) via a pluralit...

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Bibliographische Detailangaben
Hauptverfasser:	Danescu, Radu Ioan, Johnson, David Martin, Black, Kenneth Damon, Casavant, Matthew Stephen
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:	Thermal control is provided for a gas turbine (110) casing by supplying thermal control gas from a compressor (112) to a space between an outer casing (123) and an inner casing (121), and transferring the thermal control gas from the space through the opening in the inner casing (121) via a plurality of holes (144) defined through a plate (140) attached to an outer surface of the inner casing (121). The holes (144) are arranged with a predetermined non-uniform distribution corresponding to a desired preferential impingement pattern for providing non-uniform heat transfer. A gas turbine thermal control assembly includes structure providing preferential heat transfer from the inner casing (121) during operation of the gas turbine (110) via a thermal control gas flow path (190) from radially outside of the inner casing into the interior of the gas turbine (110).