High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
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United States of America Patent
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Jun 25, 2019
Grant Date -
Oct 27, 2016
app pub date -
Apr 21, 2015
filing date -
Apr 21, 2015
priority date (Note) -
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Abstract
An exhaust gas diffuser for a gas turbine engine whose inlet geometry can be selectively controlled to change the angular orientation of the diffuser at the location where the exhaust gas exits the last stage row of blades of the turbine section of the gas turbine engine. An end portion of the gas diffuser proximate the last stage row of blades can include one or more actuated sections that are independently controlled to change the angular orientation of the inlet geometry of the diffuser. In one embodiment, the angular orientation of the actuated sections is set at the manufacturing level for the service location of the engine. In another embodiment, the angular orientation of the actuated sections is selectively controlled based on the operating conditions of the engine. In another embodiment, the angular orientation of the actuated sections is controlled by pneumatic pressure from a compressor section of the engine.
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