Methods and apparatus for delivering cooling air within gas turbines
AssigneeGeneral Electric Company
InventorsGary Charles Liotta, Robert Francis Manning, Robert John Parks
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Abstract
A gas turbine engine includes a compressor rotor assembly which directs air at a sufficient pressure and temperature to a downstream turbine for cooling. The compressor assembly includes a compressor including an impeller and a cooling circuit. The impeller includes an exit, an inlet, and a body extending therebetween. The impeller body includes a first opening positioned a distance from the impeller exit. The cooling circuit extends between the compressor and the turbine and is in flow communication with the impeller opening.
Claims20
A method of cooling a gas turbine engine with compressor bleed air, the engine including a compressor rotor assembly and a turbine each rotatably coupled to a rotor shaft, the compressor rotor assembly including a centrifugal compressor and a cooling circuit, the centrifugal compressor including an impeller body and an impeller shroud, the centrifugal compressor including an inlet, an exit, and a hub extending therebetween, the impeller body including an opening disposed a distance from the impeller exit, the cooling circuit in flow communication with the impeller opening, said method comprising the steps of:
- operating the gas turbine engine;
- and
- cooling the turbine with pre-swirled bleed air supplied to the turbine from the compressor rotor assembly cooling circuit, the compressor rotor assembly cooling circuit in flow communication with the compressor rotor assembly impeller opening disposed a distance from the impeller exit wherein at least a portion of the bleed air is directed upstream axially towards the turbine.
A compressor assembly for a gas turbine engine, the gas turbine engine including a turbine disposed downstream from said compressor assembly, said compressor assembly comprising:
- an impeller comprising an exit, an inlet, and a body extending therebetween, said impeller body comprising a first opening disposed a distance from said impeller exit;
- and
- a cooling circuit in flow communication with said impeller opening, said cooling circuit configured to deliver pre-swirled bleed air from said impeller first opening to the turbine wherein at least a portion of the bleed air is directed upstream axially towards the turbine.
A rotor assembly for a gas turbine engine, said assembly comprising:
- a first rotor;
- a cooling circuit;
- a second rotor comprising an impeller comprising an exit, an inlet, and a body extending therebetween, said impeller body comprising a first opening disposed a distance from said impeller exit, said cooling circuit in flow communication with said impeller first opening and said first rotor, said cooling circuit configured to deliver pre-swirled bleed air from said second rotor impeller first opening to said first rotor wherein at least a portion of the bleed air is directed upstream axially towards said first rotor.
Dependencies are inferred from the claim text.