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US 9,803,864 B2Granted
Turbine air flow conditioner
AssigneeGeneral Electric Company
InventorsArjun Singh, Chandrasekhar Pushkaran, Nishant Govindbhai Parsania
Life of this patent
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Abstract
A turbine combustor section has a flow conditioner including a plurality of conduits arranged to convey pressurized air to an air chamber for entrance into a plurality of fuel nozzles. Each conduit includes an inlet configured to receive the pressurized air from an annular passage and an outlet configured to deliver the pressurized air to the air chamber. A cross-sectional area of each conduit varies between the inlet and the outlet so as to reduce a pressure drop across the flow conditioner.
Claims22
A system for a gas turbine, comprising:
- a turbine combustor section, including:
- a plurality of fuel nozzles to distribute an air-fuel mixture in the turbine combustor section;
- an annular passage to convey pressurized air;
- an air chamber arranged to deliver the pressurized air to the plurality of fuel nozzles;
- and
- a flow conditioner disposed in a head end region of the turbine combustor section and having an arc shape corresponding to the annular passage, the flow conditioner including a plurality of conduits arranged to convey the pressurized air, the plurality of conduits including a radially inner row of conduits and a radially outer row of conduits concentrically arranged with respect to one another, each conduit including an inlet configured to receive the pressurized air from the annular passage and an outlet configured to deliver the pressurized air to the air chamber for entrance into the plurality of fuel nozzles,
- wherein each conduit has a tubular configuration adapted to extend between the annular passage and the air chamber, and
- wherein each conduit has a first portion having a first cross-sectional area and a second portion having a second cross-sectional area, the first cross-sectional area being smaller than the second cross-sectional area so as to reduce a size of a recirculation zone of the pressurized air in the air chamber.
5 more elements
A system for a gas turbine, comprising:
- a turbine combustor section, including:
- a plurality of fuel nozzles to distribute an air-fuel mixture in the turbine combustor section;
- an annular passage to convey pressurized air;
- an air chamber arranged to deliver the pressurized air to the plurality of fuel nozzles;
- and
- a flow conditioner disposed in a head end region of the turbine combustor section and having an arc shape corresponding to the annular passage, the flow conditioner including a plurality of conduits arranged to convey the pressurized air, the plurality of conduits including a radially inner row of conduits and a radially outer row of conduits concentrically arranged with respect to one another, each conduit including an inlet configured to receive the pressurized air from the annular passage and an outlet configured to deliver the pressurized air to the air chamber for entrance into the plurality of fuel nozzles,
- wherein a cross-sectional area of each conduit varies between the inlet and the outlet so as to reduce a pressure drop across the flow conditioner.
4 more elements
Dependencies are inferred from the claim text.