Cyclonic dirt separating turbine accelerator
AssigneeGeneral Electric Company
InventorsRobert Francis Manning, Victor Hugo Silva Correia
Life of this patent
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Abstract
A dirt separator assembly for a gas turbine engine comprises a cyclonic accelerator in flow communication with compressor discharge air, the accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in the passage, a plurality of turning vanes disposed along each of the passages, the passage turning tangentially between the inlet and the outlet, the accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air, and, at least one vent located in the accelerator passages for expelling dust separated from the swirling compressed cooling air.
Claims23
A dirt separator assembly for a gas turbine engine having a compressor, a combustor, and a turbine in serial flow relation, comprising:
- a cyclonic accelerator in flow communication with compressor discharge air and located downstream of the compressor, said accelerator having a plurality of passages, each passage having an inlet, an outlet and at least one vent located in said passage;
- a plurality of turning vanes disposed along each of said passages, said plurality of turning vanes in said passages turning air in said passages tangentially between said inlet and said outlet;
- said accelerator passages decreasing from a first cross-sectional area to a second cross-sectional area and said turning vanes inducing helical swirl of compressed cooling air;
- and,
- said at least one vent located in an outer wall of said accelerator passage for expelling dust separated from said swirling compressed cooling air exiting the accelerator assn a throu h said at least one vent via rotational, tangential force and outward from an engine core of the gas turbine engine.
A dirt separator for a gas turbine engine, comprising:
- a cooling air flow path disposed in a turbine frame;
- an accelerator located in said frame portion, said accelerator in fluid communication with said cooling air flow path;
- a deflector extending over a cooling air aperture between said cooling air flow path and said accelerator, said deflector creating a tortuous path for cooling air passing from said cooling air duct to said accelerator;
- said accelerator having an accelerator passage including an inlet of a first cross-sectional area, an outlet of a second smaller cross-sectional area, and a plurality of turning vanes therein;
- and
- said accelerator passage including at least one vent located in an outer wall of said accelerator passage for removal of particulate from said passage through said vent via rotational, tangential force and outward from an engine core of the gas turbine engine.
A two stage particle separator for a gas turbine engine, comprising:
- a combustor wall and a combustor inner liner shell defining a substantially annular flow path;
- a deflector disposed in said substantially annular flow path and overlying an accelerator inlet. the deflector defining a tortious air path and forming a first stage particle separator with separated particles traveling through the combustor wall;
- an accelerator downstream of the deflector forming a second stage particle separator having said inlet and an outlet and changing from a larger cross-section at said inlet to a smaller cross-section at an outlet;
- said accelerator having an outer surface including at least one vent passing through said outer surface for expelling dust outward through said at least one vent via rotational, tangential force exiting the accelerator and outward from an engine core of the gas turbine engine.
Dependencies are inferred from the claim text.