Separators for use with gas turbine engines
AssigneeGeneral Electric Company
InventorsPradeep Hemant Sangli, Santosh Kumar Potnuru, Keith A. Miedema, Matthew D. Brothers, Ravindra Shankar Ganiger
Life of this patent
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Abstract
Separators for use with gas turbine engines are disclosed herein. An example cabin bleed system disclosed herein includes a bleed line coupled to a gas turbine engine, a separator defining a cavity fluidly coupled to the bleed line, the separator including a first ring including a first opening fluidly coupled to the cavity. a second ring surrounding the first ring, the second ring including a second opening fluidly coupled to a cabin of an aircraft, and a filter disposed in a fluid pathway extending between the first opening and the second opening.
Claims15
A cabin bleed system comprising:
- a bleed line coupled to a gas turbine engine;
- a separator defining a cavity fluidly coupled to the bleed line, the separator including:
- a first ring including a first opening fluidly coupled to the cavity;
- a second ring surrounding the first ring, the second ring including a second opening fluidly coupled to a cabin of an aircraft;
- a filter disposed in a fluid pathway extending between the first opening and the second opening;
- a shaft coupled to the separator;
- a motor coupled to the shaft, the motor to cause a rotation of the separator and the shaft, the rotation to cause a flow of fluid from the bleed line through the fluid pathway;
- and
- a particulate matter sensor disposed in the bleed line, the motor triggered based on an output of the particulate matter sensor.
A separator coupled to a bleed line of a gas turbine engine, the separator comprising:
- a first ring including a first opening fluidly coupled to a cavity, the cavity to be fluidly coupled to the bleed line;
- a second ring coupled to the first ring, the second ring outboard of the first ring;
- and
- a filter disposed between the first ring and the second ring, a rotation of the separator causing a bleed flow of the bleed line to flow through a fluid pathway including the filter, the filter configured to separate an air of the bleed flow from particulate matter of the bleed flow,
- wherein the first ring includes:
- an annular portion abutting the second ring;
- and
- a lip portion extending from the annular portion away from the second ring.
A separator coupled to a bleed line of a gas turbine engine, the separator comprising:
- a first ring including a first opening fluidly coupled to a cavity, the cavity to be fluidly coupled to the bleed line;
- a second ring coupled to the first ring, the second ring outboard of the first ring;
- a filter disposed between the first ring and the second ring, a rotation of the separator causing a bleed flow of the bleed line to flow through a fluid pathway including the filter, the filter configured to separate an air of the bleed flow from particulate matter of the bleed flow;
- and
- a piston seal on an outboard surface of the second ring.
An aircraft including:
- a cabin;
- a gas turbine engine including a bleed line, the bleed line configured to pressurize the cabin, the bleed line defining a bleed flow path;
- a shaft configured to rotate during operation of the aircraft;
- and
- a separator coupled to the shaft, the separator configured to separate a particulate matter from an airflow of the bleed line, the separator including:
- a first ring;
- a second ring coupled to the first ring, the bleed flow path flowing through an interior of the second ring;
- a filter in the interior;
- and
- a plurality of walls in the interior, the plurality of walls dividing the interior into a plurality of interior sections including a corresponding plurality of filters, the corresponding plurality of filters included in the interior.
Dependencies are inferred from the claim text.