Back to results
US 8,234,872 B2Granted
Turbine air flow conditioner
AssigneeGeneral Electric Company
InventorsJonathan Dwight Berry, Jason Thurman Stewart
Life of this patent
Estimating the term…
Abstract
A system includes an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor. The air flow conditioner comprises a perforated annular wall configured to direct an air flow in both an axial direction and a radial direction relative to an axis of the turbine combustor. In addition, the air flow conditioner is configured to uniformly supply the air flow into air inlets of one or more fuel nozzles.
Claims26
A system, comprising:
- a turbine engine, comprising:
- a combustor, comprising:
- a combustion chamber;
- a liner disposed about the combustion chamber;
- a sleeve disposed about the liner;
- an air supply path between the liner and the sleeve;
- an air chamber;
- a divider disposed axially between the combustion chamber and the air chamber relative to a longitudinal axis of the combustor;
- a fuel nozzle extending through the divider, wherein the fuel nozzle has an air inlet in the air chamber and an outlet in the combustion chamber;
- and
- an air flow conditioner disposed in the air chamber in line with the air supply path into the air chamber, wherein the air flow conditioner comprises a first perforated turning wall extending circumferentially about the longitudinal axis in a radially overlapping position relative to the air supply path, the first perforated turning wall comprises a first plurality of openings configured to pass a first portion of an air flow from the air supply path in an upstream direction away from the combustion chamber, and the first perforated turning wall is angled inwardly from the air flow path toward the longitudinal axis in the upstream direction to turn a second portion of the air flow from the air supply path inwardly toward a central region of the air chamber.
8 more elements
A system, comprising:
- an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor, wherein the air flow conditioner comprises a first perforated annular turning wall having a first plurality of openings, the first perforated annular turning wall is configured to radially overlap with an air supply path between a combustor liner and a flow sleeve of the turbine combustor, the first plurality of openings is configured to pass a first portion of an air flow from the air supply path in an upstream direction away from the combustion chamber, and the first perforated annular turning wall is angled inwardly from the air flow path toward a longitudinal axis of the turbine combustor in the upstream direction to turn a second portion of the air flow from the air supply path inwardly toward a central region of the air chamber, and the air flow conditioner is configured to distribute the air flow into air inlets of one or more fuel nozzles.
A system, comprising:
- a turbine combustor, comprising:
- a combustion chamber;
- a liner extending around the combustion chamber;
- a sleeve extending around the liner;
- an air supply path between the liner and the sleeve;
- and
- a head end upstream from the combustion chamber relative to a flow of combustion products, wherein the head end comprises:
- a fuel nozzle disposed in the head end;
- and
- an air flow conditioner disposed in the head end, wherein the air flow conditioner comprises a first perforated turning wall that radially overlaps the air supply path, the first perforated turning wall comprises a first plurality of openings, and the first perforated turning wall is angled inwardly from the air flow path toward a longitudinal axis of the turbine combustor in an upstream direction away from the combustion chamber.
7 more elements
A system, comprising:
- an air flow conditioner configured to mount in a head end air chamber of a turbine combustor in line with an air supply path radially between a combustor liner and a flow sleeve, wherein the air flow conditioner comprises a first perforated turning wall that radially overlaps the air supply path, the first perforated turning wall comprises a first plurality of openings, the first perforated turning wall is angled inwardly from the air flow path toward a longitudinal axis of the turbine combustor in an upstream direction away from a combustion chamber, a second perforated wall is disposed in a concentric arrangement relative to the first perforated turning wall and the longitudinal axis of the turbine combustor, and the first perforated turning wall is angled related to the second perforated wall.
Dependencies are inferred from the claim text.