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US 8,136,361 B2Granted
Methods and apparatus for assembling a low noise ejector motive nozzle
AssigneeGeneral Electric Company
InventorsCarl Gerard Schott, Kevin W. Kinzie, John Joseph Lynch, David W. Ball, Gunnar Leif Siden, Kenneth Neil Whaling
Life of this patent
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Abstract
A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.
Claims9
A method of assembling an ejector, said method comprising;
- providing a motive nozzle tip having a centerline axis and including a chevron-shaped nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis, the motive nozzle tip having a frusto-conical portion that is downstream from a tapered conical portion of a motive nozzle, wherein the frusto-conical portion tapers at a first angle with respect to the centerline axis and the tapered conical portion tapers at a second angle with respect to the centerline axis, the first angle being different than the second angle;
- configuring the motive nozzle tip to produce lobed-shaped vortices in a stream discharged therefrom;
- and
- coupling the motive nozzle tip to the ejector, such that the motive nozzle tip is positioned within an ejector casing that includes a low-pressure chamber and an annular mixing channel defined therein, wherein the annular mixing channel is downstream from the low-pressure chamber.
1 more element
An ejector comprising a motive nozzle tip having a centerline axis and comprising:
- a frusto-conical portion that is downstream from a tapered conical portion of a motive nozzle, wherein said frusto-conical portion tapers at a first angle with respect to the centerline axis and said tapered conical portion tapers at a second angle with respect to the centerline axis, the first angle being different than the second angle;
- and
- a chevron-shaped nozzle tip edge comprising at least one protrusion extending through a plane substantially normal to the centerline axis, said motive nozzle tip is positioned within an ejector casing that includes a low-pressure chamber and an annular mixing channel defined therein, and is configured to produce lobed-shaped vortices in a jet discharged therefrom, wherein the annular mixing channel is downstream from the low-pressure chamber.
A gas turbine engine comprising:
- a compressor;
- and
- an ejector coupled in flow communication with said compressor and configured to receive air bled therefrom, said ejector comprising:
- a casing that includes a low-pressure chamber and an annular mixing channel;
- and
- a motive nozzle tip having a centerline axis and comprising a frusto-conical portion that is downstream from a tapered conical portion of a motive nozzle, wherein said frusto-conical portion tapers at a first angle with respect to the centerline axis and said tapered conical portion tapers at a second angle with respect to the centerline axis, the first angle being different than the second angle, said motive nozzle tip further comprising a chevron-shaped nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis, said nozzle tip positioned within said casing and upstream from said annular mixing channel, wherein said motive nozzle tip is configured to produce lobed-shaped vortices in a jet discharged therefrom.
3 more elements
Dependencies are inferred from the claim text.